The invention relates to a device (10) for de-icing an air intake lip (12) of an aircraft turbojet engine nacelle (14), the device (10) comprising a de-icing circuit in which a heat transfer fluid (22) circulates, said heat transfer fluid working in a two-phase form, the circuit comprising at least one device (26) for circulating the heat transfer fluid (22) in the de-icing circuit, a system (28) for heating the heat transfer fluid (22) and which is intended to change the phase of said fluid to a vapour phase, and an inlet conduit (30), for the heat transfer fluid (22), which opens into the lip (12) through the rear wall (18) in order to inject the vapour phase fluid (22) into the lip (12), the fluid changing phase when it condenses on the front wall (16) of the lip (12) to de-ice the lip (12).
B64D 15/02 - De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
F02C 6/18 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
A door-type thrust reverser device for a turbojet engine nacelle is provided that includes a fixed structure, a mobile structure mobile with respect to said fixed structure, and at least one door mounted with the ability to pivot via pivots between a retracted position corresponding to the nacelle operating in direct-jet mode, and a deployed position corresponding to the nacelle operating in reverser-jet mode. The thrust reverser device includes a device for bleeding off some of a secondary or bypass airflow, which device is able to bleed off part of the secondary airflow from a duct through which the secondary airflow circulates and for conveying said bled-off airflow toward at least one pivot of the door, so as to cool areas on and/or around the door pivots.
The disclosure relates to a shape-woven preform which has an omega-shaped cross-section including a core and a sole. At least one part of the core and at least one part of the sole have weft yarns in common with one another.
D03D 25/00 - Woven fabrics not otherwise provided for
D03D 1/00 - Woven fabrics designed to make specified articles
D03D 11/02 - Fabrics formed with pockets, tubes, loops, folds, tucks or flaps
D03D 13/00 - Woven fabrics characterised by the special disposition of the warp or weft threads, e.g. with curved weft threads, with discontinuous warp threads, with diagonal warp or weft
The present disclosure relates to a thrust reverser for a turbojet engine nacelle, including cowls that move backwards to open the thrust reverser. Each cowl includes a primary axial guide rail that receives most of the loads of the cowl, and secondary rails guiding an outer portion of each cowl. The thrust reverser includes a rear end stop for each cowl is arranged on the primary axial guide rails.
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
B64D 29/06 - Attaching of nacelles, fairings, or cowlings
E05B 63/18 - Locks with special structural characteristics with arrangements independent of the locking mechanism for retaining the bolt in the retracted position
The present disclosure relates to a thrust reverser device for a turbo jet engine nacelle including a fixed thrust reverser support structure having a longitudinal support half beam able to support a thrust reverser half-cowl, and the thrust reverser half-cowl mounted such that it can slide on the fixed structure in a direction substantially parallel to a longitudinal axis of the device via a guidance assembly, between a direct-jet position and a reverse-thrust position. In particular, the fixed structure includes a structure for offsetting the guidance assembly that guides the half-cowl circumferentially in a plane radial to the longitudinal axis between its various positions with respect to the half-beam on which the half-cowl is mounted.
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
B64D 27/18 - Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings
6.
Device for de-icing the inlet of a nacelle of an aircraft engine, method for producing such a de-icing device, and aircraft engine nacelle provided with such a de-icing device
A de-icing device is provided that includes a piccolo tube integrated with a front bulkhead for limiting an inner volume of a perforated front lip. The piccolo tube is in contact with a noise reduction cellular structure provided with perforations and hot air circulation channels delivered by the piccolo tube, the de-icing hot air being diffused through the perforations and channels of the cellular structure, on the perforations facing the front lip.
The present disclosure relates to a cascade thrust reverser providing that when a sliding cowl and a flap are in a direct jet position, a hook is held in engagement with another hook and the flap is immobilized inside of a housing of the sliding cowl by a stem of a telescopic connecting rod subjected to pre-stress generated by a compressed spring located in the body of the connecting rod. When the sliding cowl starts to slide from the direct jet position toward the reverse jet position, the hooks disengage each other and the stem engages with an extension in the body of the connecting rod, so that the flap is rotated from the direct jet position toward the reverse jet position due to the tensile force exerted by the stem.
F02K 1/62 - Reversing jet main flow by blocking the rearward discharge by means of flaps
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 unducted fan for an aircraft turbine engine, including a propeller having a hub and an annular array of blades extending substantially radially outwards from the hub, is provided. The hub includes an annular array of cowls, each of which is mounted between the radially inner ends of the blades and suitable for being fixed to an upstream collar and to a downstream collar of the hub. At least one cowl includes, at a circumferential end, a joint edge which is contiguous with a complementary joint edge of an adjacent cowl. The at least one cowl and at least one of the upstream and downstream collars are configured so that the cowl can be mounted and dismounted by a movement including a pivoting about an initial pivot axis circumferentially separated from the at least one joint edge.
A method for assessing damage to a composite material covered with a polyurethane-type paint is provided. Two separate criteria are measured on a spectrogram obtained by infrared spectrometry, thereby characterizing thermal ageing of the paint, each separate criteria being a measurement on a curve of a spectrum of the spectrogram of a height of a particular peak, thereby giving two independent assessments of the thermal ageing. Then, the two separate criteria are combined together in order to obtain a result of a level of the damage.
G01N 21/3563 - Investigating relative effect of material at wavelengths characteristic of specific elements or molecules, e.g. atomic absorption spectrometry using infrared light for analysing solidsPreparation of samples therefor
The present disclosure relates to a seal for an aircraft turbojet engine nacelle thrust reverser, the seal having body having a cross section with respect to a longitudinal axis of the seal that is substantially circular, and a base which is intended to be mounted in a seal support. The seal is notable in that the base of said seal has apertures spaced from each other.
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
An afterbody for a turbojet engine having a central axis, provided with a nozzle comprising two doors facing each other between two lateral beams. The doors pivot around axes defining a pivot direction, between a retracted position, in which a middle portion of the downstream edge of the doors forms the edge of the outlet section of the nozzle combined with the downstream edges of the two lateral beams, and a deployed position, in which the middle portions of the downstream edges of the pivoting doors come together so as to block the channel between the two lateral beams in order to reverse the thrust of the turbojet engine gases. The edge of the outlet section of the nozzle further having a crown of noise-reducing chevrons alternating with indentations and the afterbody.
The invention relates to a method for the repair of a composite panel (10), said panel comprising at least one first composite skin (12) defined by a lower face (18), characterized in that it comprises a cutting step which consists of forming a hole (22) stepped like a staircase in at least the first skin (12), a fitting step which involves arranging a support face of a shaping tool against the lower face (18) of the first skin (12), a reconstitution step of the first skin (12) consisting of closing the hole (22) by means of a repair piece (38) and a fastening step which involves fastening the repair piece (38) on the first skin (12) by mechanical fastening means (42).
B29C 73/10 - Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass using preformed elements using patches sealing on the surface of the article
B29C 73/06 - Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass using preformed elements using plugs sealing in the hole
B29C 73/12 - Apparatus therefor, e.g. for applying
The invention relates to a method for characterising the thermal ageing of a part made of a composite material, especially a composite material with an organic matrix, the method comprising the steps of: taking (50) a sample of composite material from the part; subjecting (51) the sample to a thermogravimetric analysis in an oxidising atmosphere; determining (52), from the deconvolution of the thermogram obtained, the intensity of a given range peak, said intensity being characteristic of the thermal ageing; and determining (53) the thermal ageing of the composite material by comparing the intensity of the peak with a reference nomogram.
G01N 5/04 - Analysing materials by weighing, e.g. weighing small particles separated from a gas or liquid by removing a component, e.g. by evaporation, and weighing the remainder
G01M 99/00 - Subject matter not provided for in other groups of this subclass
14.
Integrated thrust reverser device and aircraft engine nacelle equipped therewith
The present disclosure provides a thrust reverser device that is integrated in an aircraft nacelle. Blocking flaps are stored inside a mobile cowl disposed in a downstream section of the nacelle, under deflection cascade assemblies during direct-jet operation of the nacelle. Various devices are provided for executing the passage from direct-jet operation to reverse-jet operation in two stages: the mobile cowl moves in translation towards the downstream end of the nacelle; and each flap is then deployed in the main air flow path.
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
F02K 1/62 - Reversing jet main flow by blocking the rearward discharge by means of flaps
F02K 1/70 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
F02K 1/09 - Varying effective area of jet pipe or nozzle by axially moving an external member, e.g. a shroud
F02K 3/06 - 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 with front fan
15.
Thrust reverser for a turbojet engine nacelle, comprising cascades partially integrated in the cowls
A thrust reverser for a turbojet engine nacelle includes movable cowls which move backward relative to a front frame under the action of an actuation system, thereby making flaps tilt, via a control mechanism, so as to substantially close the annular cold air flow path, and by opening cascades disposed around this flow path and which receive the cold air flow and return it forward. When the thrust reverser is closed, the cascades are partially integrated in the cowls, and the thrust reverser includes an actuation system which makes the cascades move backward along a stroke which is shorter than the stroke of the cowl.
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
F16H 25/22 - Screw mechanisms with balls, rollers, or similar members between the co-operating partsElements essential to the use of such members
A control device for a thrust reverser of a turbojet engine nacelle, which includes movable portions actuated by actuators, includes: a first blocking control acting on a motor-actuated system; and a second blocking control acting, mechanically, on the movable portions. The second blocking control may inhibit, when activated, a deployment of the movable portions. The control device further includes a device inhibiting disengagement of the first blocking control when a mechanical control is activated.
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
F02K 1/62 - Reversing jet main flow by blocking the rearward discharge by means of flaps
17.
Turbojet engine nacelle including a thrust reversing device with doors, including inner flanks on the sides of an opening
A turbojet engine nacelle includes a thrust reversing device having doors that swing to brake a direct gas flow, guiding it through counter-thrust openings, and the inside of each door has, at the front, a cavity receiving a spoiler turned towards the front when this door is open. The nacelle includes a fixed structure upstream from each door supporting a deflection edge that partially covers the cavity. In particular, the fixed structure supports, on each side, counter-thrust openings, a flank disposed in the continuation of the deflection edge and extending behind the cavity, which is incorporated into a leaf of the door.
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
F02K 1/70 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
F02K 3/06 - 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 with front fan
18.
Nacelle for an aircraft turbojet engine with an extended front lip
A nacelle for an aircraft turbojet engine includes: a substantially cylindrical internal envelope, a substantially cylindrical external envelope, a downstream partition wall and an upstream partition wall secured to the cylindrical internal envelope and a front lip disposed forward of the upstream partition wall. The cylindrical internal envelope includes an upstream portion including an acoustic shroud connected, by an attachment flange, to a downstream portion including a fan casing. In particular, the front lip is extended and disposed over the upstream partition wall by presenting a downstream edge between the upstream and downstream partition walls in order to be secured to a homologous edge of the cylindrical external envelope so as to arrange a maintenance access to the attachment flange.
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F02C 3/04 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
F02K 3/06 - 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 with front fan
The invention concerns a method for producing a honeycomb core panel (10) suitable for producing a sound absorbing panel of an aircraft nacelle, the panel comprising a honeycomb core (12) delimited by a first face (16) and an opposing second face (20), and a first skin (14) that covers the first face (16) of the honeycomb core (12), an insulating layer (24) that consists of at least one adhesive layer (26) strengthened by a reinforcement (28) with galvanic isolation, and that is interposed between the honeycomb core (12) and said first skin (14), said insulating layer (24) forming a prefabricated element designed to be deposited on the honeycomb core (12) in one step, characterised in that the method comprises at least a step of depositing the insulating layer (24) on the first face (16) of the honeycomb core (12), and a step of depositing the first skin (14) on the insulating layer (24).
The present disclosure provides a nozzle for an aircraft turboprop engine with an unducted fan, including: an inner wall, an outer wall radially spaced apart from the inner wall and concentric with the inner wall, a junction area of the inner and outer walls including an opening contained in a plane transverse to a longitudinal axis of the nozzle. In particular, the junction area of the inner and outer walls includes two connecting plates and a member to secure the two connecting plates together, or in another form, the junction area includes a pad secured to the inner wall, and a pad secured to the outer wall, facing the pad of the inner wall of the nozzle.
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F02K 1/28 - 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
F02K 3/072 - 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 with counter-rotating rotors
F02C 3/067 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
F02K 3/06 - 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 with front fan
A method for assembling a set including an inner wall, a shrouded outer wall and an intermediate element, each presenting substantially circular sections, the shrouded outer wall presenting a shape substantially complementary to a shape of outer and inner surfaces of the intermediate element, and whose inner surface covers the outer surface of the intermediate element. In particular, the method includes a step of placing a brazing sheet, whose melting temperature is lower than melting temperatures of other elements of the set, over an assembly surface in contact with another assembly surface, and a step of heating, by a furnace, a set including the outer or inner walls and the intermediate element between which is interposed a brazing sheet so as to fix the outer or inner wall by brazing on the intermediate element.
B23K 31/02 - Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by any single one of main groups relating to soldering or welding
The present disclosure provides an aircraft element including a leading edge section and a trailing edge section, and the leading edge section includes an anti-frost treatment device. This aircraft element is remarkable in that the trailing edge section includes a superhydrophobic surface.
The present disclosure relates to a front frame for an aircraft nacelle comprising a turbojet mounted on a suspension strut, said nacelle comprising a thrust reverser including an actuator designed to open a thrust reversal cowling. The front frame comprises a tubular torsion box, a first straight attachment edge intended to attach the box to a turbojet casing and a second straight attachment edge intended to attach the box to air flow diversion means. The front frame is arranged to transmit tensile and compressive loads between the turbojet casing and the air flow diversion means and torsion loads absorbed by the suspension strut. The front frame is characterized in that the tubular torsion box has a semi-elliptical or elliptical cross-section.
F02C 6/00 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use
B64D 29/06 - Attaching of nacelles, fairings, or cowlings
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
F01D 25/28 - Supporting or mounting arrangements, e.g. for turbine casing
F02K 1/70 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
The invention concerns an actuating device (1) for moving a mobile cover of a thrust reverser, comprising: an actuator (5) comprising a first element (10), such as a screw, and a second element (12), such as a nut, mounted mobile device relative to the first element (10) such that the rotation of the first element (10) results in a translational movement of the second element (12) relative to the first element (10), and a locking device (31) comprising a rotating part (34) linked in rotation with the first element (10), and a locking part (35) that is mobile relative to the rotating part (34) between a locked position in which the locking part (35) is engaged with the rotating part (34) to prevent the first element (10) from rotating and an unlocked position in which the locking part (35) is disengaged from the rotating part to allow the rotation of the first element (10), and an electromagnet (39) for moving the locking part (35) to the unlocked position.
The present disclosure provides an aircraft nacelle including: an outer aerodynamic wall having an upstream air intake lip; an inner aerodynamic wall, the air intake lip connecting the two outer and inner aerodynamic skins; a front wall arranged downstream of the air intake lip and connecting the two outer and inner aerodynamic skins; and a network for the circulation of a first fluid for cooling a second fluid. The network includes two air/oil-type heat exchangers, one air/air type heat exchanger, an air scoop to collect air from the outside of the nacelle, an orifice to collect cold air, and an outlet orifice to discharge air.
The present disclosure relates to a propulsion unit for an aircraft including a nacelle which surrounds a turbojet engine. The nacelle has an inner structure surrounding a downstream compartment of the turbojet engine, and the inner structure includes two annular half-portions. The propulsion unit also includes a rail/guide unit and to move the annular half-portions between a working position and a maintenance position. In particular, the rail/guide unit radially moves away the annular half-portions relative to a longitudinal axis of the nacelle, during a translation movement of the annular half-portions. The nacelle is provided with a connecting rod which is connected to the annular half-portions and to the turbojet engine and so that the connecting rod contributes to rotate the annular half-portions about the rail.
F02K 3/06 - 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 with front fan
B64D 29/00 - Power-plant nacelles, fairings or cowlings
The invention relates to an assembly for handling an aircraft turbojet, comprising: a chassis (2); four actuators (301, 302, 303, 304) secured to the chassis and arranged two by two, facing each other, either side of a longitudinal axis of the chassis (2); and two connecting arms (4, 5) extending in a transverse direction of the chassis, each one connecting two of the actuators (301, 302, 303, 304); each connecting arm (4, 5) comprising two devices (401, 501) for holding the turbojet.
B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided forHandling, transporting, testing or inspecting aircraft components, not otherwise provided for
F01D 25/28 - Supporting or mounting arrangements, e.g. for turbine casing
28.
Fiber structure for an axisymmetric component made of composite material with a varying diameter, and component comprising same
A single-piece woven fiber structure for fabricating an axisymmetric part of varying diameter made out of composite material, the fiber structure having a portion of frustoconical shape with a large diameter and a small diameter, the ratio between the large diameter and the small diameter being not less than 2. The fiber structure is formed by winding layers of warp and weft yarns that are woven on a mandrel having a profile that is defined as a function of the profile of the part to be fabricated with warp yarn take-up. For each layer of yarns, the weft yarns are angularly distributed on a single diameter in a zone of the large diameter of the portion of frustoconical shape and on at least two different diameters in a zone of the small diameter of the portion of frustoconical shape in order to form at least two superposed plies of weft yarns.
A device for drilling an acoustic component including a drilling head, and the drilling head has a support unit including at least two autonomous drilling cassettes. Each cassette includes at least one drill bit, a stationary frame with respect to the support unit, and a bit support moveable along the main axis (Δ) of the cassette between a retracted position and a deployed position. In particular, each bit support is equipped with a device for sensing the skin of the acoustic component to be drilled allowing to automatically control the drilling depth of the bits of each cassette.
B23B 39/16 - Drilling machines with a plurality of working-spindlesDrilling automatons
B23B 49/00 - Measuring or gauging equipment on boring machines for positioning or guiding the drillDevices for indicating failure of drills during boringCentring devices for holes to be bored
B32B 37/12 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
G10K 11/172 - Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using resonance effects
30.
Locking/unlocking device for a one-piece cowl of a thrust reverser of a turbojet engine nacelle
An assembly for a turbojet engine includes a pylon, a nacelle supported by the pylon, and a locking device interposed between the pylon and a cowl of the nacelle. The cowl slides between operating and maintenance positions. The locking device is movable between active and inhibited positions, and the device allows an operation mode in the active position and a maintenance mode in the inhibited position. In particular, the locking device comprises a rocker to maintain the cowl to the pylon, and the rocker includes an inhibiting lever and an activation lever. The inhibiting and activation levers are mounted on a switching shaft of the locking device. The inhibiting lever is set in rotation through an actuator, providing direct access from a bypass flow duct in the active position while the activation lever is set in rotation from the bypass duct in the inhibited position.
The present invention relates to a door-type thrust reverser device (21) for a turbojet engine nacelle, comprising: - a fixed structure (31), and - a mobile structure (33) mobile with respect to said fixed structure, comprising at least one door (23) mounted with the ability to pivot via pivots (39) between a retracted position corresponding to the nacelle operating in direct-jet mode, and a deployed position corresponding to the nacelle operating in reverse-jet mode. The thrust reverser device according to the invention is notable in that it comprises a device (41) for bleeding off some of a secondary or bypass airflow which device is able to bleed off part of the secondary airflow from a duct through which the secondary airflow circulates and for conveying said bled-off airflow toward at least one pivot (39) of the door, so as to cool the areas (29) around the door (23) pivots (39).
The invention relates to a thrust reverser of a turbofan pod, comprising movable cowlings (4) that retract relative to stationary front structure (2) to reveal stationary or movable thrust reverser cascades, as well as a secondary variable nozzle section (8) connected to the movable cowlings by guiding means enabling movement controlled by actuators (10) engaged with the front structure to apply an axial thrust. The invention is characterized in that the actuators (10) are directly connected to the secondary nozzle (8), and in that the thrust reverser comprises latches (14) connected to the movable cowlings (4), comprising two positions providing, alternately, latching onto the front structure (2) or latching onto the control (10) of the secondary nozzle (8).
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
The invention relates to a structural assembly (1) of an aircraft turbojet engine nacelle and a thermal protection mat (2) attached to the structure (1), the mat being attached to said structure (1) via at least one attachment device, the attachment device comprising an attachment base (11) rigidly connected to the structure (1), said attachment base (11) being rigidly connected to one end of a link (15), said link (15) passing through the mat (2) via a passage (2a, 2b, 2c) provided in the mat (2), and being rigidly connected at the other end of same to a retaining button (16), the assembly being characterised in that the attachment device comprises a removable spacer (14) inserted at least partially into a recess (2b) of the thermal protection mat (2), the spacer being disposed between the thermal protection mat (2) and the retaining button (16) and having a through-hole (14a) through which the link (15) can pass, the spacer being held in position by the retaining button (16).
Bypass turbojet engine nacelle thrust reverser comprising mobile cowls (4) which retract with respect to a fixed forward structure (2) in order to uncover thrust reversal cascades or vanes, and a variable secondary nozzle (6) connected to the mobile cowls by guide means allowing axial sliding of the system which controls the movement of this variable secondary nozzle, characterized in that it comprises actuators (8) bearing against the forward structure (2) to control means (20) of reversing the direction of travel, which are connected to the mobile cowls (4), which retract the variable secondary nozzle (6) when these actuators deliver a forward travel, and blocking devices (30) which link the second nozzle to the mobile cowls when this nozzle is deployed.
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
F02K 1/62 - Reversing jet main flow by blocking the rearward discharge by means of flaps
35.
SYSTEM FOR LOCKING A THRUST REVERSER WITH FLAPS, COMPRISING LOCKS FOR AN INTERMEDIATE OPENING POSITION
The invention relates to a system for locking the position of the flaps of a thrust reverser of a turbojet nacelle, said flaps being controlled by actuators, each one swinging about a transverse pivot in order to partially close off the air stream so as to guide it forwards, characterised in that it comprises locks (36) for locking the flaps in an intermediate opening position, between the closed position and the entirely opened-up position.
The invention relates to a thrust reversal device (12) for an aircraft turbojet engine pod including at least one movable cover (22) and a thrust reversal flap (26) that extends from a head (28) to a leg (30). Said device is characterized in that a front portion of the movable cover (22) forms a spoiler (40). The spoiler (40) and the head (28) of the thrust reversal flap (26) radially define therebetween an exhaust passage (42) suitable for allowing a flow of exhaust air (44) when the flap (26) is in the thrust reversal position thereof. Said device is also characterized in that the movable cover (22) comprises a deflector (46) that is arranged downstream from the exhaust passage (42) and designed to guide the exhaust air flow (44) along the rear surface (34) of the flap (26) forming the suction side.
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 acoustic sandwich panel comprising a plurality of alveolar units (2) joined by means of an intumescent adhesive (3) arranged between the edges of the alveolar units (2) to be joined, thereby forming at least one connection area (4), said acoustic sandwich panel being characterised, along said connection area, in that the intumescent adhesive network (3) formed in this way has at least one discontinuity (5) allowing the circulation of a fluid between at least two alveolar units (2).
B32B 3/06 - 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 features of form at particular places, e.g. in edge regions for securing layers togetherLayered 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 features of form at particular places, e.g. in edge regions for attaching the product to another member, e.g. to a support
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
G10K 11/168 - Plural layers of different materials, e.g. sandwiches
38.
Assembly centering device for turbojet engine nacelle
The present disclosure relates to a centering device for a nacelle of a turbojet engine providing the flush centering of an outer downstream panel of a thrust reverser with respect to a cowl of a fan casing. The centering device includes, in one single piece: a sub plate allowing the fixing of the centering device to the fan casing; a first positioning arm integrally formed with the sub plate, protruding upstream, in such a manner as to form, with respect to a directing axis (A) of the nacelle; a first radial abutment designed for guiding the cowl of the fan casing; and a second positioning arm, integrally formed with the sub plate, protruding downstream, in such a manner as to form, with respect to the directing axis (A) of the nacelle, a second radial abutment designed for guiding the outer downstream panel.
The present disclosure relates to a drilling robot and a method for controlling a drilling robot including a driven mechanical structure allowing to place a drilling tool in a sequence of drillings programmed in terms of position and orientation of the drilling of a part such as a technical skin. The method includes a step of determining the acceleration of the drilling tool at the end of the approach on a drilling position, then also testing a stabilization condition of the drilling tool to finally establish a drilling authorization.
G05B 19/416 - Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by control of velocity, acceleration or deceleration
40.
DEVICE FOR SECURELY LOCKING TWO PARTS OF A TURBOJET ENGINE NACELLE
Device (10) for securely locking a first part (12) to a second part (14), the device (10) comprising at least one centring stud (20a, 20b) and a lock (24a, 24b) consisting of a hook (26a, 26b), a longitudinal hinge pin (28) that pivotably connects the hook (26a, 26b) to the first part (12), and a retaining member that is designed to engage with the hook (26a, 26b). The hinge pin (28) of the hook (26a, 26b) delimits an axial stop (46, 52a, 52b), and the stud (20a, 20b) has a free locking end (23a, 23b) that extends perpendicular to the hinge pin (28) that is to be blocked and that is designed to engage with the axial stop (46, 52a, 52b) so as to block the hinge pin (28) in axial translation.
The invention relates to a locking device (12) for a thrust reverser (14) with door (16) equipping a turbo jet engine nacelle (10), characterized in that the device (12) comprises a first fitting (28) secured to the door (16) and a second fitting (30) secured to the fixed structure of the reverser (14), an S-shaped double hook (32) which has a first hook (34) and a second hook (36) and which is pivot mounted on the body (20) of the actuator (18) so that it pivots between a locked position in which the first hook (34) and the second hook (36) collaborate with the first fitting (28) and with the second fitting (30) respectively, so as to lock the door (16) in the closed position thereof, and an unlocked position in which said hooks (34, 36) release the door (16), and a means (38) of actuating the double hook (32).
The invention relates to a shape-woven preform which has an omega-shaped cross-section including a core (4) and a sole (2). At least part of the core (4) and at least part of the sole (2) have weft threads (26, 28, 30) in common with one another.
D03D 1/00 - Woven fabrics designed to make specified articles
D03D 11/02 - Fabrics formed with pockets, tubes, loops, folds, tucks or flaps
D03D 13/00 - Woven fabrics characterised by the special disposition of the warp or weft threads, e.g. with curved weft threads, with discontinuous warp threads, with diagonal warp or weft
The present disclosure relates to a turbojet engine nacelle equipped with at least one thrust reverser. The thrust reverser includes: two half-cowls forming an outer cowl which is articulated on hinges and translates between closed and open positions, a first actuator to translationally actuate a downstream frame, a second actuator to rotationally actuate each half-cowl, and a lock capable of locking or unlocking the half-cowls relative to one another. In particular, the thrust reverser includes cascades vanes supported at their upstream end by an upstream frame and at their downstream end by the downstream frame, and a connector between the downstream frame and the external cowl. The cascade vanes are enclosed in a shroud formed by a fan casing and a fan cowl.
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
44.
TURBOJET ENGINE NACELLE WITH A FLEXIBLE HYDRAULIC FITTING COMPRISING A LENGTH ADJUSTMENT
The invention relates to a turbojet engine nacelle comprising a flexible hydraulic fitting (30) linking two pipes (36, 42), fixed respectively on a mobile element (2) and a fixed element (22) of the nacelle, characterized in that the hydraulic fitting comprises a flexible part (44) having a connector (32, 38) at each end, with at least one of the connectors (38) being adjustable in length, the nacelle comprising a fastening support (40) of the adjustable-length connector (38), said connector (38) comprising a means of adjustment (76) of the axial position of the connector (38) with respect to the fastening support (40).
F16L 3/01 - Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets for supporting or guiding the pipes, cables or protective tubing, between relatively movable points, e.g. movable channels
F16L 15/02 - Screw-threaded jointsForms of screw-threads for such joints allowing substantial longitudinal adjustment by the use of a long screw-threaded part
F16L 27/107 - Adjustable jointsJoints allowing movement comprising a flexible connection only the ends of the pipe being interconnected by a flexible sleeve
F16L 27/12 - Adjustable jointsJoints allowing movement allowing substantial longitudinal adjustment or movement
45.
SEAL OF THE BUBBLE GASKET TYPE INCORPORATING AT LEAST ONE RIGID END STOP
The invention relates to a sealing gasket intended to be interposed between two parts of a propulsion assembly, said sealing gasket (1) comprising a cylindrical tubular part (2) and at least one pair of contact studs (8, 9), each stud having two opposite ends each one forming a bearing surface (81, 91, 82, 92), each contact stud (8, 9) being positioned in a respective opening of the tubular part (2) of the gasket so that the bearing surfaces (81, 91) of the contact studs which face toward the inside of the tubular part (2), referred to as internal bearing surfaces (81, 91), are able to come into contact once the deformation of the gasket exceeds a predetermined threshold deformation.
The invention relates to a nacelle (1) of an aircraft, characterised in that it comprises an automatic identification device (2) on a surface (3) of the nacelle (1), containing at least one element of information allowing access to a base of technical resources relating to the nacelle (1).
Hydraulic control of a thrust reverser for a nacelle of a turbojet, comprising a hydraulic machine (30) fed by a pressure source (2), which powers the actuators (36) controlling the stroke movement of the reverser, characterised in that said hydraulic machine (30) has a variable cylinder capacity.
A thrust reverser of a turbofan engine nacelle, comprising movable covers (4) that retract relative to a fixed front structure (10) to expose openings radially towards the outside, and rotary gratings (12) linked to the front structure by pivots (48) which, when said covers open, pivot in the annular passage, partially closing it and returning the flow, via the openings, towards the front, characterised in that, when the covers (4) are closed, the rotary gratings (12) are at least partially contained in the front structure (10), the reverser comprising guide means (44) that move said gratings backwards, in addition to the pivoting of same, when the covers are opened.
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.
DEVICE AND ASSEMBLY FOR NON-DESTRUCTIVE TESTING OF A COMPOSITE PART AND METHOD FOR NON-DESTRUCTIVE TESTING OF A COMPOSITE PART BY TRANSMISSION ULTRASOUND
The invention relates to a device (23) for non-destructive testing of a composite part (21), which is characterised by comprising: at least two magnetic bodies (25, 27), at least one of said at least two magnetic bodies being adapted such as to exercise a force of attraction such as to allow mutual restraint, or restraint of one by the other, of the magnetic bodies on either side of said part, said magnetic bodies being intended to be positioned directly on at least one wall (29, 31) of the part to be tested; and at least one transmitting ultrasound probe (33) positioned on one of said magnetic bodies, and at least one receiving ultrasound probe (35) positioned on the other one of said magnetic bodies.
G01N 29/22 - Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic wavesVisualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object Details
G01N 29/265 - Arrangements for orientation or scanning by moving the sensor relative to a stationary material
50.
TURBOJET ENGINE NACELLE COMPRISING A SECURE LOCK FOR THE REAR HALF-PORTIONS
A turbojet engine nacelle comprising a secure lock for the rear half-portions. A turbojet engine nacelle comprising two rear half-portions (24, 26) arranged downstream from front half-covers (20, 22), the two rear portions and the two covers closing against each other in a same axial junction plane (P), a lock provided at the junction between the two rear portions (24, 26), on the upstream side, and tangentially clamping these two portions together, comprises a manoeuvring handle (28) that pivots in a transverse plane, characterised in that, with the lock locked and the front covers (20, 22) closed, the handle (28) is fully fitted into a transverse external cutout that extends over the two covers, apart from a shoulder formed at the free end of same that is below one of the covers (20).
The invention relates to a sandwich panel comprising at least one core produced in a honeycomb structure (2), receiving a skin made of composite materials (6, 14) on each side, said panel comprising compact lateral parts on the side of said structure, along the edges thereof, characterised in that the structure receives a reinforcement (10) arranged on the rear surface thereof along the cutting edges.
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
F16B 5/01 - Joining sheets or plates to one another or to strips or bars parallel to them by means of fastening elements specially adapted for honeycomb panels
52.
METHOD FOR REPAIRING SANDWICH PANELS MADE OF COMPOSITE MATERIALS INVOLVING THE CREATION OF A CORE OR OF A MOULD USING STEREOLITHOGRAPHY
Method for repairing sandwich panels made of composite materials following impact that has damaged the core of this panel characterized in that it involves acquisition of a numerical model of the shape of the damaged zone then use of a stereolithography method based on the numerical model to create a replacement core (14) or a mould (10) in which this replacement core will be moulded, followed by creation of a replacement component (18) comprising this core, then the installation of this component which is fitted into an opening (6) cut in the sandwich panel around the damage, and finally attachment of the replacement component to the panel.
B29C 73/04 - Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass using preformed elements
B29C 73/06 - Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass using preformed elements using plugs sealing in the hole
B29C 67/00 - Shaping techniques not covered by groups , or
53.
DEVICE FOR DE-ICING THE INLET OF A NACELLE OF AN AIRCRAFT ENGINE, METHOD FOR PRODUCING SUCH A DE-ICING DEVICE, AND AIRCRAFT ENGINE NACELLE PROVIDED WITH SUCH A DE-ICING DEVICE
The invention relates to a de-icing device comprising a piccolo tube (43) built into the front wall (37) defining the inner volume of the perforated front lip (36). The piccolo tube (43) is in contact with an alveolar noise-reduction structure (44) that has perforations and channels for the circulation of hot air supplied by the piccolo tube (43), the hot de-icing air spreading through the perforations and channels of the alveolar structure (44), to the perforations facing the front lip (36).
A thrust reverser device for an aircraft includes at least two thrust reversers, and each of them includes a movable cowl movably actuated by an actuator driven by an electric motor. The electric motor is powered by a single power-conversion module including at least one autotransformer which is supplied with an alternating electric voltage and connected to at least one rectifier stage converting the alternating electric voltage into a direct voltage. The rectifier stage is connected to a current balancing stage and a current smoothing stage, supplying with the direct voltage the electric motor of the electric actuator of the movable cowl.
H02P 7/06 - Arrangements for regulating or controlling the speed or torque of electric DC motors for regulating or controlling an individual DC dynamo-electric motor by varying field or armature current
F02K 1/76 - Control or regulation of thrust reversers
B64D 41/00 - Power installations for auxiliary purposes
B64D 33/04 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
55.
CONNECTION BETWEEN A TURBO JET ENGINE NACELLE THRUST REVERSER AND AN ACTUATOR, WITH LASH
The present invention relates to an assembly comprising: - a mobile frame (8) supporting at least one turbo jet engine nacelle thrust reverser cowl, - an actuator comprising actuating cylinders (2) applying a retraction or traction axial force for respectively opening or closing the reverser so as to carry out maintenance operations, and - a connecting device connecting said actuator and said reverser. According to the invention, this assembly is notable in that said connection device comprises: - a bearing surface (10) applying the retraction force to said mobile frame (8), and - a cable (18) or an articulated link applying the traction force to said mobile frame (8).
B64D 29/06 - Attaching of nacelles, fairings, or cowlings
F15B 15/02 - Mechanical layout characterised by the means for converting the movement of the fluid-actuated element into movement of the finally-operated member
The invention relates to a method for assessing the damage to a polyurethane-type paint-covered composite material. Said method uses infrared spectrometry on said paint and is characterized in that two separate criteria, characterizing the heat aging of the paint, are measured on the obtained spectrogram. Each criterion includes measuring a height of a particular peak (6) on the curve of the spectrum, thus giving two separate assessments of said aging. Then both these criteria are combined with each other to obtain a result indicating the damage level.
G01N 21/35 - Investigating relative effect of material at wavelengths characteristic of specific elements or molecules, e.g. atomic absorption spectrometry using infrared light
G01N 21/84 - Systems specially adapted for particular applications
G01N 21/88 - Investigating the presence of flaws, defects or contamination
G01N 21/95 - Investigating the presence of flaws, defects or contamination characterised by the material or shape of the object to be examined
According to the invention, a panel having a sandwich structure, including a core (1) sandwiched between a first skin (2) and a second skin (3), and an assembly for repairing one of said skins which includes resin (4a) and a doubler (4b), characterized in that the repair assembly includes a plurality of non-through attachments (4c) which attach the doubler (4b) to the skin to be repaired, each substantially being in the shape of a rod having a head mounted thereon and which are attached to the acoustic panel by the resin (4a) injected into the core (1).
G10K 11/172 - Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using resonance effects
B29C 67/00 - Shaping techniques not covered by groups , or
B32B 43/00 - Operations specially adapted for layered products and not otherwise provided for, e.g. repairingApparatus therefor
B64D 29/00 - Power-plant nacelles, fairings or cowlings
B29C 73/10 - Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass using preformed elements using patches sealing on the surface of the article
The present invention relates to a seal (105) for an aircraft turbojet engine nacelle thrust reverser, said seal comprising a body (113) of which the cross section with respect to a longitudinal axis (L) of the seal is, for example, substantially circular, and a base (115) which is intended to be mounted in a seal support. This seal is notable in that the base (115) of said seal has mutually-spaced openings (143).
F16J 15/02 - Sealings between relatively-stationary surfaces
F16J 15/06 - Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
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 concerns a nacelle (10) for an aircraft engine, comprising a thrust reverser cowling (20) that is slidably mounted between a direct jet position, and a reversed jet position in which the cowling (20) opens a passage in the nacelle (10) and uncovers the deflection means, and a drive means for moving the cowling (20), characterised in that the nozzle section (30) of the cowling (20) delimits at least one opening (36) that is combined with an escape door (38), the escape door (38) being movably mounted on the cowling (20) between a closed position in which the door (38) engages with the associated opening (36) to counteract the flow of air through said opening (36), and an open escape position in which the door (38) is retracted to allow a portion of the air flow to flow through said opening (36).
B64D 33/04 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
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 1/12 - Varying effective area of jet pipe or nozzle by means of pivoted flaps
F02K 1/08 - Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
61.
THRUST REVERSER FOR A TURBOJET POD, INCLUDING AN END STOP ON THE MAIN GUIDE RAIL
The invention relates to a thrust reverser for a turbojet pod, including cowls (6) that move backwards to open said reverser, wherein each cowl comprises a main axial guide rail, that mainly bears the load of said cowl, and a secondary rail guiding an outer portion of said cowl. Said thrust reverser is characterized in that a rear end stop (14, 16) of the cowl (6) is arranged on the main rail.
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
62.
AFTERBODY FOR A TURBOJET ENGINE COMPRISING A NOZZLE PROVIDED WITH A THRUST REVERSER SYSTEM THAT INCORPORATES A CROWN OF NOISE-REDUCING CHEVRONS
The invention concerns an afterbody for a turbojet engine having a central axis (XX'), provided with a nozzle (1) comprising two doors (3, 4) mounted facing each other between two lateral beams (5, 6) pivoting around axes (15, 16, 17, 18) defining a pivot direction, between a retracted position, in which a middle portion (19a, 20a) of the downstream edge of said doors (3, 4) forms the edge (24) of the outlet section (S) of the nozzle (1) combined with the downstream edges (11, 14) of the two lateral beams (5, 6), and a deployed position, in which said middle portions (19a, 20a) of the downstream edges of the pivoting doors (3, 4) come together so as to block the channel between the two lateral beams (5, 6) in order to reverse the thrust of the turbojet engine gases, the edge of the outlet section of the nozzle further having a crown of noise-reducing chevrons (26) alternating with indentations (25) and the afterbody being characterised in that each noise-reducing chevron (26) formed on the middle portion (19a, 20a) of the downstream edge of a pivoting door is opposite an indentation in the middle portion (20a, 19a) of the other pivoting door (4, 3) in the direction perpendicular to said pivot direction, the shapes of the chevrons (26) and of the indentations (25) being defined to match in such a way that each chevron (26A) fits into the opposing indentation (25A) when the pivoting doors (4, 3) are deployed.
The present invention concerns a seal (26) designed to be interposed between a cover of a rear section of a nacelle and a turbojet engine of a propulsion assembly of an aircraft, the seal (26) comprising a tubular body (28) that extends axially and that delimits a first inner cavity (30), and a securing flange (32) that is rigidly connected to the tubular body (28). The seal (26) according to the invention is remarkable in that it comprises a protuberance (34) that extends generally radially from the tubular body (28) and forms a first lip (36a) and a second lip (36b), the protuberance (34) delimiting a second inner cavity (38).
The invention concerns an afterbody for a turbojet engine having a central axis (XX'), provided with a nozzle (1) comprising two doors (3, 4) mounted facing each other between two lateral beams (5, 6) pivoting around axes (15, 16, 17, 18) defining a pivot direction, between a retracted position, in which a middle portion (19a, 20a) of the downstream edge of said doors (3, 4) forms the edge (24) of the outlet section (S) of the nozzle (1) combined with the downstream edges (11, 14) of the two lateral beams (5, 6), and a deployed position, in which said middle portions (19a, 20a) of the downstream edges of the pivoting doors (3, 4) come together so as to block the channel between the two lateral beams (5, 6) in order to reverse the thrust of the turbojet engine gases, the edge of the outlet section of the nozzle further having a crown of noise-reducing chevrons (26) alternating with indentations (25) and the afterbody being characterised in that each noise-reducing chevron (26) formed on the middle portion (19a, 20a) of the downstream edge of a pivoting door is opposite an indentation in the middle portion (20a, 19a) of the other pivoting door (4, 3) in the direction perpendicular to said pivot direction, the shapes of the chevrons (26) and of the indentations (25) being defined to match in such a way that each chevron (26A) fits into the opposing indentation (25A) when the pivoting doors (4, 3) are deployed.
The present invention relates to a method for repairing a skin (3, 4) of a composite panel (1), said skin comprising a group of stacked plies embedded in a matrix. The method comprises steps of: removing the plies and the matrix in a repair zone; installing a group of repair plies, said repair plies being disposed such as to overlap with plies of the skin to be repaired; and curing a material that is intended to form a matrix around the repair plies. The method is characterised in that the repair plies are disposed such as to overlap with the plies of the skin on both sides of the repair zone in relation to a neutral plane of the skin to be repaired.
B29C 73/10 - Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass using preformed elements using patches sealing on the surface of the article
B29C 73/26 - Apparatus or accessories not otherwise provided for for mechanical pretreatment
66.
THRUST REVERSER OF A TURBOJET NACELLE, COMPRISING GRIDS AND CYLINDERS FIXED UPSTREAM OF MOBILE HOODS
The invention relates to a thrust reverser of a turbojet nacelle, comprising mobile hoods (10) which retract in relation to a front frame (2) under the effect of cylinders (14), driving, by means of connecting links (24), the tilting of flaps (8) initially tucked away inside said hoods, in order to substantially close the annular cold air stream (4), and opening grids (12) arranged around said stream, which grids receive the cold air flow in order to send it back towards the front. The invention is characterised in that the rear ends of the grids (12) and the cylinders (14) are fixed upstream of the mobile hoods (10) and slide therewith, said grids and said cylinders being returned to inside a casing (18) of the front frame (2) when the reverser is closed.
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.
KEY TOOL AND COMPOSITE PANEL, IN PARTICULAR FOR AN AIRCRAFT ENGINE NACELLE, PRODUCED USING SUCH A TOOL
The key tool of the invention comprises at least two keys having adjacent edges, the tool (14, 15) being substantially cylindrical in shape with a central axis, the adjacent edges being substantially parallel to the central axis. The adjacent edges have covers (20, 21) that are tangential relative to the inner and/or outer surface of the key tool. Application to the production of composite panels, in particular for an aircraft engine nacelle.
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 33/48 - Moulds or coresDetails thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling
B29C 33/00 - Moulds or coresDetails thereof or accessories therefor
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
68.
NACELLE COMPRISING A THRUST REVERSER DEVICE WITH MAINTAINED MOBILE GRIDS
The invention relates to an aircraft nacelle comprising a thrust reverser device, an outer hood being fixed directly upstream of the thrust reverser device, as a fan hood (3). The thrust reverser device comprises thrust reverser grids (4, 5) which are mobile between a direct jet position and a thrust reversing position and driven by a mobile hood (4) that can translate along the axis of the nacelle. The thrust reverser grids (4, 5) cooperate with rigidifying and sealing means (11, 20; 9, 25; 47, 60, 52; 42, 50, 61) of said thrust reverser device.
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
69.
FRONT COVER FOR A TURBOJET ENGINE NACELLE COMPRISING A MANOEUVRING SYSTEM
A front cover for a turbojet engine nacelle, which slides forwards on a guide system (8) linked to the fixed rear structure (4), in order to provide, in the open position, a space between said cover and said structure, characterised in that it comprises a manoeuvring system (10) comprising a linking device that links a handle (12) actuated by an operator to the rear structure (4), and that moves the cover (2) along the complete travel path of same when said handle is manoeuvred, with a demultiplication of the movement applied by the operator.
Disclosed is an auxiliary arm forming a profiled duct that radially crosses the air flow in a nacelle comprising a turbofan. The auxiliary arm includes a fire-proof seal (18) for following the relative movements between the outer structure (2) and the inner structure (4) and is characterized in that same has an inner part (6) to be rigidly secured to the inner structure (4) as well as an outer part (14) to be flexibly connected to the outer structure (2) by means of the fire-proof seal (18), said two parts being connected to one another along a connection surface.
The invention relates to a production method and a honeycomb composite panel according to which two honeycomb structures (5, 6) are assembled along one of the connecting edges of said structures above a step (22) in a skin of variable thickness (20). A bevel (23) is produced under the connecting edge of at least one honeycomb structure (6). At least one other honeycomb structure (5) is arranged on the skin (20) in such a way as to overhang the step (22), and the at least one bevelled structure (6) is then glued to the skin, beyond (27) the step and in abutment against at least the other structure (5).
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
G10K 11/168 - Plural layers of different materials, e.g. sandwiches
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
B29L 31/60 - Multitubular or multicompartmented articles, e.g. honeycomb
72.
ASSEMBLY COMPRISING A COLLET PROVIDED WITH A FLANGE COMPRISING AN ANNULAR HOLLOW RECEIVING FOLDS OF COMPOSITE MATERIALS
An assembly comprising a collet provided with a flange comprising an annular hollow receiving folds of composite materials. An assembly comprising a collet (2) made from composite materials provided with a flange (20), said collet having an axial part fittingly receiving, on the inside or on the outside, a complementary axial part of the flange, characterised in that the axial part of the flange comprises, facing the collet, a hollow (26) forming a transverse annular space that receives, at the bottom, folds of the composite materials of the collet during the draping of the skins (4, 8) of same for the production thereof.
Assembly comprising a shell ring (2) equipped with a flange (30), this shell ring having a substantially axial part that receives with a tight fit, on the inside or the outside, a complementary axial part of the flange that is fixed by a connecting region, characterized in that the connecting region has an annular transverse space that is provided between the shell ring (2) and the flange (30), passes more or less all the way round the shell ring, and is closed axially on both sides by bearing zones (20, 38), said annular transverse space being filled with a connecting material (72) injected through at least one drilled hole (40) in the shell ring or the flange.
The thrust reverser device is integrated in an aircraft engine nacelle. Blocking flaps (18) are stored inside a mobile cowl (10, 21) disposed in a downstream section of the nacelle, under deflection cascade assemblies (15) during direct-jet operation of the nacelle. Means are provided for executing the passage from direct-jet operation to reverse-jet operation in two stages: -the mobile cowl (10, 21) moves in translation towards the downstream end of the nacelle; -each flap (18) is then deployed in the main airflow path (46).
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 1/09 - Varying effective area of jet pipe or nozzle by axially moving an external member, e.g. a shroud
F02K 3/06 - 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 with front fan
F02K 1/76 - Control or regulation of thrust reversers
75.
AUTONOMOUS ELECTRICAL ENERGY PRODUCTION FACILITY FOR AN AIRCRAFT NACELLE
An autonomous electrical energy production facility, designed for a propulsion nacelle of an aircraft comprising an electric circuit comprising actuators (8, 28), characterised in that it comprises means (2) for storing electrical energy that can receive energy from the actuators (8) when thy operate during braking, an electrolyser (12) powered with current by said storage means, and a fuel cell (18) receiving flows of oxygen (O2) and hydrogen (H2) supplied by said electrolyser, which supplies current to the electric circuit (24), producing water (H2O) which is returned to the electrolyser.
The invention relates to a propulsion assembly (1) for an aircraft, comprising a nacelle (3) supporting a turboreactor. Said propulsion assembly is characterised in that the nacelle comprises visual means for indicating the operating state of the propulsion assembly, said means comprising at least one luminous assembly comprising, in turn, at least one luminous device (11), and at least one calculator suitable for collecting information about the operating state of the propulsion assembly and for controlling the luminous device according to said collected information.
A method for producing a woven preform for a beam made from composite materials provided with transverse inner reinforcements. A method for producing a woven preform designed to be impregnated, in order to form a beam (2) representing an elongate formwork provided with transverse inner reinforcements (14) linking sides of this beam together, characterised by the weaving a fabric in a plane comprising a main side (4) provided with slots formed by debinding superposed layers of fabric, said plane being folded to obtain different sides of the beam (8, 10, 12), said slots being raised in order to form transverse walls that constitute the inner reinforcements (14), said transverse walls being linked together opposite the main side (4) by perpendicular linking walls, designed to be secured to the inside of the side of the beam opposite (10) said main side.
An electric thrust reverser system for an aircraft engine nacelle and an aircraft engine nacelle provided with same. The invention concerns an electric thrust reverser system for an aircraft engine nacelle, comprising at least one mechanism (2 or 3) for actuating a thrust reverser mechanism like a reverser door. The actuating mechanism (2 or 3) comprises first (6) and second (7) drive cylinders. Each cylinder comprises a mechanical connection casing (9), a primary lock (8) and a mobile rod (10) rigidly connected to a point linked to the associated reverser mechanism, like a reverser door. A motorised drive unit (11) is connected mechanically by flexible shafts (12) to the mechanical connection casings (9) of each cylinder (6, 7) of the actuating mechanism (2 or 3) and set in motion under the control of a control unit (1) by means of an electrical connection (16, 17). A tertiary lock (13) is disposed to secure the associated thrust reverser mechanism like a thrust reverser door to a fixed structure of the nacelle.
Turbo jet engine nacelle thrust reverser comprising mobile cowls (10) which move back with respect to a front frame (2) under the effect of an actuating system, via a control mechanism driving the pivoting of flaps (8) to more or less close off the annular cold-air duct (4) and open the cascades of veins (12) arranged around this duct which receive the cold air flow to deflect same forward, characterized in that with the reverser closed, the cascades of veins (12) are partially built into the cowls (10) and in that it comprises an actuating system which causes the cascades of veins to move back by a travel that is reduced in comparison with that of the cowl.
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
80.
DEVICE FOR ASSISTING IN THE MANOEUVRING OF A COVER AND TURBOJET ENGINE NACELLE EQUIPPED WITH SAME
The present invention concerns a device for assisting in the manoeuvring of a cover of a nacelle of a turbojet engine or similar. The assistance device comprises a joint collinear with an existing joint or hinge for a fitting of the cover (1, 2), the joint of the device being rigidly secured to an angled part (13-15) of which one end bears on the fitting (35, 38) of the cover (1, 2) and of which one point is hinged to a compression spring (17, 27) in order to apply assistance momentum to the fitting of the cover when the cover (1, 2) is raised. Application to nacelles of turbojet engines or similar.
The present invention relates to a process for repairing a panel (1) comprising at least one perforated skin (3), called the acoustic skin, the process comprising the step of applying at least one doubler (51, 52, 53) to at least one damaged zone (4) of the acoustic skin (3) of said panel, the doubler being superposed on the acoustic skin, the doubler comprising a plurality of orifices, the ratio of the size of the orifices of the doubler to the size of the perforations in the acoustic skin being higher than or equal to 100.
B29C 73/10 - Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass using preformed elements using patches sealing on the surface of the article
The present invention relates to a turbofan nacelle having a downstream section including at least one cowling (3a) ending in at least one hinged flap (50) constituting a nozzle, characterised in that said flap is hingedly and translatably hinged relative to said cowling.
An air intake structure for a turbojet engine nacelle includes an inner panel to be attached to a fan casing, and an external panel capable of a translational movement in a longitudinal direction of the nacelle. The external panel incorporates a portion of an air inlet lip able to provide a junction between the inner panel and the external panel, and each of the air inlet lip portion and the inner panel is equipped, at least in the region of a joining end, with an acoustic attenuation structure. In particular, at least one of the joining ends is equipped with a radial buffer able to come into contact with a corresponding joining flange exhibited by the other joining end when the external panel is in a closed position.
A gas ejection cone includes a cylindrical-shaped front cone portion, a conical-shaped rear cone portion, a ventilation tube and a support bearing of this drainage and/or ventilation tube. The ventilation tube extends inside the cylindrical-shaped front and conical-shaped rear cone portions and emerges at the end of the conical-shaped rear cone portion. In particular, the conical-shaped rear cone portion includes a front sub-portion connected to the cylindrical-shaped front cone portion, and a rear sub-portion removably secured to the front sub-portion. The rear sub-portion is further equipped with an outlet port of the ventilation tube.
The invention concerns device for de-icing an air inlet lip (111) of an aircraft nacelle (100), said device comprising a pre-exchanger (2), an intake means capable of taking in low-pressure air downstream from the fan (12), two high-pressure air intake means downstream from the compressor (10, 11) in addition to controlled valves (6, 7, 8, 9, 14) and check valves (4, 5) installed in an air flow network (1, 13), remarkable in that the pre-exchanger (2) comprises a low-pressure air outlet (19) capable of opening into the air inlet lip of the aircraft nacelle (100) via a pipe (3) of the air flow network.
A method for controlling a lift cylinder for an aircraft engine nacelle, a cylinder lifting system implementing the method and a nacelle equipped with same. The cylinder lifting system comprises a means (28, 37-39; 64, 68; 50) for modifying the maximum force value of the cylinder activated by a means (37; 46; 74; 92) for determining a portion defined as the start of the extension stroke of the cylinder. As a result of the modification of the maximum force value (28), the pressure source (29) therefore only applies the full force of the cylinder after the starting stroke so as to protect a lock (11) of the reverser cowl (4, 10) forgotten during maintenance.
F15B 15/16 - Fluid-actuated devices for displacing a member from one position to anotherGearing associated therewith characterised by the construction of the motor unit of the straight-cylinder type of the telescopic type
F15B 15/04 - Mechanical layout characterised by the means for converting the movement of the fluid-actuated element into movement of the finally-operated member with oscillating cylinder
F15B 11/028 - Systems essentially incorporating special features for controlling the speed or the actuating force or speed of an output member for controlling the actuating force
A dual-grid reverser without rods in the duct. A thrust reverser device 1 for an aircraft nacelle comprising a fixed outer structure (2) provided with a front frame, said device comprising: • - a movable cowl (3) slidably mounted relative to said fixed outer structure (2) between a direct jet position in which no thrust reverse takes place, and a reversed jet position in which thrust reverse takes place, • - radially external thrust reverse grids (5), uncovered when said movable cowl (3) slides from the direct jet position of same to the reversed jet position of same, and • - radially internal thrust reverser components (4), each mounted pivoting on said front frame, and linked to said movable cowl (3) by at least one rod (6).
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
88.
CONTROL DEVICE FOR A TURBOJET ENGINE THRUST REVERSER, BLOCKING THE REVERSER
A control device for a turbojet engine thrust reverser, blocking the reverser. A control device for a thrust reverser of a turbojet engine nacelle comprising mobile parts (10) driven by actuators (12), which are deployed to reverse the thrust, said device comprising a first blocking control (24) acting on the driven system and a second blocking control acting mechanically on the mobile elements, which, when implemented, prevent the deployment of these mobile parts (10), characterised in that it comprises a means (44) which, when the mechanical control is implemented, prevents the first control from being disengaged.
A nacelle of a turbine engine includes an external cowling, an internal cowling, and a heat exchanger associated with at least one circulation duct for a fluid. In particular, the circulation duct forms a recirculation loop through the heat exchanger, and the recirculation loop includes at least one circulation area extending at least partially along the external cowling in contact with a wall of the external cowling so as to allow exchange of heat by conduction with the air outside the nacelle.
F02K 3/06 - 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 with front fan
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
The present invention relates to a method for manufacturing a composite part comprising at least one main structure (1) and at least one auxiliary structure which is secured directly to said main structure and has smaller dimensions than said main structure. The method according to the invention is noteworthy in that it comprises the following steps of: -successively draping, by way of an automated draping method: o a plurality of composite plies that define the main structure (1); o at least one reference strip (19, 21) on said main structure (1), delimiting a draping zone (17) for the auxiliary structure; -manually draping, in said draping zone (17) for the auxiliary structure, a plurality of composite plies (5) that define said auxiliary structure; -polymerizing at least said main structure (1) and auxiliary structure.
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 65/78 - Means for handling the parts to be joined, e.g. for making containers or hollow articles
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
F02K 1/70 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
Method of manufacturing a composite component comprising at least one main structure (1) and at least one auxiliary structure directly attached to said main structure and of smaller dimensions than said main structure, the method comprising the following steps: using an automated lay-up method, successively laying up (i) a plurality of composite plies defining the main structure (1), and (ii) at least one marker tape (19, 21) on said main structure (1) delimiting a zone (17) for the laying-up of the auxiliary structure; in the lay-up zone (17) of the auxiliary structure, manually laying-up a plurality of composite plies (5) defining said auxiliary structure; and polymerizing at least said main (1) and auxiliary structures.
A nacelle includes an outer structure provided with a thrust reverser and a front frame, a movable cowl, and an inner structure covering a downstream section of a turbojet engine. The outer structure and the inner structure define a flow stream of an air flow. In particular, the connection of the front frame and diversion cascade of the thrust reverser which is mounted on a reduced transverse section area of the movable cowl is centered on an axis offset relative to an axis on which the connection of the front frame and the diversion cascade mounted on the remainder of the periphery of the movable cowl is centered.
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
B64D 29/06 - Attaching of nacelles, fairings, or cowlings
B64D 33/04 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
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
93.
THRUST REVERSER WITH A BLOCKING FLAP ARTICULATED BY A THREE-POINT LINKAGE
The present invention relates to a thrust reverser (1) for a turbojet engine comprising a fixed upstream structure (10) supporting retractable devices (11) for diverting a portion of the flow of air, and a cover (12) that is movable in translation in a substantially longitudinal direction combined with a pivoting blocking flap (13), characterised in that the blocking flap is articulated by a three-point linkage system comprising at least a first telescopic rod (14) having a first end (14a) connected to the fixed upstream structure, a second rod (15) having a first end (15a) connected to the movable cover and a third rod (16) having a first end (16a) connected to the blocking flap, each of the three rods having a second end linked to the other two at a linkage point of the three rods.
F02K 1/62 - Reversing jet main flow by blocking the rearward discharge by means of flaps
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
F02K 1/70 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
94.
FITTING FOR ATTACHING AN ACTUATOR FOR A DOOR-TYPE REVERSER OF A JET ENGINE NACELLE, AND JET ENGINE NACELLE
The jet engine nacelle is of the type having a door-type thrust reverser, with an opening mechanism comprising at least one mobilizing actuator. The nacelle has an engine attachment flange (22) and an attachment flange (20) for the reverser, integral with a composite panel (34) that limits a secondary flow of the fan outlet jet. The actuator is attached (28) by a fitting (24-28) to the attachment flange (20) for the reverser.
Turbojet engine nacelle thrust reverser comprising mobile cowls (10) which retreat with respect to a front frame (2), causing, through the intermediary of actuating cylinders (20), flaps (8) that are initially folded up inside these cowls to pivot in order to substantially close off the annular cold air duct (4), and opening cascades of vanes (12) positioned around this duct which receive the stream of cold air and deflect it forward, characterized in that the cascades of vanes (12) are fixed to the mobile cowls (10) and slide therewith.
F02K 1/62 - Reversing jet main flow by blocking the rearward discharge by means of flaps
F02K 1/70 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
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
96.
PROFILED TWO-PART CONNECTING ROD DESIGNED TO BE POSITIONED IN AN AIRCRAFT ENGINE FLOW
Connecting rod designed to be positioned in an aircraft engine flow (F), comprising a profiled longitudinal tubular bar (2) which at each end has fixing means (8), characterized in that it comprises a main part (4) comprising a longitudinal central portion with a hollow cross section open on one side, forming the overall shape of a U, and at each end the fixing means (8) made of the same material to form one and the same component, this connecting rod additionally comprising a longitudinal cap (6) closing the opening of the cross section of the main component in order to form the profiled tubular bar (2).
A turbojet engine nacelle comprising a thrust reversing device with doors, comprising inner walls on the sides of the opening. A turbojet engine nacelle comprising a thrust reversing device comprising doors (4) that swing to brake the direct gas flow, guiding it through counter-thrust openings (8), the inside of each door comprising, at the front, a cavity receiving a spoiler turned towards the front when this door is open, the fixed structure (2) upstream from each door (4) supporting a deflection edge (16) that partially covers the cavity, characterised in that the fixed structure (2) supports, on each side, counter-thrust openings (8), a flank (18) disposed in the continuation of the deflection edge (16) and extending behind the cavity, which is incorporated into a leaf of the door (4).
A turbojet engine nacelle comprising a thrust reversing device with doors, comprising inner walls on the sides of the opening. A turbojet engine nacelle comprising a thrust reversing device comprising doors (4) that swing to brake the direct gas flow, guiding it through counter-thrust openings (8), the inside of each door comprising, at the front, a cavity receiving a spoiler turned towards the front when this door is open, the fixed structure (2) upstream from each door (4) supporting a deflection edge (16) that partially covers the cavity, characterised in that the fixed structure (2) supports, on each side, counter-thrust openings (8), a flank (18) disposed in the continuation of the deflection edge (16) and extending behind the cavity, which is incorporated into a leaf of the door (4).
Reduction of the drag of a wall by an ultrasonic wave grating. A method for reducing the drag of an aircraft comprising at least one device for generating an ultrasonic interference grating on at least one shrouded wall of the aircraft, characterised in that it comprises a step of heterodyning the interference grating in such a way as to make it mobile.
The invention relates to an aircraft propulsion assembly (1) including a turbojet pod (3) wherein said pod includes a stationary structure and a movable structure (7), including: a thrust reversal device (9) including at least one cover (15) translatable along a substantially longitudinal axis (17) of the pod between a retracted position, corresponding to a direct jet operation of the pod, and a deployed position, corresponding to a reverse jet position of the pod; and a secondary air flow exhaust nozzle (11) including a device (33) for electrically controlling and actuating said nozzle. The propulsion assembly according to the invention is characterized in that the device for controlling and actuating the nozzle includes at least one electrical switch (37) suitable for being closed during a direct jet operation of the pod and moreover suitable for being open during a reverse jet operation of the pod. Said switch includes at least one stationary connector (39) and at least one movable connector (41).
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
patents
