A method for detecting an anomaly in a system of an aircraft, including obtaining a current series of measurements of one or more physical quantities of the system, during a time period when the system is in operation; —on the basis of the current series of measurements, providing, by an encoder-decoder, a current reconstructed series; and —comparing the reconstructed current series with the current series of measurements in order to obtain a current series of anomalies. The method further includes computing a current distribution function of the current series of anomalies; —computing an area separating the current distribution function from a reference distribution function; and —comparing the area with a predefined threshold.
G06N 3/0442 - Recurrent networks, e.g. Hopfield networks characterised by memory or gating, e.g. long short-term memory [LSTM] or gated recurrent units [GRU]
The invention relates to an airflow ejector nozzle (102, 126) for a turbine engine, in particular of an aircraft, the ejector nozzle extending about a longitudinal axis (XL), the nozzle being partially defined by a radially outer panel (2001) and a radially inner panel (2002) which, between them, at least partially form a flow stream for an airflow, the nozzle comprising a plurality of spacers (202) which extend radially between the outer and inner panels so as to keep them at a radial distance (HC, HS) from one another, the spacers being arranged about the longitudinal axis and each having a first radial end (3001) which is rigidly attached to one of the outer or inner panels, characterised in that each spacer comprises a second radial end (3002) which is opposite the first end and which is attached to the other one of the inner or outer panels so as to make it possible for the radial distance to be adjusted.
F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
3.
THRUST REVERSER COMPRISING MEANS FACILITATING THE MOUNTING OF A MEMBRANE FOR SEALING OFF THE SECONDARY FLOW PATH
A thrust reverser including a sealing membrane designed to deflect at least one portion of a secondary flow towards a deflection cascade when a movable structure of the reverser is in the retracted reverse-thrust position, the reverser including a rear frame for supporting the deflection cascade. The reverser further includes an interface device between the sealing membrane and a rear cascade structure including the rear cascade support frame, the vanes located furthest back on the deflection cascade, and a bearing member via which the cascade bears against the rear cascade support frame. Moreover, the device forms an elastic clip mounted around the rear structure, and a rear clip portion whereof is arranged behind the structure.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
4.
ASSEMBLY COMPRISING A STATIONARY SURFACE AND A MOVABLE SURFACE OF AN AIRCRAFT
An assembly for a propulsion unit including a stationary surface, a surface movable relative to the stationary surface, and a linking system to link the stationary surface and the movable surface and to allow the accommodation of a movement of the movable surface relative to the stationary surface. The linking system includes a linking device connected to the stationary surface, and a locking device connecting the linking device to the movable surface and including a fitting on which the linking device is mounted. The locking device, in an unlocking position, facilitates the displacement of the fitting relative to the movable surface during a movement of the movable surface relative to the stationary surface.
A triple-flow turbine engine for an aircraft, this turbine engine having a longitudinal axis and including upstream suspension elements which are located in a first plane perpendicular to the axis and are connected or fixed to the gas generator of the turbine engine; downstream suspension elements which are located in a second plane perpendicular to the axis and are connected or fixed to the gas generator; and thrust-absorbing rods which include first ends which are connected or fixed to the gas generator and opposing second ends which are located in a third plane perpendicular to the axis, wherein the first, second and third planes are located at a cold compartment of the gas generator.
F02C 7/20 - Mounting or supporting of plantAccommodating heat expansion or creep
F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
6.
SEAL COMPRISING A SUCCESSION OF ZONES WITH AND WITHOUT ANTI-FRICTION COATINGS
A seal is configured to be arranged between a first element and a second element of a propulsion assembly. The seal includes a longitudinal sector designed to be in contact with the second element, wherein the longitudinal sector is formed of an elastic leak-tight material and includes a first zone having an anti-friction coating, a second zone having a leak-tight coating, and a third zone having an anti-friction coating. The first, second and third zones arranged side by side and extend longitudinally from a first end to a second end of the longitudinal sector.
The invention relates to a thrust-reversal system for an aircraft turbojet engine (2), the thrust-reversal system (18) delimiting a secondary duct (16a), comprising an internal fixed structure (160) and an external fixed structure (162) connected together at at least one bifurcation (164, 166) delimited on either side by a wall (16a, 160b) of the internal fixed structure (160), the system comprising: at least one mobile cowl (20), which can move between a retracted position, and a deployed position; a set of air deflection devices; at least one sealing membrane (24), which can move between a retracted position and a deployed position; the sealing membrane (24) being attached to at least one fixed attachment element relative to the external fixed structure (162) and, at the front attachment points (240), to deployment devices (26, 28); the deployment devices (26, 28) comprising, for the or for each sealing membrane, at least a first and a second traction cable (28), each traction cable (28) being connected to the sealing membrane and to a drawing system (30), the drawing system (30) making it possible to pull on the traction cables during the deployment of the thrust-reversal device.
F02K 1/76 - Control or regulation of thrust reversers
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
8.
PROPULSION ASSEMBLY FOR AN AIRCRAFT, COMPRISING AN INTERMEDIATE COWL OF THE STATIONARY, REMOVABLE TYPE, MOUNTED ON A HINGE SYSTEM
An aircraft propulsion unit including a nacelle comprising a fan compartment, a front cowling forming an air inlet, and an intermediate section having at least one removable fixed intermediate cowling, externally delimiting the fan compartment, and attached to another structure of the propulsion unit by removable through fasteners. The intermediate cowling is connected to another element of the propulsion unit by means of a hinge system which, as a result of removing the removable through fasteners, is designed to allow the intermediate cowling to be moved between a closed position, in which it extends continuously with the front cowling, and an open position, in which the intermediate cowling is shifted upstream or downstream so as to open the fan compartment
F02K 7/00 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof
B64D 27/16 - Aircraft characterised by the type or position of power plants of jet type
B64D 29/00 - Power-plant nacelles, fairings or cowlings
F02C 7/042 - Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
The invention relates to a method for manufacturing a composite panel comprising a cellular core positioned between two skins, comprising the following steps: positioning a first resin layer (4) on a first mould (2); positioning a cellular-structure element (6) which has a cellular structure (8) arranged between two fibrous preforms (10, 12) intended to form the skins, a first of the fibrous preforms being positioned on the first resin layer; positioning a second resin layer (14) on the second of the fibrous preforms or on a second mould; positioning one or the second mould, the first mould and the second mould being arranged relative to one another such that the two moulds can move relative to one another; curing under vacuum, causing the resin to permeate the cellular-structure element and the two moulds to move relative to one another.
B29C 70/02 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising combinations of reinforcements and fillers incorporated in matrix material, forming one or more layers, with or without non-reinforced or non-filled layers
B29C 43/20 - Making multilayered or multicoloured articles
B29C 43/36 - Moulds for making articles of definite length, i.e. discrete articles
B29C 70/42 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B29C 70/46 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
B32B 5/24 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer
B32B 37/14 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers
10.
THRUST-REVERSAL SYSTEM FOR AN AIRCRAFT TURBOJET ENGINE, NACELLE AND PROPULSION UNIT COMPRISING SUCH A SYSTEM
The invention relates to a thrust-reversal system comprising: at least one movable cowl (20), movable between a retracted position and a deployed position; a set of air deflection devices (22); at least one shut-off device (24) for shutting off the secondary duct (16a) and movable between a retracted position corresponding to the retracted position of the movable cowl (20), in which position the shut-off device is at least partially housed in a space (200) provided in the movable cowl (20), and a deployed position corresponding to the deployed position of the movable cowl (20), in which position the shut-off device (24) is at least partially deployed into the secondary duct (16a), so as to deflect a majority portion of the secondary airflow towards the air deflection devices (22); the thrust-reversal system comprising at least one deployable membrane (22, 24), the deployable membrane (22, 24) comprising at least one reinforcement.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
The invention relates to an aircraft propulsion assembly (1) extending along a longitudinal axis (X) and comprising a turbine engine (2), a pylon (3) that connects the turbine engine (2) to the wing of the aircraft, an inner fairing (4) that surrounds the turbine engine (2), and an outer fairing (5) that circumferentially surrounds the inner fairing (4) and that comprises a right hollow cowl (10A) having an internal space and a left hollow cowl (10B) having an internal space, which cowls are capable of moving between a closed position and an open position. Each of the cowls (10A, 10B) comprises an upper part (20A, 20B) which is located below the pylon (3) when the cowl is in the closed position and the internal space of which forms an upstream flow path (V2A, V2B) that widens laterally from upstream to downstream, and further comprises a lower part (30A, 30B) that circumferentially extends the upper part (20A, 20B) downwards when the cowl is in the closed position, and the internal space of the lower part (30A, 30B) of each of the cowls (10A, 10B) forms a downstream flow path (V3A, V3B) that extends the upstream flow path (V2A, V2B).
An exhaust cone for an aircraft turbomachine, extending along a longitudinal axis and having a radially internal annular wall and a radially external skin delimiting a primary flow path for hot gases and surrounding the internal annular wall, and partitions mounted radially between the external skin and the internal annular wall and intersecting them in a manner that together with the skin and wall delimits acoustic chambers. The exhaust cone can further include at least one seal arranged between a radial end of one of the partitions and at least one among the internal annular wall and the external skin.
A gripper for gripping a honeycomb-shaped part and depositing the part on a target surface includes gripping elements mounted on a support, each of the gripping elements being configured to be inserted into an internal cell of the honeycomb-shaped part. The gripping elements include a gripping surface that is laterally moveable relative to the support so as to come into contact with a side wall element of the internal cell.
A method for manufacturing a multi-perforated acoustic skin out of composite material for an acoustic attenuation structure, the method including forming a fibrous preform including a matrix precursor material, carrying out a heat treatment for transforming the precursor into a matrix so as to obtain a multi-perforated acoustic skin made of composite material including a fibrous reinforcement densified by the matrix, the forming of the fibrous preform including draping fibers on a surface of a mandrel including protuberances, and the mandrel and the protuberances can be each made of a material that melts at a temperature lower than the heat-treatment temperature for transforming the precursor into a matrix in such a way as to eliminate the mandrel and the protuberances during the transforming heat treatment step.
B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
B29K 105/10 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns oriented
The invention relates to a propulsion assembly (1) comprising a turbomachine having a longitudinal axis, a nacelle, a first element (E1), a second element (E2) movable in translation with respect to the first element in a direction parallel to the longitudinal axis between a first and a second position and a fluidic circuit (70), the nacelle comprising at least one element from among the first and second elements, the propulsion assembly being characterized in that: the fluidic circuit (70) comprises a first duct (71) and a second duct (72) secured respectively to the first and second elements and respectively comprising first and second interlocking connectors (73, 74) configured to cooperate with one another so as to allow the fluid to flow between the first and second ducts when the second element is in the first position and to prevent the flow of the fluid when the second element is in the second position.
F02C 7/14 - Cooling of plants of fluids in the plant
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
16.
SURFACE HEAT EXCHANGER COMPRISING A PRESSURE LOSS REDUCER AND AIRCRAFT NACELLE PROVIDED WITH SUCH A HEAT EXCHANGER
The invention relates to a heat exchanger (20), in particular for an aircraft nacelle, comprising a first skin (21) and a second skin (22) joined together, and a plurality of channels (23) for distributing a hydraulic fluid (F1) arranged between the first skin (21) and the second skin (22), wherein the exchanger further comprises a first hydraulic interface (24) and a second hydraulic interface (29) for the hydraulic fluid. The exchanger (20) further comprises at least one pressure loss reduction member (40) extending axially towards the first hydraulic interface (24) or the second hydraulic interface (25), wherein the pressure loss reduction member (40) has a generally conical cross-section.
F02C 7/14 - Cooling of plants of fluids in the plant
F28D 3/02 - Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium flows in a continuous film, or trickles freely, over the conduits with tubular conduits
The invention relates to a hydraulic control device (10) for a thrust reverser (12) of an aircraft propulsion assembly nacelle, this device (10) comprising: a hydraulic motor (26), a first solenoid valve (28), referred to as the isolation solenoid valve, comprising a fluid inlet (28a) capable of being connected to a fluid source (24) of an aircraft, a fluid discharge line (34) fitted with a check valve (32), and a hydraulic circuit (36) for connecting the motor (26) to the isolation solenoid valve (28) and to the discharge line (34).
The invention relates to a hydraulic control device (10) for a thrust reverser (12) of an aircraft propulsion assembly nacelle, this device (10) comprising: - a hydraulic motor (26); - a first solenoid valve (28), referred to as the isolation solenoid valve, comprising a fluid inlet (28a) capable of being connected to a fluid source (24) of an aircraft; - a fluid discharge line (34) fitted with a check valve (32); - and a hydraulic circuit (36) for connecting the motor (26) to the isolation solenoid valve (28) and to the discharge line (34).
The invention relates to an acoustic panel (17) comprising at least: - a first box (18) comprising a first cellular structure (20) that comprises acoustic cells open at least at one of their ends, and a first porous acoustic structure (22) arranged on the first cellular structure (20) and closing off the end of the acoustic cells; - a second box (19) comprising a second cellular structure (21) that comprises acoustic cells that are open at least at one of their ends and a second porous acoustic structure (23) arranged on the second cellular structure (21) and closing off the end of the acoustic cells, wherein the first and second boxes (18, 19) are arranged next to one another and attached to one another, characterised in that the first porous acoustic structure (22) at least partially covers the second cellular structure (21) in a region of overlap (30).
The invention relates to an air inlet (1) for an aircraft turboprop (20) comprising an intake duct (2) for an air flow which leads, at a bifurcation (5), into a supply duct (3) to a turbine (25) and into an ejection duct (4) for ejecting foreign bodies from the air flow, the air inlet further comprising a heat exchanger (7) for cooling a heat transfer fluid, wherein a closure member (8) is controllable at the bifurcation (5) to assume: - a stowed position (P0) in which the air flow passes through the ejection duct (4) from the bifurcation (5) to a discharge outlet (6), a first deployed position in which the closure member (8) completely obstructs the ejection duct (4), and a second deployed position in which the closure member (8) partially obstructs the intake duct (2) in order to draw a reverse air flow into the ejection duct (4) when the aircraft is on the ground.
The invention relates to a thrust reverser for an aircraft propulsion unit, comprising a mobile structure (29) comprising at least one reverser cowl (33) having a cavity (54) open at the upstream end and delimited between a radially outer wall (50) and a radially inner wall (52) of the reverser cowl (33), the reverser also comprising a membrane (58) for shutting off the secondary flow path (21B), as well as a membrane-deployment member (62) connected to this membrane (58), and designed to be arranged at least partially in the secondary flow path (21B) when the mobile structure occupies its retracted thrust-reversal position. According to the invention, when the mobile structure (29) occupies its advanced forward-thrust position, the membrane-deployment member (62), in the form of a connecting rod, is at least partially housed in the cavity (54) of the mobile reverser cowl (33).
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
F02K 1/76 - Control or regulation of thrust reversers
22.
THRUST REVERSER WITH SEALING MEMBRANE AND RETENTION SYSTEM
The invention relates to a thrust reverser (1) for an aircraft propulsion unit, the thrust reverser (1) comprising a stationary structure (3), a movable structure (13) that is translatable with respect to the stationary structure (3) between a thrust position and a thrust reversal position, at least one sealing membrane (17) designed to deflect at least part of the secondary flow towards the outside, at least one retention system (21) designed to engage with the stationary structure (3) and the corresponding sealing membrane (17), the retention system (21) being configured to subject the corresponding sealing membrane (17) to a return force comprising a component opposite to the general direction of flow in the thrust reversal position.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
F02K 1/76 - Control or regulation of thrust reversers
23.
METHOD FOR JOINING TWO ANODISED ELEMENTS BY FRICTION STIR WELDING
The present application describes a method for joining two anodized elements by friction stir welding. This method for joining a first element to a second element comprises a step of anodizing the first element, a step of anodizing the second element, and a step of producing a weld seam by friction stir welding the first element to the second element.
B23K 20/12 - Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by frictionFriction welding
B23K 20/233 - Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating taking account of the properties of the materials to be welded without ferrous layer
A propulsion assembly for an aircraft equipped with a thrust reverser comprising an actuator for moving a movable structure between an advanced direct thrust position and a retracted thrust reversal position, the propulsion assembly further comprising an actuator support device equipped with a first connecting part for connecting it to the deflection edge and/or to the outer shell of the intermediate casing, with a second connecting part for connecting it to a body of the actuator, and with a central part running axially between the shell and the actuator. Moreover, the actuator support device forms a guide for a set of cascades of the movable structure.
F02K 1/76 - Control or regulation of thrust reversers
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
25.
THRUST REVERSER COMPRISING AN IMPROVED SAFETY SYSTEM FOR DEPLOYING A MEMBRANE FOR SEALING OFF THE SECONDARY FLOW PATH
The invention relates to a thrust reverser for an aircraft propulsion assembly, comprising a membrane for sealing off a secondary flow path, and at least one connecting rod for deploying this membrane, which is designed to be moved from a first position in which it projects radially into the secondary flow path, when the mobile structure occupies its advanced direct-thrust position, to a second position in which it is folded down in the downstream direction, when the mobile structure occupies its retracted thrust-reversal position. According to the invention, the reverser also comprises a device (70) for actuating the connecting rod (62), equipped with a safety system (120) for limiting the risks of poor kinematics.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
F02K 1/76 - Control or regulation of thrust reversers
An acoustic panel comprising a first group of cavities oriented towards a front end of the panel and a second group of cavities oriented towards a rear end of the panel.
B32B 15/092 - Layered products essentially comprising metal comprising metal as the main or only constituent of a layer, next to another layer of a specific substance of synthetic resin comprising epoxy resins
B32B 15/20 - Layered products essentially comprising metal comprising aluminium or copper
F02C 7/045 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
The invention relates to a nozzle for ejecting a turbine engine air flow, in particular for an aircraft, the ejector nozzle extending firstly around a longitudinal axis (X) and secondly between an inlet cross-section and an outlet cross-section along the longitudinal axis (X), the ejector nozzle being delimited at least in part by an external structure (22) and an internal structure (23) having an axis of revolution centred on the longitudinal axis and at least partially forming a flow path. According to the invention, the internal structure (23) is removably mounted with respect to the external structure (22) and is removably attached to a radially inner shroud (25) extending axially downstream of the internal structure (23) and partially defining the outlet cross-section (21), and the internal structure comprises retaining means ensuring that a radial height (H2) of the outlet cross-section (21), during operation, remains fixed and constant.
F02K 3/02 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
28.
AIR FLOW EJECTOR NOZZLE WITH A CONSTANT OUTLET CROSS-SECTION AND TURBINE ENGINE PROVIDED WITH SUCH A NOZZLE
The invention relates to a nozzle for ejecting a turbine engine air flow, in particular for an aircraft, the ejector nozzle extending firstly around a longitudinal axis (X) and secondly between an inlet cross-section (20) and an outlet cross-section (21) along the longitudinal axis (X), the ejector nozzle being delimited at least in part by a radially outer shroud (24) and a radially inner shroud (25) at least partially forming a flow path (18, 15). According to the invention, a plurality of struts (45) extend radially between the radially outer shroud (24) and the radially inner shroud (25), and the struts (45) are arranged regularly around the longitudinal axis (X) and have a predetermined height (H1) configured such that a radial height (H2) of the outlet cross-section (21), during operation, remains fixed and constant.
F02K 3/02 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
29.
AIRFLOW EJECTION NOZZLE WITH CONSTANT OUTLET SECTION AND TURBINE ENGINE EQUIPPED WITH SUCH A NOZZLE
The invention relates to a turbine engine airflow ejection nozzle, in particular for an aircraft, the ejection nozzle extending about a longitudinal axis (X) and between an inlet section (20) and an outlet section (21) along the longitudinal axis (X), the ejection nozzle being at least partially delimited by a radially outer shroud (24) and a radially inner shroud (25) at least partially forming a flow path (18, 15). According to the invention, a plurality of struts (45) extend radially between the radially outer shroud (24) and the radially inner shroud (25), and the struts (45) are arranged evenly about the longitudinal axis (X) and have a predetermined height (H1) configured so that a radial height (H2) of the outlet section (21), during operation, is fixed and constant.
F02K 3/02 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
30.
AIR FLOW EJECTOR NOZZLE WITH DETACHABLE INTERNAL STRUCTURE AND TURBINE ENGINE PROVIDED WITH SUCH A NOZZLE
The invention relates to a nozzle for ejecting a turbine engine air flow, in particular for an aircraft, the ejector nozzle extending firstly around a longitudinal axis (X) and secondly between an inlet cross-section and an outlet cross-section along the longitudinal axis (X), the ejector nozzle being delimited at least in part by an external structure (22) and an internal structure (23) having an axis of revolution centred on the longitudinal axis and at least partially forming a flow path. According to the invention, the internal structure (23) is removably mounted with respect to the external structure (22) and is removably attached to a radially inner shroud (25) extending axially downstream of the internal structure (23) and partially defining the outlet cross-section (21), and the internal structure comprises retaining means ensuring that a radial height (H2) of the outlet cross-section (21), during operation, remains fixed and constant.
F02K 3/02 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
A de-icing system which includes actuators attached to the part; and a device for controlling the actuators in order to vibrate the part. The control device is designed for the following, the actuators being divided into a plurality of groups: to control the actuators of a first one of the groups in order to establish a resonant frequency of the part; then to control the actuators of a second one of the groups in order to establish a resonant frequency of the part and, in parallel, to control the actuators of the first group in order to de-ice the part by vibrating it, using the resonant frequency established with this first group.
B64D 15/16 - De-icing or preventing icing on exterior surfaces of aircraft by mechanical means, e.g. pulsating mats or shoes attached to, or built into, surface
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
32.
THRUST REVERSER COMPRISING AT LEAST ONE DEPLOYABLE MEMBRANE, HAVING LOW-MASS DEPLOYMENT MEANS
The invention relates to a thrust reverser for an aircraft propulsion assembly, the thrust reverser comprising a membrane (58) for closing the secondary duct, a second end of which membrane is connected to the inner wall of the secondary duct by a cable (62) that co-operates with an actuating device (70) for actuating this cable, wherein the device (70) comprises an elastic means (80) that co-operates with the second cable end (62b) of the deployment member (62), and wherein the reverser is configured such that, during an initial phase of the movement of the movable structure towards its retracted thrust reversal position, the elastic means (80) releases previously stored energy while urging the second cable end (62b), and such that, during a subsequent phase of this movement of the movable structure, the elastic means (80) stores energy while being urged by this second end (62b).
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
F02K 1/76 - Control or regulation of thrust reversers
33.
Thrust reverser comprising movable cascades and a sealing membrane
A thrust reverser for an aircraft propulsion assembly, including at least one sealing membrane designed to deflect at least one portion of the secondary flow towards a set of cascades when the movable structure of the reverser is in the retracted thrust reversal position, the reverser also including a first flexible hook connecting a first end of the membrane to the fixed structure of the reverser, a second hook connecting a second end of the membrane to the fixed structure or to the movable structure, the second hook being fixed to the radially inner delimiting wall of the secondary vein, or guided by an internal guide fixed to the same radially inner delimiting wall.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
F02K 1/60 - Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
F02K 1/62 - Reversing jet main flow by blocking the rearward discharge by means of flaps
34.
METHOD FOR PRODUCING A PART MADE OF COMPOSITE MATERIAL
A method for producing a part made of composite material, includes obtaining a mold includes (i) a fibrous texture, (ii) a granular filtration layer located between a drainage surface of the texture and a permeable discharge surface and including a powder of filtration particles, and (iii) an element for retaining the granular layer, which element is distinct from the layer and located between the permeable discharge surface and the drainage surface, introducing a suspension including matrix particles in a liquid medium through an introduction surface of the fibrous texture that is distinct from the drainage surface, the liquid medium passing through the drainage surface, the granular filtration layer and the retention element to be discharged through the permeable discharge surface, and the matrix particles being retained in the pores of the fibrous texture by the granular filtration layer, and forming the part made of composite material by forming a matrix.
B28B 1/26 - Producing shaped articles from the material by slip-casting, i.e. by casting a suspension or dispersion of the material in a liquid-absorbent or porous mould, the liquid being allowed to soak into or pass through the walls of the mouldMoulds therefor
06 - Common metals and ores; objects made of metal
07 - Machines and machine tools
40 - Treatment of materials; recycling, air and water treatment,
42 - Scientific, technological and industrial services, research and design
Goods & Services
Steel buildings; metal tanks [structures]; common metals and
their alloys, including stainless steel; anti-friction
metal; extruded metal; white metal; sheet metal; steel
sheets; sheets of metal; forged metal parts; pressed metal
parts; steel; stainless steel; unwrought or semi-wrought
steel; alloys of common metals; aluminum; steel alloys. Machines for metal machining. Treatment of metals; metal treating, namely stamping,
forming, profiling, embossing, hydroforming; treatment of
metals by hydroforming based on explosives; providing metal
forming services by explosive-based hydroforming; metal
processing and shaping using the technique of hydroforming
based on explosives for production of metal parts complying
with particular specifications; customization and adaptation
of metal parts via hydroforming based on explosives for
third parties; heat treatment of metals; stamping services;
deep-drawing of metals; shaping of metal components; custom
assembly of materials for third parties; welding services;
machining of parts for third parties. Scientific, technical and industrial research relating to
materials and metals; research and development of new
products relating to materials and metals; technical
advisory services, engineering and expertise (engineering
work) in the field of materials and metals; machine and
material testing; material testing and analysis services;
design of technological demonstrators; engineering services
relating to metal forming systems; metal forming feasibility
study.
36.
THRUST REVERSER COMPRISING AT LEAST ONE DEPLOYABLE DEFLECTION MEMBRANE WITH IMPROVED ATTACHMENT
The invention relates to a deployable membrane (58) for closing off a secondary flow duct for a thrust reverser of an aircraft propulsion assembly, wherein the membrane extends in a circumferential direction (27) and comprises a membrane extension (70) configured so as to form a strap, a projecting portion of which comprises a first connecting section (70a) for attachment to the membrane, and a second connecting section (70b) intended to be connected to a membrane deployment element (62) located within the reverser, and wherein the strap comprises a transition zone (70c) arranged between its first connecting section (70a) having a first width (L1) in the circumferential direction (27), and its second connecting section (70b) having a second width (L2) strictly smaller than the first width (L1).
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
37.
DEVICE FOR HANDLING AN ELEMENT OF AN AIRCRAFT AND HANDLING ASSEMBLY PROVIDED WITH SUCH A DEVICE
The invention relates to a device (2) for handling an element (E) of an aircraft, the device comprising a shell (5) that is intended to surround the element, a cradle (6) defining a region for receiving the shell, and a support platform (13) on which the cradle is mounted, wherein the platform is capable of co-operating with a lifting system (3) of the device. The device comprises first means for adjusting the angular position of the cradle relative to the platform and second means for adjusting the position of the cradle along three degrees of freedom relative to three perpendicular axes, respectively.
A thrust reverser for an aircraft propulsion assembly, including a fixed structure equipped with at least one cascade as well as a radially inner delimiting wall of a secondary vein, and a movable structure including at least one reverser cowling, the cascade being arranged, in the forward direct thrust position, in a housing of the reverser cowling, and, in the retracted thrust reversal position, the wall reveals a passage opening of the secondary vein towards the cascade, the thrust reverser also including at least one sealing membrane designed to deflect at least one portion of the secondary flow. A hook is provided for securing the membrane to a rear cascade support frame, and to the radially inner delimiting wall of the secondary vein.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
39.
THRUST REVERSER COMPRISING AT LEAST ONE DEPLOYABLE DEFLECTION MEMBRANE HAVING A DESIGN THAT FACILITATES MAINTENANCE
The invention relates to a thrust reverser for an aircraft propulsion assembly, the reverser comprising two membrane support frames (60, 70) and a membrane support connecting rod (66) connected at its ends to the frames by two mechanical connections (67, 69), and a deployable deflection membrane (32), the reverser being configured such that, when the first mechanical connection (67) is in an attached state and the second mechanical connection (69) is in a detached state, the support connecting rod (66) can be brought into a maintenance configuration in which the second end (66b) of the connecting rod is located farther away from the second membrane support frame (60) than in the nominal configuration, thereby allowing relative movement of the membrane along the connecting rod in order to disengage it from the latter via the second end (66b) of the connecting rod.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
40.
METHOD FOR MANUFACTURING AN OPEN PART WITH REINFORCED RIBS
The invention relates to a method for manufacturing an open part (10) made of composite material and comprising a skin (12), ribs extending in an associated direction of extension, and at least one reinforced rib (14) having a reinforced head (22), the method comprising: - providing a first fibre preform (PF1) for forming the skin and the body of the ribs; - providing a second fibre preform (PF2) for forming the reinforced head of the reinforced ribs; - placing the assembly formed of the first and second fibre preforms in a moulding device (30) comprising a die (32) shaped to form the ribs of the part; and - thermocompressing the assembly to form the part; and the first preform comprises discontinuous fibres (PF12) for forming the body, while the second preform comprises continuous fibres oriented in the direction of extension.
B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29D 99/00 - Subject matter not provided for in other groups of this subclass
41.
METHOD FOR PRODUCING A PART MADE OF COMPOSITE MATERIAL AND HAVING RAISED ELEMENTS, AND CORRESPONDING PART
The invention relates to a part (20) made of composite material for a turbine engine, in particular for an aircraft, the part comprising: - a composite skin (22) having an inner face (28) and an outer face (26), the composite skin comprising continuous fibres; and - at least one element (24) extending in an associated direction of extension (X), each element (24) comprising a body (30) extending from the inner face (28) of the skin to a free end (32) in a direction of elevation (Z) different from the direction of extension, each body (30) being connected to the inner face by at least one fillet (36, 36'), the body being made of a composite material predominantly comprising discontinuous fibres; characterised in that the part (20) further comprises an additional skin (40) of continuous fibres covering at least the at least one fillet for connecting the body to the inner face of the skin.
B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29D 99/00 - Subject matter not provided for in other groups of this subclass
42.
PROPULSION ASSEMBLY WITH LONGITUDINAL LOCKING OF AT LEAST ONE NACELLE COVER
The invention relates to a propulsion assembly (1) for an aircraft, the assembly comprising: a turbine engine; a nacelle (5) having a section provided with at least one cover (7) that is movably mounted so as to deploy between a working position and a maintenance position for the purpose of providing access to a turbine engine (3); a pylon (11) suitable for attaching the turbine engine and/or the nacelle (5) to the aircraft; a longitudinal locking mechanism (19) comprising, for each cover (7), a finger (21) and a sleeve (23) provided with two retaining portions extending transversely to the corresponding longitudinal axis (17), wherein the finger (21) is configured so as to be guided between the two retaining portions in the maintenance position; and wherein the sleeve (23) is attached to the corresponding cover (7) or to an element connected to the corresponding cover (7), and the finger (21) is attached to the pylon (11), or vice versa.
A movable-cascade thrust reverser includes a multi-functional annular fixed structure configured to be rigidly connected to a turbine engine fan casing or to an intermediate casing secured to the fan casing
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
44.
Air intake lip for a nacelle of an aircraft propulsion assembly
An annular air intake lip for a nacelle of an aircraft propulsion assembly is provided. The annular lip can extend about an axis of revolution and include: an external annular wall, an internal annular wall, an upstream annular wall connecting the external and internal annular walls to define an annular cavity therebetween. At least part of the annular lip can include at least one heat transfer coating that is made from a carbon allotrope material.
A system for cooling a liquid for lubricating an aircraft turbomachine, includes an exchanger including a cooling volume and a circuit for cooling a heat-transfer fluid by a loop for circulating the two-phase fluid, with thermocapillary pumping. The cooling circuit includes a condenser including channels connected in parallel to one another in order to make it possible to cool the fluid circulating in the condenser from a vapour state to a liquid state, a first capillary evaporator of the exchanger in order to absorb the heat of the lubricating liquid in the first volume, the first evaporator including a capillary porous wick for separating the heat-transfer fluid in the two-phase state between a liquid state and a gaseous state by a capillary pressure jump.
An electronic device for diagnosing the condition of a system of actuators of an aircraft turbine engine, the device being configured to be coupled to an electrical wiring harness of a turbine engine connecting a computer of a turbine engine to a system of actuators of the turbine engine, the device including a power supply block to power the device, a connection block configured to enable the connection of the device to the electrical wiring harness of the turbine engine to be diagnosed, a communication block configured to send information to a user and to receive instructions from the user, and a control block including a test signal transmission module and modules for measuring the signals received by the device in response to the test signals over a work cycle of the system of actuators of the turbine engine.
B64F 5/60 - Testing or inspecting aircraft components or systems
G01R 31/00 - Arrangements for testing electric propertiesArrangements for locating electric faultsArrangements for electrical testing characterised by what is being tested not provided for elsewhere
G01R 31/28 - Testing of electronic circuits, e.g. by signal tracer
47.
REMOTE TRIGGERING OF A FIRE EXTINGUISHING OPERATION IN A FIRE ZONE OF A PROPULSION SYSTEM
An assembly for an aircraft propulsion system including a nacelle extending around a longitudinal axis and including an internal face that delimits, with an external face of the aircraft propulsion system, a fire zone, an extinguisher for extinguishing a fire in the fire zone, the extinguisher including a tank for containing an extinguishing agent, and a spraying nozzle for spraying the extinguishing agent out of the tank and into the fire zone, an activation device for activating the extinguisher, and a controller that transmits a control order to the activation device, the activation device receiving the control order and transmitting an activation order to the extinguisher, the activation order activating the extinguisher so as to cause the expulsion of the extinguishing agent via the nozzle. The extinguisher is mounted on the nacelle. The assembly includes one or more of a wireless communicator and a cable.
A62C 3/08 - Fire prevention, containment or extinguishing specially adapted for particular objects or places in vehicles, e.g. in road vehicles in aircraft
A62C 37/36 - Control of fire-fighting equipment an actuating signal being generated by a sensor separate from an outlet device
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
48.
THRUST REVERSER GRILLE FOR AN AIRCRAFT NACELLE AND METHOD FOR PRODUCING SUCH A GRILLE
The invention relates to an air-deflecting grille (5) for an aircraft nacelle thrust reverser system, the grille (5) comprising at least two longitudinal members (6) extending in a longitudinal direction (L) of the grille, each longitudinal member (6) being connected to at least one adjacent longitudinal member by a plurality of vanes (7), the grille (5) comprising, at each of its longitudinal ends, an attachment flange extending in a transverse direction (T) of the grille (5) and being secured to end vanes connecting the corresponding ends of the longitudinal members (6), each longitudinal member (6) being formed from at least one fibrous ply (60) comprising: •- at least one first portion (600), or longitudinal portion (600), extending in the longitudinal direction (L) of the grille (5); and •- at least one second portion (602), or transverse portion (602), extending in the transverse direction (T) of the grille (5), so as to form at least a portion of at least one end vane.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
49.
INTEGRATING AN EXTINGUISHER INTO A "FIRE" ZONE OF A TURBOMACHINE
An assembly for an aircraft gas turbine engine includes a nacelle extending substantially around a longitudinal axis and including a fixed structure disposed around the aircraft gas turbine engine, the fixed structure including an internal surface suitable for delimiting with an external surface of the gas turbine engine a fire zone of the nacelle, a thermal protection covering the internal surface of the fixed structure of the nacelle at the level of the fire zone of the nacelle, and an extinguisher designed to extinguish a fire in the fire zone of the nacelle, the extinguisher including a tank suitable for containing an extinguishing agent. The tank is located between the thermal protection and the internal surface of the fixed structure of the nacelle.
A62C 3/08 - Fire prevention, containment or extinguishing specially adapted for particular objects or places in vehicles, e.g. in road vehicles in aircraft
B64D 29/00 - Power-plant nacelles, fairings or cowlings
The invention relates to a cellular structure for an acoustic panel, the cellular structure comprising: - at least one acoustic cell comprising a cavity bounded by a peripheral wall; and - at least one first partition (24) arranged in the cavity to divide the cavity into two, the first partition (24) comprising a first acoustically permeable membrane (25), characterised in that the first partition (24) further comprises first lugs (26), each first lug (26) being received in a respective first slot formed in the peripheral wall to mechanically fasten the first partition (24) in the corresponding cavity.
An assembly for an exhaust cone of an aircraft turbomachine, including a first annular wall, and first partitions and second partitions defining between them a plurality of acoustic boxes distributed around the first wall, an assembly formed by the first and the second partitions being fastened to the first wall with first fastening members arranged upstream and with second fastening members arranged downstream, the first fastening members being offset circumferentially with respect to the second fastening members.
An assembly for an ejection cone of an aircraft turbomachine, including a first annular wall and a plurality of first partitions and of second partitions extending substantially perpendicularly from the first wall, the first partitions additionally extending wholly in the axial direction and the second partitions extending wholly in a circumferential direction between the adjacent pairs of first partitions and being curved partitions including at least one arcuate portion in the axial direction upstream or downstream, the first wall, the first partitions and the second partitions additionally defining between them a plurality of acoustic boxes distributed around the first wall.
An open composite panel for an aircraft includes a composite skin having an inner face and an outer face, and a plurality of stiffening ribs, each rib extending over the inner face of the skin in a respective direction of extension and projecting from the inner face to a top that is opposite said inner face. The plurality of ribs includes at least one reinforced rib, each reinforced rib having at least one elongate stiffening portion extending along the top of the reinforced rib, said stiffening portion including fibers extending substantially in the direction of extension of the reinforced rib.
The invention relates to an installation for assembling a core of a panel of a turbomachine, comprising: - a fairing (12) having an outlet slot (112) for an adhesive tape (106), - a first reel (104) for storing and dispensing the adhesive tape (106) to the outlet slot (112), the adhesive tape (106) being intended to be stored around the first reel (104) and having at least one contact face with a first protective film (114, 116), - a second reel (108, 110), for returning the first protective film (114), mounted outside the fairing (12), - the second reel (108, 110) being configured to wind up the protective film (114, 116) as the adhesive tape (106) is unwound from the first reel (104) towards the outlet slot (112).
The invention relates to an installation for assembling the core of a panel of an aircraft turbine engine, comprising a bonding system (100) comprising: - a member (102) for storing and dispensing the adhesive (25), and - a nozzle (104) for ejecting the adhesive (25), the nozzle (104) extending between a first open end (106) connected to the storing and dispensing member (102) and a second open opposite end (108) for discharging the adhesive (25), the nozzle (104) further comprising an internal passage (105) for the adhesive (25), extending between the first and second ends (106, 108).
A nacelle for an aircraft propulsion unit includes an air intake cowl, and an intermediate section including fixed and removable hoods defining an access space between front ends of the hoods and an outer rear end of the air intake cowl. The intermediate section includes an annular row of mutually spaced connecting parts which rigidly connect the outer rear end of the air intake cowl to the front ends of the hoods so as to transmit longitudinal forces, and an intermediate cowl extending between the air intake cowl and the hoods, around the connecting parts, thereby closing the access space and creating aerodynamic continuity with the air intake cowl and the hoods. The intermediate cowl is formed from at least one strip which is held in place by tangential clamping of the circumferential ends of the strip.
The invention relates to an actuating device (1) for an aircraft thrust reverser system (3) comprising at least one thrust reverser device (2), the actuating device (1) comprising at least one motorized drive unit (10) situated on an upstream side of a first lost-motion lock (12a) and designed to actuate an input shaft (11) of this first lock (12a), the first lock being designed, when unlocked, to actuate an output shaft driving a flexible synchronization shaft (13) situated on a downstream side, and the actuating device (1) further comprising at least one first movable jack rod (14b) which is mechanically connected to the flexible synchronization shaft and secured to a movable element of the thrust reverser device (2), the first movable rod belonging to a first set of movable rods which is associated with the first lock (12a).
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
F02K 1/76 - Control or regulation of thrust reversers
58.
MULTIAXIAL FIBRE SHEET COMPRISING METAL ELEMENTS FOR PRODUCING A COMPOSITE MATERIAL PART
The present invention relates to a multiaxial fibre sheet (10) for producing a composite material part (100) for a turbine engine, in particular an aircraft turbine engine, the multiaxial fibre sheet (10) being formed by a stack of multiple layers of fibres (12, 14, 16), each of the layers of fibres comprising unidirectional fibres (12a, 14a, 16a) oriented in different directions from the fibres (12a, 14a, 16a) of the other layers of fibres (12, 14, 16), the layers of fibres (12, 14, 16) being connected to one another by connecting yarns (18), wherein at least one of the layers of fibres (12, 14, 16) is embedded with metal elements (40) configured to dissipate an electric current produced by a lightning strike on the multiaxial fibre sheet (10).
B29C 70/20 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in a single direction, e.g. roving or other parallel fibres
B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
A rear assembly for a turbojet engine nacelle includes at least one composite wall separating a cold portion from a hot portion comprising an element to be cooled, the composite wall having first and second skins which extend facing the cold portion and the hot portion respectively, and which are separated from one another by a middle assembly having cells delimited by internal walls. The first skin includes a plurality of through-openings connecting the cold portion and the cells, the internal walls having through-openings connecting the cells to one another, and the second skin having a through-opening which has its mouth facing the element to be cooled.
An air intake module for an aircraft turbomachine extending along a longitudinal axis oriented from upstream to downstream and including an inner wall and an outer wall defining together a vein for circulating an air flow, a plurality of guide vanes of the air flow extending radially in the vein and each comprising an upstream leading edge, at least one stator member fixedly mounted on the inner wall and on the outer wall and extending radially in the vein upstream of the guide vanes, the stator member comprising an infrared wave emitting device configured to emit an infrared beam on the leading edge of at least one of the guide vanes for de-icing it.
Application head for automated fiber placement, which application head includes at least: an application roller that is designed to apply fibers to a shaping tool which application roller is rotatably movable on its axis for applying fibers to the shaping tool, and a feed device includes a winding of a strip of fibers having a predefined orientation, the strip of fibers being configured to be transferred by unwinding from the feed device onto the application roller with at least one portion of the fibers of the strip being oriented such that they are not perpendicular to the axis of the roller.
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
62.
SYSTEM FOR COOLING A REFRIGERANT FOR AN AIRCRAFT COMPRISING A SAFETY HEATING DEVICE AND METHOD FOR USING SUCH A SYSTEM
A system (1) for cooling a refrigerant (R) for an aircraft comprising a plurality of ducts (2) for circulating the refrigerant (R) that are configured to be at least partially in contact with an airflow (A) so as to cool the refrigerant (R) through convection, the cooling system (1) comprising a safety heating device (3) extending internally inside at least one portion of the circulation ducts (2) so as to heat the refrigerant (R), a member (4) for measuring a physical parameter of the refrigerant (R) according to the flow rate of the refrigerant (R) in the circulation ducts (2) and a control member (5) configured to activate the safety heating device (3) when the measured physical parameter is below a predetermined threshold corresponding to a minimum flow rate of the refrigerant (R) in the circulation ducts (2).
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
63.
METHOD AND DEVICE FOR MACHINING AN AERONAUTICAL WORKPIECE
The invention relates to a method (300) and a machining tool for machining a workpiece (1) having a surface (S1, S2) intended to be machined and connected to an edge (B1) of the workpiece (1), the surface (S1, S2) and the edge (B1) extending along a length L1 of the workpiece (1), the method comprising the steps of: a) applying a machining tool (100) to the workpiece (1), the tool (100) comprising at least one reference guide (104, 106a, 106b, 106c) which is brought to bear against the surface (S1, S2) and/or the edge (B1) of the workpiece (1); b) moving the tool (100) along the length L1 so that the rotary member (102) machines the part of the surface according to a predetermined shape profile (PF1, PF2, PF3, PF4), the tool (100) being maintained in bearing contact with the workpiece (1) during this movement.
B23Q 9/02 - Arrangements for supporting or guiding portable metal-working machines or apparatus for securing machines or apparatus to workpieces, or other parts, of particular shape, e.g. to beams of particular cross-section
B23C 3/12 - Trimming or finishing edges, e.g. deburring welded corners
B24B 9/00 - Machines or devices designed for grinding edges or bevels on work or for removing burrsAccessories therefor
64.
AIR INLET OF AN AIRCRAFT TURBOMACHINE NACELLE, AND ASSOCIATED METHOD
An air inlet of an aircraft turbomachine nacelle (1) extending along a main axis (X) oriented from front to rear, the air inlet comprising at least one acoustic device (3) comprising an acoustic core (30) on the inner wall (21) between the inner wall (21) and the outer wall (22), the inner wall (21) comprising at least one perforated portion (21P) facing the acoustic core (30) so as to allow the passage of acoustic waves, and at least one vibratory de-icing member (4) positioned in the inner cavity (20) between the acoustic core (30) and the perforated portion (21P), the vibratory de-icing member (4) being in contact with the perforated portion (21P) of the inner wall (21) in order to make it vibrate, and at a distance from the acoustic core (30).
B64D 15/16 - De-icing or preventing icing on exterior surfaces of aircraft by mechanical means, e.g. pulsating mats or shoes attached to, or built into, surface
F02C 7/045 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
65.
METHOD FOR MANUFACTURING AN AERODYNAMIC PANEL FOR AN AIRCRAFT PROPULSION ASSEMBLY
The invention relates to a method for manufacturing an aerodynamic panel (32) for an aircraft propulsion assembly (10), the method comprising the following steps: a) applying at least one reinforcement plate (38, 42, 44) to a first face (34a) of a wall (34); b) rigidly attaching the reinforcement plate (38, 42, 44) to the wall (34, 36) by friction stir welding; c) producing through-holes (50) through the wall (34) and the reinforcement plate (38, 42, 44), these holes (50) being formed through the weld seam (40); and d) fitting screws (52, 54, 56) into the holes (50), these screws (52, 54, 56) comprising countersunk heads (58) that have a thickness (H) greater than the thickness (E1) of the wall (34) and less than the thickness (E3) of the weld seam (40).
B64D 29/00 - Power-plant nacelles, fairings or cowlings
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
B23K 20/12 - Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by frictionFriction welding
66.
THRUST REVERSER COMPRISING AT LEAST ONE DEPLOYABLE DEFLECTING MEMBRANE
The invention relates to a thrust reverser for an aircraft propulsion assembly, comprising a deployable deflecting or obstructing membrane (132) designed to deflect or obstruct at least a portion of the secondary flow escaping from a radial extraction opening when this membrane is in a deployed configuration adopted when the movable structure of the reverser is in a retreated thrust reversal position. According to the invention, in this deployed configuration, the membrane (132) has a generally radially outwardly curved shape defining, at a base (108) of the membrane, an air inlet opening (110) via which air can enter the membrane, the membrane (132) extending between: - a membrane front portion (102) forming a forward flap reaching to the base of the membrane; and - a membrane rear portion (104) forming a rearward flap reaching to the base of the membrane.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
67.
METHOD FOR DEPOSITING A METAL COATING BY THERMAL SPRAYING AND MIXTURE FOR IMPLEMENTING SUCH A METHOD
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventor
Monerie-Moulin, Francis
Riquet, Audrey
Le Sausse, Nicolas
Abstract
The invention relates to a method (100) for depositing a metal coating (R) by thermal spraying, which method comprises the following sequential steps: - providing a surface (S) to be coated (110), a tank (2) for a mixture and a metal spraying device (1) connected to the tank, the mixture comprising ellipsoidal metal particles (PMe) and ellipsoidal mineral particles (PMi) having a hardness that is greater than a hardness of the surface and a melting point that is strictly greater than the melting point of the metal particles; - heating the mixture (120) to a temperature below the melting point of the metal particles via neutral gas so as to obtain partially softened and ductile metal particles; - spraying the mixture (130) through the nozzle (20) so as to form a jet of material in the direction of the surface and to form the metal coating on this surface.
C23C 24/08 - Coating starting from inorganic powder by application of heat or pressure and heat
B05B 7/20 - Spraying apparatus for discharge of liquids or other fluent materials from two or more sources, e.g. of liquid and air, of powder and gas incorporating means for heating the material to be sprayed by flame or combustion
C23C 24/10 - Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
C23C 24/04 - Impact or kinetic deposition of particles
68.
STRUCTURAL AND/OR ACOUSTIC PANEL OF A NACELLE OF AN AIRCRAFT PROPULSION ASSEMBLY AND RELATED MANUFACTURING METHOD
A method for manufacturing a panel for a nacelle of an aircraft propulsion assembly includes: preparing mold elements each including lateral faces, an upper face, and a lower face; draping a material on a portion of the upper face and/or the lower face and at least one of the lateral faces of each of the mold elements to form at least one fold; and extracting the mold elements such that the at least one fold forms a cellular structure of the panel. The portion of the material on the upper face and/or the lower face forms a peripheral portion of the fold. The portion on the at least one of the lateral faces of each of the mold elements forms a central portion of the fold. The central portion is a portion of transverse partition walls of the panel, which define a plurality of cells.
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
The invention relates to a thrust reverser for an aircraft propulsion assembly, comprising a deployable deflecting membrane (232) designed to deflect or obstruct at least a portion of the secondary flow escaping from a radial extraction opening when this membrane is in a deployed configuration adopted when the movable structure of the reverser is in a retreated thrust reversal position. According to the invention, the membrane (232) has a generally radially outwardly curved shape extending between a membrane front end secured to a front frame of the support structure (266) and a membrane rear end secured to a rear frame of the support structure.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
70.
DEVICE FOR ATTACHING A HEAT SHIELD TO AN AIRCRAFT PANEL AND ASSOCIATED METHOD
The invention relates to a device (1) for attaching a heat shield (2) to an aircraft panel (3), the device comprising a first attachment element (4) associated with the heat shield (2), a second attachment element (5) associated with the aircraft panel, and a metal wire (6) forming a loop (7). At least one of the attachment elements is provided with means (10, 11) for retaining the loop, the loop being closed by a braking member (12) of the ends (9) of the loop intended for bringing the attachment elements together, the loop abutting one of the attachment elements at its middle portion (8) and the other one of the attachment elements at the braking member (12), respectively. The loop is set apart from the heat shield (2) and the aircraft panel (3), and passes outside the heat shield (2) and the aircraft panel (3).
The invention relates to an acoustic panel (12) with resonators for an aircraft propulsion assembly nacelle, the acoustic panel (12) comprising adjoining acoustic cells (28) which form a cellular core (24), each acoustic cell (28) comprising an enclosure (30) extending along an acoustic propagation axis (L) of the acoustic waves and, inside the enclosure (30), at least one partial obstacle (36, 38) that extends from a wall of the enclosure (30) in a direction transverse to the acoustic propagation axis (L), the at least one obstacle (36, 38) having at least one edge (41a, 41b) rigidly attached to a wall of the enclosure (30) and a free edge (40) that delimits an off-centre internal passage (42) for increasing the length of the path travelled by the acoustic waves through the acoustic cell (28). The at least one partial obstacle (36, 38) further comprises at least one drainage hole (37) adjacent to an edge that is rigidly attached to a wall of the enclosure (30).
G10K 11/172 - Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using resonance effects
B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
F02C 7/045 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
The invention relates to a propeller (1) of an aircraft turbine engine, comprising a cone (2) and a plurality of blades (3), the propeller (1) comprising a plurality of electrical de-icing members (4) rigidly connected to a wall (30) of the blades (3), and a control system (6) electrically connected to the electrical de-icing members (4) and comprising at least one electrical switch (7A) having a variable switching duty cycle which is configured, using an input electrical power (Pe), to distribute an output electrical power (Ps) to the electrical de-icing members (4) and to emit a dissipated electrical power (Pd) in the form of heat, at least one electrical switch (7A) of the control system (6) being mounted on an inner face (21) of a wall (20) of the cone (2) so as to transfer the dissipated electrical power (Pd) by thermal conduction into the wall (20) of the cone (2).
A gripping head can be used for applying a patch to a surface to be draped. The gripping head for gripping a patch and applying the patch to a surface to be draped includes a suction chamber delimiting a suction sector and connected to a suction intake and a gripper connected to said suction chamber and comprising a piece of elastically deformable material configured to grip a patch under a gripping effect created in said suction chamber. The gripper includes selectively activatable gripping zones and the gripping head includes means for selectively activating the gripping zones.
Tooling for manufacturing an air deflection cascade for a thrust reverser system of an aircraft nacelle includes a plurality of spars, each spar being connected to at least one adjacent spar by a plurality of deflection vanes. The tooling includes at least one molding bar and at least one molding column of a row of vanes, comprising two opposing lateral faces extending along the longitudinal direction of the tooling, and comprising molding cavities. The tooling includes a fixed structure on which the molding bar and the molding column are mounted. The fixed structure enabling a translational movement, along a transverse direction of the tooling, of the molding bar. The tooling includes a compression device to provide the compression of elements made of a composite material arranged in the tooling and intended to form at least one part of the cascade to be manufactured.
B29C 43/02 - Compression moulding, i.e. applying external pressure to flow the moulding materialApparatus therefor of articles of definite length, i.e. discrete articles
B29C 43/36 - Moulds for making articles of definite length, i.e. discrete articles
B29C 70/46 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
The invention relates to a surface heat exchanger (20), in particular for an aircraft nacelle, comprising a first metal sheet (2) and a second metal sheet (3) that are joined together, and a plurality of distribution channels (4) for a fluid which are arranged between the first metal sheet (2) and the second metal sheet (3), the exchanger further comprising fluid inlet (5) and outlet (6) interfaces. The exchanger further comprises fluid distribution means which define, for each distribution channel (4), a fluid flow section, each of the distribution channels (4) being connected to the inlet (5) and outlet (6) interfaces by such a flow section, the distribution channels (4) being distributed over the entire periphery of the inlet interface (5) and/or of the outlet interface (6).
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
76.
THRUST REVERSAL SYSTEM FOR AN AIRCRAFT, AND ASSOCIATED INSTALLATION AND AIRCRAFT
This system (101) comprises a local control module (120) comprising an analogue input port (121) and an analogue wired connection, referred to as control connection (122), between a global control module (104) and the analogue input (121). The local control module (120) is designed to receive, via the control connection (122) and the analogue input (121), movement commands from the global control module (104) in order to control an electric actuator (114) so as to move a cover (112). The local control module (120) furthermore comprises a transmission digital output (152) that is separate from the analogue input (121), the local control module (120) being designed to transmit operating information from the thrust reversal system (101) via the digital output (120).
A method for manufacturing an acoustic panel including a first skin, a second skin and an intermediate structure enclosed between these skins and forming oblique cavities with respect to the latter. The method includes an intermediate polymerization step for fastening the intermediate structure to the first skin in order to increase the compressive strength thereof and in particular to support an automated operation of draping the second skin.
B32B 3/30 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids characterised by a layer formed with recesses or projections, e.g. grooved, ribbed
B29C 35/02 - Heating or curing, e.g. crosslinking or vulcanising
B29C 65/70 - Joining of preformed partsApparatus therefor by moulding
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B29K 63/00 - Use of epoxy resins as moulding material
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
B32B 3/26 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 7/12 - Interconnection of layers using interposed adhesives or interposed materials with bonding properties
B32B 15/14 - Layered products essentially comprising metal next to a fibrous or filamentary layer
B32B 15/20 - Layered products essentially comprising metal comprising aluminium or copper
An acoustic panel for an aircraft turbomachine has a sandwich structure. The sandwich structure includes a cell structure with a plurality of acoustic cells, a perforated acoustic structure, and a porous acoustic structure attached to the perforated acoustic structure. The perforated acoustic structure is arranged between the cell structure and the porous acoustic structure. The porous acoustic structure is multi-layered and has a first woven textile layer and a second woven textile layer connected to the first layer. The second layer is arranged between the first layer and the perforated acoustic structure.
The invention relates to an assembly structure (10) for manufacturing a composite part. The structure comprises:—a skin preform (Pp) and a generally omega-shaped stiffener preform (PT) each having first and second opposing surfaces, the stiffener preform extending along and opposite the first surface of the skin preform. longitudinally and transversely in the form of a stiffener preform cross-section,—a rigid skin tooling (Op) disposed opposite the entire second surface (Sp2) of the skin preform,—a local rigid stiffener tooling (Or1, Or2) extending transversely around the stiffener preform cross-section with a transverse dimension smaller than the transverse dimension of the first surface of the skin preform.
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
06 - Common metals and ores; objects made of metal
07 - Machines and machine tools
40 - Treatment of materials; recycling, air and water treatment,
42 - Scientific, technological and industrial services, research and design
Goods & Services
(1) Constructions en acier; réservoirs métalliques [structures]; métaux communs et leurs alliages, y compris acier inoxydable; métal antifriction; métal extrudé; métal blanc; tôles métalliques; tôles d'acier; feuilles de métal; pièces métalliques forgées; pièces métalliques embouties; acier; acier inoxydable; acier brut ou mi-ouvré; alliages de métaux communs; aluminium; alliages d'acier.
(2) Machines pour l'usinage des métaux. (1) Traitement des métaux; traitement de métaux à savoir estampage, formage, profilage, embossage, hydroformage; traitement des métaux par hydroformage à base d'explosifs; fourniture de services de formage de métaux par hydroformage à base d'explosif; services de façonnage et de transformation de métaux utilisant la technique de l'hydroformage à base d'explosif pour la production de pièces métalliques conformes à des spécifications particulières; personnalisation et adaptation de pièces métalliques via hydroformage à base d'explosif pour des tiers; traitement thermique des métaux; services d'estampage; emboutissage de métaux; façonnage de composants métalliques; assemblage de matériaux sur commande pour des tiers; services de soudage; usinage de pièces pour des tiers.
(2) Recherche scientifique, technique et industrielle relative aux matériaux et métaux; recherche et développement de nouveaux produits relatifs aux matériaux et métaux; services de conseils techniques, ingénierie et expertise (travaux d'ingénieurs) dans le domaine des matériaux et métaux; essais de machines et de matériaux; services de tests et d'analyse de matériaux; conception de démonstrateurs technologiques; services d'ingénierie en matière de systèmes de formage de métaux; étude de faisabilité de formage de métaux.
06 - Common metals and ores; objects made of metal
07 - Machines and machine tools
40 - Treatment of materials; recycling, air and water treatment,
42 - Scientific, technological and industrial services, research and design
Goods & Services
Steel buildings; metal tanks [structures]; common metals and their alloys, including stainless steel; anti-friction metal; extruded metal; white metal; sheet metal; steel sheets; sheets of metal; forged metal parts; pressed metal parts; steel; stainless steel; unwrought or semi-wrought steel; alloys of common metals; aluminum; steel alloys. Machines for metal machining. Treatment of metals; metal treating, namely stamping, forming, profiling, embossing, hydroforming; treatment of metals by hydroforming based on explosives; providing metal forming services by explosive-based hydroforming; metal processing and shaping using the technique of hydroforming based on explosives for production of metal parts complying with particular specifications; customization and adaptation of metal parts via hydroforming based on explosives for third parties; heat treatment of metals; stamping services; deep-drawing of metals; shaping of metal components; custom assembly of materials for third parties; welding services; machining of parts for third parties. Scientific, technical and industrial research relating to materials and metals; research and development of new products relating to materials and metals; technical advisory services, engineering and expertise (engineering work) in the field of materials and metals; machine and material testing; material testing and analysis services; design of technological demonstrators; engineering services relating to metal forming systems; metal forming feasibility study.
82.
Reverser with movable cascades for an aircraft propulsion assembly, comprising a system for limiting the buckling of an actuator of the reverser
A thrust reverser for an aircraft propulsion unit, including a movable system with cascade vanes and an actuator allowing moving a movable system between an advanced direct thrust position and a backward thrust reversal position, the system also including an inter-cascade structure for limiting buckling of the actuator, forming a channel crossed by the actuator and delimited by a cylindrical internal surface extending along a first closed directrix curve, the fixed portion of the actuator including an end equipped with an external ring for limiting buckling of the actuator, the ring having a cylindrical external surface extending along a second closed directrix curve, the first and second closed directrix curves preferably having the same shapes and being concentric while being spaced apart from one another with the same spacing.
F02K 1/76 - Control or regulation of thrust reversers
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
83.
ACOUSTIC PANEL FOR AN AIRCRAFT PROPULSION ASSEMBLY AND METHOD FOR PRODUCING SAME
The invention relates to a method for producing an acoustic panel (24') for an aircraft propulsion assembly (10), the panel comprising first and second skins (26, 30) and a cellular layer (28) positioned between the first and second skins (26, 30), the first skin (26) being acoustically permeable and the cellular layer (28) comprising cells (32) that are in fluid communication with perforations (34) in the first skin (26), each of these cells (32) comprising a central well (38) surrounded by peripheral walls (36) of the cell (32), the method comprising a step of producing the cellular layer (28) and a step of assembling the panel (24'), characterised in that the step of producing the cellular layer (28) comprises preparing a sheet (50) and folding this sheet (50) so as to form the cell (32) and its well (38), or so as to form the cells (32) and their wells (38).
A propulsion unit includes a fairing delimiting a flow conduit for a secondary flow. This fairing comprises includes panels, at least one of which is articulated on a mast via connecting members such as clevises.
B64D 29/06 - Attaching of nacelles, fairings, or cowlings
F02K 1/32 - Plants characterised by the form or arrangement of the jet pipe or nozzleJet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for reversing thrust
09 - Scientific and electric apparatus and instruments
12 - Land, air and water vehicles; parts of land vehicles
40 - Treatment of materials; recycling, air and water treatment,
42 - Scientific, technological and industrial services, research and design
Goods & Services
Motors/engines, thrusters, thrust reversers for locomotion
apparatus (except for land vehicles), including aeronautical
vehicles; parts and spare parts for motors/engines and
thrusters for locomotion apparatus (except for land
vehicles), including aeronautical vehicles; parts and spare
parts for thrust reversers for locomotion apparatus (except
for land vehicles), including aeronautical vehicles. Electric and electronic apparatus and instruments, namely,
for measuring, controlling and electric checking of the
opening of motor thrust inverters, potential calculators,
full authority digital engine control (FADEC) calculators,
temperature, pressure, vibration analyses, flight control
calculators; electric, electronic and magnetic sensors for
pressure, speed, displacement, temperature, position,
vibration, electronic cards for processing parameters;
electric connectors; electronic systems and equipment,
whether on board or not, for acquiring and processing data;
electrical and electronic devices and equipment for
maintenance and monitoring (on board aircraft or engines,
fixed on test benches or portable for ground interventions)
for reading and interpreting data from computers and
sensors. Apparatus for locomotion by air, aeronautical vehicles
including aircraft and airplanes; parts and spare parts for
aircraft cabins; nacelles for engines, jet engines and
thrusters for aeronautical vehicles; nacelles for
motors/engines for locomotion apparatus (except for land
vehicles), including aeronautical vehicles; parts and spare
parts of nacelles for motors/engines for locomotion
apparatus (except for land vehicles), including aeronautical
vehicles. Assembly of aeronautical vehicles including airplanes and
aircraft, for third parties; assembly of motors/engines, jet
engines, aeronautical thrust reversers, for third parties;
assembly of components of aeronautical vehicles including
motor/engine nacelles, jet engines, thrusters and thrust
reversers for third parties. Technical, scientific and industrial research in connection
with aeronautical vehicles; research and development of new
products in connection with aeronautical vehicles;
mechanical engineering research in the aeronautical field;
technical advice, research and assistance concerning the
design, certification and modification of aeronautical
vehicles and components thereof, including motor/engine
nacelles, jet engines, thrusters or thrust reversers for
aeronautical vehicles; engineering, professional consulting
and expert reports (services of engineers) in the field of
aeronautics; testing of materials; technical advice and
assistance concerning the manufacture of aeronautical
vehicles and component parts thereof, including motor/engine
nacelles, jet engines, thrusters or thrust reversers,
aeronautical vehicles.
A locking system for an aircraft nacelle is provided. The locking system includes a first portion configured to be mounted on a first part of an aircraft nacelle, and a second portion configured to be mounted on a second part of the aircraft nacelle. The locking system can be configured such that, when it is in the closed position, the first portion and the second portion are held together. The locking system further includes at least one buffer part and a load sensor joined together and configured to compress the load sensor between the buffer part and another part of the locking system when the locking system is in the closed position.
B64D 29/06 - Attaching of nacelles, fairings, or cowlings
E05C 5/00 - Fastening devices with bolts moving otherwise than only rectilinearly and only pivotally or rotatively
E05C 5/02 - Fastening devices with bolts moving otherwise than only rectilinearly and only pivotally or rotatively both moving axially and turning about their axes to secure the wing
87.
THRUST REVERSER RING FOR AN AIRCRAFT NACELLE THRUST REVERSER AND AIRCRAFT NACELLE
The invention relates to a thrust reverser ring of an aircraft jet engine extending along a longitudinal axis. The ring comprises thrust reverser modules each extending in a longitudinal direction (D) parallel to the longitudinal axis, the thrust reverser modules being distributed circumferentially about the axis so as to form a ring. One thrust reverser module (10) is arranged between two adjacent thrust reverser modules and is mechanically independent of the latter, the thrust reverser module (10) comprising: - a spar (12) which extends in the longitudinal direction (D) and includes two opposite ends (12c, 12d) spaced apart from each other in this direction, each end being configured to attach the spar to an aircraft nacelle; and - a plurality of transverse blade members (14a, 14b) which are distributed along the spar, extending away from the spar.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
88.
THRUST REVERSER MODULE OF A THRUST REVERSER RING FOR AN AIRCRAFT NACELLE THRUST REVERSER
The invention relates to a thrust reverser module (30) of a thrust reverser ring for an aircraft nacelle thrust reverser, characterised in that the thrust reverser module (30) comprises: - a first spar (42) which extends in a longitudinal direction (D) and carries blade elements (42a1, 42a2, 42a3) each extending transversely relative to the longitudinal direction (D), the transverse blade elements (42a1, 42a2, 42a3) being distributed along the first spar (42); and - a second spar (44) which extends in parallel with the first spar (42) and comprises first and second large opposite faces (44a, 44b), at least one portion of the transverse blade elements (42a1, 42a2, 42a3) of the first spar (42) being connected to the first large face (44a) of the second spar (44) that is arranged opposite, the second large face (44b) of the second spar (44) carrying transverse blade elements (44b1, 44b2, 44b3) which each extend transversely relative to the longitudinal direction of the second spar (44), away from a zone (Z1, Z2, Z3) of the second spar (44) referred to as connection zone of the blade element in question, and in a direction opposite the first large face (44a) of the second spar (44), the transverse blade elements (42a1, 42a2, 42a3) of the at least one portion of the transverse blade elements of the first spar (42) each being connected to the first large face (44a) of the second spar (44), between two successive connection zones (Z1, Z2, Z3) of two successive transverse blade elements (44b1, 44b2, 44b3) carried by the second large face (44b) of the second spar (44), such that the transverse blade elements (42a1, 42a2, 42a3) of the at least one portion of the transverse blade elements of the first spar (42) connected to the second spar and the transverse blade elements (44 b1, 44b2, 44b3) carried by the second large face (44b) of the second spar (44) form a staggered arrangement relative to the second spar.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
89.
Air inlet for an aircraft propulsion unit comprising a member for moving a movable upstream portion and method for using such an air inlet
An air inlet for an aircraft propulsion unit having a movable upstream portion, a stationary downstream portion and at least one member for longitudinally translating the movable upstream portion between a retracted position in which the movable upstream portion is adjacent to the stationary downstream portion, and an extended position in which the movable upstream portion is separated from the stationary downstream portion, the moving member having at least one guiding bar connected to the movable upstream portion and a drive bar having a plurality of teeth, the stationary downstream portion having, for each moving member, a gear wheel configured to co-operate with the teeth in order to form a rack-and-pinion connection and at least one guiding member of the guiding bar.
A cascade (22) of vanes for a cascade thrust reverser (19) for an aircraft propulsion assembly nacelle comprises: a first bladed stage (22A) and a second bladed stage (22B), which are superimposed, each comprising rows of vanes (50A, 50B) and of spars (52A, 52B) which cross over one another so as to form a cellular structure (53A, 53B) for the passage of the air flow; and front (40) and rear (42) end flanges each rigidly connected to all or some of the spars of at least one of the bladed stages. The cellular structures are connected to each other, independently of the front and rear end flanges, by connecting means (66) configured to block relative displacements between the cellular structures. This results in good thrust reversal performance, compatibility with inexpensive manufacturing processes, and a reduction in vibration instability and aerodynamic disturbances.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
91.
THRUST REVERSER FOR AN AIRCRAFT TURBINE ENGINE COMPRISING MEANS FOR DEPLOYING AND RETRACTING, BY MEANS OF A CABLE, A DIAPHRAGM FOR CLOSING THE SECONDARY DUCT
The invention relates to a thrust reverser (30) comprising a movable reverser cowl (33) equipped with a radially inner wall (52) involved in externally defining a secondary duct (21B), the reverser also comprising a diaphragm (58) for closing the secondary duct, as well as means (62) for deploying and retracting the diaphragm. According to the invention, the means (62) comprise: - a cable (64) for driving the diaphragm; and - a member (66) for guiding the first cable, which is mounted on the wall (18). In addition, in the advanced forward thrust position: - a first portion of the cable (64a), which emerges from the guiding member (66), is connected to a first diaphragm end (58a); and - a second portion of the cable (64b), which emerges from the guiding member (66), is connected to the movable reverser cowl (33).
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
F02K 1/76 - Control or regulation of thrust reversers
An acoustic assembly including a multicellular acoustic panel having at least one through cavity along a direction X, wherein the acoustic assembly further includes at least one sealing element including a body enclosing one or more acoustic cells, the body being able to be inserted into the cavity and extending along the direction X between a first face and a second face, the sealing element further including a seal on the second face of the body able to ensure the sealing with the acoustic panel.
This device (1) for counting a number of mechanical cycles produced by a cyclically moving part comprises a module (4) for storing the number of mechanical cycles produced by the mobile part, a module (3) for detecting a mechanical cycle produced by the mobile part capable of incrementing the number stored in the storage module (4) and a module for transmitting, upon request, (5) the stored number able to recover the number stored in the storage module (4), the detection module (3) comprising a piezoelectric generator (6) configured to determine an embodiment of a mechanical cycle by the mobile part and the on-demand transmission module (5) comprising an RFID tag (12) provided with an antenna (13).
G01H 11/08 - Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by detecting changes in electric or magnetic properties by electric means using piezoelectric devices
G07C 3/04 - Registering or indicating working or idle time only using counting means or digital clocks
B60C 23/04 - Signalling devices actuated by tyre pressure mounted on the wheel or tyre
94.
DEVICE FOR DETECTING THE POSITION OF A MOBILE PART, AND ASSOCIATED METHOD AND AIRCRAFT
This device (2) for detecting the position of a mobile part (1) able to move between a first extreme position, a second extreme position and at least one intermediate position, comprises a fixed antenna (3) and a plurality of radio-frequency identification tags (4, 4a, 4b, 4c) arranged along the path of the mobile part (1) between said extreme and intermediate positions, the device (2) further comprising a mechanical contactor (5) configured to establish an electrical connection between the antenna (3) and a unique combination of at least one radio-frequency identification tag (4, 4a, 4b, 4c) for each position of the mobile part (1).
G01D 5/252 - Selecting one or more conductors or channels from a plurality of conductors or channels, e.g. by closing contacts a combination of conductors or channels
H01Q 1/22 - SupportsMounting means by structural association with other equipment or articles
G01D 21/00 - Measuring or testing not otherwise provided for
G06K 19/07 - Record carriers with conductive marks, printed circuits or semiconductor circuit elements, e.g. credit or identity cards with integrated circuit chips
G06K 19/077 - Constructional details, e.g. mounting of circuits in the carrier
95.
Thrust reverser with cascades of mobile vanes, comprising a rear structure supporting the cascades of vanes and incorporating an acoustic function
A thrust reverser for an aircraft propulsion unit, including a fixed structure, at least one cowl and a plurality of cascades of deflection vanes, the cowl and the cascades of vanes forming a system capable of translational movement relative to the fixed structure along a longitudinal central axis, the mobile system further including at least one rear cascade-support structure to which a rear end of the cascades of vanes is fixed, the rear structure extending in a circumferential direction of the reverser. The rear structure incorporates an acoustic-absorption device including an array of cells and a skin covering the cells, the skin having a first surface arranged facing the cells, and a second surface bounding part of a secondary flow path.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
The invention relates to a thrust reverser assembly for a turbojet engine, comprising a stationary structure having a main axis; a shroud, movable and capable of translational movement along the main axis between an attached position in which the shroud is attached to the stationary structure, and a spaced position in which the shroud is spaced from the stationary structure; at least one latch capable of holding the stationary structure and the shroud in the attached position; at least one actuator mounted between the stationary structure and the shroud and configured to move the shroud along the main axis between the attached position and the spaced position; and a seal configured to provide a seal between the stationary structure and the shroud in the attached position, wherein the seal has a tapered cross section.
F02K 1/76 - Control or regulation of thrust reversers
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
97.
ACOUSTICALLY-TREATED AIR EJECTION NOZZLE FOR A NACELLE
An air ejection nozzle for a nacelle includes an outer aerodynamic line and an inner aerodynamic line meeting at a trailing edge. The air ejection nozzle includes at discrete positions at least one area of larger thickness that is compensated by at least one fairing to connect the aerodynamic lines to form the trailing edge. The fairing includes an outer wall and an inner wall delimiting a cavity therebetween. The inner wall provides for the continuity of the inner aerodynamic line, and the outer wall is solid and the inner wall is pierced so that the at least one fairing forms an acoustic attenuation structure.
F02K 1/34 - Plants characterised by the form or arrangement of the jet pipe or nozzleJet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for attenuating noise
B64D 29/00 - Power-plant nacelles, fairings or cowlings
A method for controlling the application of a patch can include the following steps:
positioning a patch on a surface to be covered by means of a gripper and with or without partial overlapping with adjacent patches;
acquiring by means of an optical control means at least one image of the positioned patch;
detecting defects in the positioning of the patch by identifying differences in the thickness of the patch on the surface to be covered based on the at least one image of the positioned patch; and
mapping the defects in the positioning of the patch.
The invention relates to a jet deflection module (26) for a thrust reverser (10) of an aircraft turbine engine, this module (26) extending in a surface (P) and including: - longitudinal members (32) which are spaced apart from one another and parallel to one another; - at least one deflection element which extends between the longitudinal members (32) and which is connected to these longitudinal members (32); and - two attachment profiles, front (36) and rear (38), respectively, which are connected to the longitudinal members (32), these two profiles (36, 38) forming, with two of these longitudinal members (32), a peripheral contour of the module, characterised in that a first of the attachment profiles (36, 38) comprises a plurality of hooks (70) at a distance from one another, each of these hooks (70) comprising at least one opening (72) oriented perpendicularly to the surface (P) and additionally a bearing surface (74) parallel to this surface (P).
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
100.
JET DEFLECTION MODULE FOR A THRUST REVERSER OF AN AIRCRAFT TURBINE ENGINE
The invention relates to a jet deflection module (26) for a thrust reverser (10) of an aircraft turbine engine, this module (26) extending in a surface (P) and comprising: - longitudinal members (32) which are spaced apart from one another and parallel to one another; - at least one deflection member (34) which extends between the longitudinal members (32) and which is connected to these longitudinal members (32); - two, respectively front (36) and rear (38), attachment profiles which are connected to the longitudinal members (32) and which form, together with two of these longitudinal members (32), a peripheral contour of the module (26), a first of the attachment profiles (36, 38) comprising at least two clevis joints (90) which are parallel to one another and to the longitudinal members (32) and which each comprise a hole (92), the holes (92) of the clevis joints (90) being aligned and defining a pivoting axis (A) of the module (26), characterised in that the clevis joints (90) extend in the continuation of the longitudinal members (32).
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
