A fastener apparatus may include a first part configured to be attached to a second part and the first part may include a polymer including a plurality of continuous fibers that continuously extend from one end of the first part to another end of the first part. In an aspect, the plurality of continuous fibers may be longer than a length of the first part or long enough to wrap fully around a major axis of the part.
A thrust reverser for a turbofan engine for an aircraft includes a fixed structure arranged in communication with a fan duct of the turbofan engine, a pivot door connected to the fixed structure by at least one hinge and configured to rotate around the hinge to move between an open position and a closed position, and a continuous loop seal mounted to the fixed structure and configured to contact a seal land surface on the pivot door when the pivot door is in the closed position. The continuous loop seal forms a single continuous loop without breaks along a longest dimension of the continuous loop seal. A propulsion system for the aircraft includes the turbofan engine with a multi-blade fan, a fan duct, and the thrust reverser.
An aircraft propulsion system includes an engine assembly including a fan that rotates to move air to create thrust, and a cowl that surrounds at least a portion of the engine assembly. The cowl includes an outer surface arranged away from the engine assembly that provides an aerodynamic surface. The aircraft propulsion system also includes a thrust reverser mechanism connected to the cowl and configured to change a direction of the thrust while in a reverse position. The thrust reverser includes a blocking door and blocking door hinge. The blocking door is connected to the blocking door hinge, and the blocking door is configured to pivot around a hinge line between a forward position and the reverse position. The blocking door hinge includes a hinge bolt that is misaligned with the hinge line.
An aircraft propulsion system includes an engine assembly including a fan that moves air, and a cowl that surrounds at least a portion of the engine assembly when the cowl is in a closed position. The cowl includes an outer surface arranged away from the engine assembly that provides an aerodynamic surface. The aircraft propulsion system also includes a cowl mechanism connected to the cowl and configured to guide the cowl along a movement path from the closed position to an open position. In the open position, an entirety of the cowl is arranged farther away from a horizontal plane passing through a rotating axis of the fan than in the closed position.
An apparatus and method of operating a translating cowl for a turbine engine. The translating cowl is moveable between a first position and a second position. The translating cowl includes a fixed cascade element located within and a blocker door that is operably coupled to die translating cowl. Hie blocker door is movable between a stowed position and a deployed position.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
F02K 3/04 - 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
F02K 1/76 - Control or regulation of thrust reversers
An inlet lip structure includes: an annular inner barrel with forward and aft ends; an annular outer barrel with forward and aft ends; an annular aft bulkhead interconnecting the aft ends of the inner and outer barrels; an annular forward bulkhead interconnecting the forward ends of the inner and outer barrels; an annular lip skin interconnecting the forward ends of the inner and outer barrels, the lip skin having a C-shaped cross-section comprising a nose with inner and outer legs extending therefrom, the lip skin having opposed inner and outer surfaces; and wherein the outer leg of the lip skin incorporates a fuse element having an ultimate strength which is lower than an ultimate strength of the remainder of the lip skin.
F02C 7/05 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
B64D 29/00 - Power-plant nacelles, fairings or cowlings
A thrust reverser assembly for a gas turbine engine including a core engine, a nacelle surrounding at least a portion of the core engine defining a bypass duct between the nacelle and the core engine where an outer door movable between a stowed position and a deployed position extends outwards from the nacelle and a blocker door movable between a stowed position and a deployed position extends into an airflow conduit defined by the bypass duct to deflect air outwards.
F02K 1/70 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
F02K 1/76 - Control or regulation of thrust reversers
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 thrust reverser cascade can include a peripheral frame having at least one side. At least one plate can be mounted to the at least one side and have a plurality of spaced grooves. In addition, a plurality of vanes can include corresponding terminal ends positioned in the plurality of spaced grooves.
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 1/54 - Nozzles having means for reversing jet thrust
An acoustic liner can include a support layer with a set of partitioned cavities defining a set of cells with open faces, a first facing sheet operably coupled to the support layer such that the first facing sheet overlies and closes the open faces, and a set of internal separator structures within at least some of the set of partitioned cavities.
A thrust reverser assembly for a turbine engine can include a core engine surrounded by a nacelle. A bypass duct can be formed in the space between the core engine and the nacelle. A blocker door can be movable to a deployed position extending into the bypass duct. A stop can be provided on the core engine to abut and support force applied to the deployed blocker door. The stop can have an airfoil shape.
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
F01L 9/02 - Valve-gear or valve arrangements actuated non-mechanically by fluid means, e.g. hydraulic
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 1/76 - Control or regulation of thrust reversers
A thrust reverser assembly for high-bypass turbofan engine. The thrust reverser assembly includes a translating cowl mounted to a nacelle of an engine. The thrust reverser assembly includes blocker doors axially guided adjacent first ends thereof by a fixed structure and pivotally and slidably connected along lengths thereof to an inner wall of the translating cowl so that translation of the translating cowl in the aft direction causes the blocker door to move from a stowed position to a deployed position. The thrust reverser assembly includes a stop disposed on the core engine or on the blocker door, receiving the load from the high pressure airflow, otherwise borne by an actuation system when deploying the translating cowl and blocker 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
An acoustic liner can include a support layer having a set of partitioned cavities with open faces, a first facing sheet and second facing sheet both having perforations and operably coupled to the support layer such that the facing sheets overlie and close the open faces, and an aerogel layer operably coupled to the second facing sheet.
B32B 3/26 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids
B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
B32B 15/04 - Layered products essentially comprising metal comprising metal as the main or only constituent of a layer, next to another layer of a specific substance
B32B 15/20 - Layered products essentially comprising metal comprising aluminium or copper
F02C 7/045 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
B32B 5/18 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by features of a layer containing foamed or specifically porous material
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
13.
Acoustic liner and method of forming an acoustic liner
An acoustic liner can comprise a support layer including a set of partitioned cavities defining a set of cells with open faces, as well as a first and second facing sheet operably coupled to the support layer that overlie and close the open faces. A set of aerogel fillings can be provided within at least some of the set of cells.
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
B32B 3/26 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids
B32B 27/06 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance
B32B 3/08 - 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 characterised by added members at particular parts
A method and apparatus for a gas turbine engine including a core engine a nacelle surrounding at least a portion of the core engine and defining an interior with an opening. An access door for the opening to provide selective access to the opening where the access door provides pressure relief for the interior.
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
An acoustic liner (20) with perforation (30) and method of constructing (100) an acoustic liner including forming perforations in the facing sheet by grit blasting (104) the facing sheet and mounting (106) the facing sheet to one side of a support layer having a set of partitioned cavities wherein the facing sheet closes an open face of the cavities except for the perforations to form a set of acoustic resonator cells.
G10K 11/172 - Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using resonance effects
G10K 11/168 - Plural layers of different materials, e.g. sandwiches
B24C 1/04 - Methods for use of abrasive blasting for producing particular effectsUse of auxiliary equipment in connection with such methods for treating only selected parts of a surface, e.g. for carving stone or glass
16.
Acoustic liners and method of shaping an inlet of an acoustic liner
An acoustic liner for a turbine engine, the acoustic liner includes a support layer that includes a set of partitioned cavities with open faces, a perforated sheet that includes a set of perforations with corresponding inlets, the perforated sheet supported by the support layer such that perforations are in overlying relationship with the open faces to form paired perforations and cavities that define acoustic resonator cells, and a coating applied to the perforated sheet.
G10K 11/168 - Plural layers of different materials, e.g. sandwiches
G10K 11/172 - Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using resonance effects
B05D 5/08 - Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures to obtain an anti-friction or anti-adhesive surface
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
B32B 3/24 - 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 an apertured layer, e.g. of expanded metal
B32B 3/26 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids
An acoustic liner for a turbine engine, the acoustic liner includes a support layer that includes a set of partitioned cavities with open faces, a facing sheet operably coupled to the support layer such that the facing sheet overlies and closes the open faces, a set of perforations located in the facing sheet and in fluid communication with a corresponding one of the cavities to form a set of acoustic resonators, and at least a subset of the perforations have an axially-oriented, relative to the axial flow path, inlet.
A thermal insulation blanket assembly having a thermal insulation blanket including an aerogel insulation material having a first surface and a second surface that is oppositely-disposed from the first surface, a backing covering the second surface of the aerogel insulation material, and a skin layer covering the first surface of the aerogel insulation material.
A thermal insulation blanket assembly having a thermal insulation blanket including an aerogel insulation material having a first surface and a second surface that is oppositely-disposed from the first surface, a backing covering the second surface of the aerogel insulation material, and a skin layer covering the first surface of the aerogel insulation material.
B32B 3/04 - 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 characterised by a layer folded at the edge, e.g. over another layer
A thrust reverser assembly for a gas turbine engine including a core engine, a nacelle surrounding at least a portion of the core engine to define a bypass duct between the nacelle and the core engine, including a translating cowl moveable between a first position and a second position, a blocker door movable between a stowed position and a deployed position. The thrust reverser assembly includes multiple actuator assemblies to both translate the cowl and deploy the blocker 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
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F02K 1/76 - Control or regulation of thrust reversers
A thrust reverser assembly (44) for a gas turbine engine (10) and a method to operate it. The gas turbine engine comprises a core engine (14), a nacelle (12) surrounding at least a portion of the core engine (14) defining a bypass duct (30) between the nacelle (12) and the core engine (14) where an outer door (48) movable between a stowed position (58) and a deployed position (68) extends outwards from the nacelle (12) and a blocker door (48, 50) movable between a stowed position (58) and an deployed position (68) extends into an airflow conduit (31) defined by the bypass duct (30) to deflect air outwards.
A gas turbine engine and thrust reverse assembly having a set of outer doors movable between a stowed position and an deployed position, where the set of outer doors extends outwards from the nacelle and a set of blocker doors movable between a stowed position and an deployed position, where the set of blocker door extends into an air flow conduit defined by the bypass duct to deflect air outwards.
F02K 1/54 - Nozzles having means for reversing jet thrust
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
A thrust reverser assembly for a gas turbine engine including a core engine, a nacelle surrounding at least a portion of the core engine defining a bypass duct between the nacelle and the core engine where an outer door movable between a stowed position and a deployed position extends outwards from the nacelle and a blocker door movable between a stowed position and an deployed position extends into an airflow conduit defined by the bypass duct to deflect air outwards.
F02K 1/70 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
F02K 1/76 - Control or regulation of thrust reversers
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
24.
Gas turbine engine with thrust reverser assembly and method of operating
A gas turbine engine and thrust reverser assembly having a set of outer doors movable between a stowed position and a deployed position, where the set of outer doors extends outwards from the nacelle and a set of blocker doors movable between a stowed position and an deployed position, where the set of blocker door extends into an air flow conduit defined by the bypass duct to deflect air outwards.
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 1/70 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
A fluid supply assembly having a conduit through which a fluid may be supplied. A thermal shut-off may be provided to control the supply of fluid through the conduit in response to an environmental temperature condition.
F16K 17/38 - Safety valvesEqualising valves actuated in consequence of extraneous circumstances, e.g. shock, change of position of excessive temperature
A single degree of freedom (SDOF) acoustic liner includes a porous face sheet, a substantially imperforate back sheet generally parallel to and opposing said porous face sheet and defining a thickness therebetween, and an acoustic core layer of contiguous adjacent resonant cavities disposed between the porous face sheet and the imperforate back sheet. The acoustic core layer includes a first resonant cell having a first internal volume therein and a second resonant cell having a second internal volume therein different than the first internal volume. A cell partition wall extends between the porous face sheet and the imperforate back sheet, and separates and seals the first resonant cell from the second resonant cell. In a thickness direction, and perpendicular to a plane generally parallel with the porous face sheet and the substantially imperforate back sheet, the first internal volume overlaps the second internal volume over the cell partition wall.
An aircraft engine pylon having an upper fitting, an upper panel located below the upper fitting, a shear pin at least partially coupling the upper fitting and the upper panel, and tension fasteners at least partially coupling the upper fitting and the upper panel with the shear pin defining a shear force load path and the tension fasteners defining tension force load paths.
A latch assembly for a door is provided. The latch assembly includes a latch keep carried by one of the door and the surrounding structure and having a strike seat in which a strike may be removably received, a latch carried by the other of the door and the surrounding structure and having a catch configured to engage the strike, and a cable having a first portion secured to the other of the door and the surrounding structure and a second portion carrying the strike.
E05B 65/10 - Locks for special use for panic or emergency doors
B64C 1/14 - WindowsDoorsHatch covers or access panelsSurrounding frame structuresCanopiesWindscreens
E05C 17/36 - Devices for holding wings openDevices for limiting opening of wings or for holding wings open by a movable member extending between frame and wingBraking devices, stops or buffers, combined therewith by mechanical means with a movable bar or equivalent member extending between frame and wing comprising a flexible member, e.g. chains
E05C 3/12 - Fastening devices with bolts moving pivotally or rotatively with latching action
E05C 3/16 - Fastening devices with bolts moving pivotally or rotatively with latching action with operating handle or equivalent member moving otherwise than rigidly with the latch
E05C 17/16 - Devices for holding wings openDevices for limiting opening of wings or for holding wings open by a movable member extending between frame and wingBraking devices, stops or buffers, combined therewith by mechanical means with a movable bar or equivalent member extending between frame and wing consisting of a single rod pivoted only at one end and having an elongated slot
E05C 9/22 - Guides for sliding bars, rods, or cables
E05C 9/20 - Coupling means for sliding bars, rods, or cables
E05C 9/24 - Means for transmitting movements between vertical and horizontal sliding bars, rods, or cables, e.g. corner guides
A turbofan engine having a fan, a fan casing surrounding the fan and having a first radial flange, a thrust reverser having a second radial flange, and a band clamp coupling the first and second radial flanges to connect the thrust reverser and the fan casing. The band clamp may be a segmented band clamp.
F02K 1/70 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
F16B 2/08 - Clamps, i.e. with gripping action effected by positive means other than the inherent resistance to deformation of the material of the fastening external, i.e. with contracting action using bands
A turbofan engine having a thrust reverser having at least one movable control surface, movable to and from a reversing position where at least a portion of the bypass air flow is at least partially reversed, a thrust reverser actuation system having multiple actuators and a lockout mechanism movable between an inhibit condition, wherein movement of the multiple actuators is prevented, and a permit condition, wherein movement of the multiple actuators is permitted.
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
An aircraft engine assembly comprising a nacelle configured to surround the aircraft engine having an inlet open to ambient air and an annular acoustic panel provided within the nacelle. Sound emitted from the aircraft engine is attenuated by the annular acoustic panel. The annular acoustic panel comprises an open framework, made from a first material, forming a plurality of cells.
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
E04B 1/82 - Heat, sound or noise insulation, absorption, or reflectionOther building methods affording favourable thermal or acoustical conditions, e.g. accumulating of heat within walls specifically with respect to sound only
A system and method for ice protection of a component, wherein the system is adapted to be adhesively bonded to a surface of the component. The system includes a heating element layer, at least one thermally conductive adhesive layer that adhesively bonds a first side of the heating element layer to the component, an insulation layer, at least one thermally insulating adhesive layer that adhesively bonds a second side of the heating element to the insulation layer, an electrical bus bar adapted to provide a connection between a power supply and the heating element layer, and at least one temperature sensor.
A pylon structure for mounting an aircraft engine to a wing. The pylon structure comprises a torque box having a wing mount on the aft portion, a first engine mount on the fore portion and second engine mount on the aft portion.
A thrust reverser cascade having a frame and a body. The body comprises multiple layers formed by an additive manufacturing process where at least one of the layers is coupled to the frame.
B33Y 80/00 - Products made by additive manufacturing
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
A thrust reverser cascade having a frame and a body. The body comprises multiple layers formed by an additive manufacturing process where at least one of the layers is coupled to the frame.
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
B33Y 80/00 - Products made by additive manufacturing
A turbofan engine having a fan, a fan casing surrounding the fan and having a first radial flange, a thrust reverser having a second radial flange, and a band clamp coupling the first and second radial flanges to connect the thrust reverser and the fan casing. The band clamp may be a segmented band clamp.
A turbofan engine having a thrust reverser having at least one movable control surface, movable to and from a reversing position where at least a portion of the bypass air flow is at least partially reversed, a thrust reverser actuation system having multiple actuators and a lockout mechanism movable between an inhibit condition, wherein movement of the multiple actuators is prevented, and a permit condition, wherein movement of the multiple actuators is permitted.
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
An inner cowl structure for circumscribing at least a portion of a jet engine extending from an aircraft includes an apron configured to mount directly to the engine independent of the pylon and overly an upper portion of the jet engine, and an inner body configured to circumscribe a portion of the jet engine not circumscribed by the apron.
264870AB STRACTAn inner cowl structure for circumscribing at least a portion of a jet engine extending from an aircraft includes an apron comprising support hinges and/or railings for actuating cowl doors and configured to mount directly to the engine independent of the pylon and cover an upper portion of the jet engine, and an inner body configured to circumscribe a portion of the jet engine not circumscribed by the apron. The inner cowl body is at least one of hingedly or slidably coupled to the apron such that the resulting combination of the coupled apron and inner cowl body defines a hoop structure that is structurally independent of the pylon and completely circumscribes at least an axial portion of the jet engine.Date Recue/Date Received 2020-04-29
A system and method for ice protection of a component, wherein the system is adapted to be adhesively bonded to a surface of the component. The system includes a heating element layer, at least one thermally conductive adhesive layer that adhesively bonds a first side of the heating element layer to the component, an insulation layer, at least one thermally insulating adhesive layer that adhesively bonds a second side of the heating element to the insulation layer, an electrical bus bar adapted to provide a connection between a power supply and the heating element layer, and at least one temperature sensor.
A system and method for ice protection of a component, wherein the system is adapted to be adhesively bonded to a surface of the component. The system includes a heating element layer, at least one thermally conductive adhesive layer that adhesively bonds a first side of the heating element layer to the component, an insulation layer, at least one thermally insulating adhesive layer that adhesively bonds a second side of the heating element to the insulation layer, an electrical bus bar adapted to provide a connection between a power supply and the heating element layer, and at least one temperature sensor.
H05B 3/14 - Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor characterised by the composition or nature of the conductive material the material being non-metallic
A thrust reverser assembly and operation suitable for high-bypass turbofan engines. The thrust reverser assembly includes a translating cowl mounted to a nacelle of an engine and adapted to translate in an aft direction of the engine. The translating cowl has a radially inner wall that defines a radially outer flow surface of a bypass duct of the engine. The thrust reverser assembly includes blocker doors axially guided adjacent first ends thereof by a fixed structure and pivotally and slidably connected along lengths thereof to the inner wall of the translating cowl so that translation of the translating cowl in the aft direction causes each blocker door to move from a stowed position to a deployed position as a result of the blocker door sliding at its first end relative to the fixed structure and sliding along its length relative to the inner wall of the translating cowl.
Processes for fabricating polymer composite materials that contain a polymer matrix, reinforcement fabrics, and particles of a filler material. The processes include spraying the particles of the filler material on at least two articles that each comprise at least one of the reinforcement fabrics to form particle-laden articles. The particle-laden articles are stacked to form a stacked structure, and a resin present within the stacked structure is then cured to form a laminate polymer composite material. The process can be employed in the fabrication of at least a portion of an aircraft engine nacelle, for example, the inlet lip of a fan nacelle.
B29C 70/02 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising combinations of reinforcements and fillers incorporated in matrix material, forming one or more layers, with or without non-reinforced or non-filled layers
44.
POLYMER COMPOSITE MATERIALS AND PROCESSES THEREFOR
Processes for fabricating polymer composite materials that contain a polymer matrix, reinforcement fabrics (54), and particles of a filler material (52). The processes include spraying the particles of the filler material (52) on at least two articles (54,74) that each comprise at least one of the reinforcement fabrics (54) to form particle-laden articles (56,76). The particle-laden articles (56,76) are stacked to form a stacked structure (58,78), and a resin present within the stacked structure (58,78) is then cured to form a laminate polymer composite material. The process can be employed in the fabrication of at least a portion of an aircraft engine nacelle (34), for example, the inlet lip (42) of a fan nacelle (34).
A nacelle for housing an engine includes a fan cowl sized to cover at least a first axial portion of the engine. The engine includes an inlet end, an exhaust end, and an axis extending through the engine from the inlet end through the exhaust end. The fan cowl is coupled to an engine mounting pylon via a slider-type mounting system that includes at least one slider track assembly defining at least one slot therein. The at least one slot is configured to receive at least one fan cowl slider fitting.
A nacelle for housing an engine includes a fan cowl sized to cover at least a first axial portion of the engine. The engine includes an inlet end, an exhaust end, and an axis extending through the engine from the inlet end through the exhaust end. The fan cowl is coupled to an engine mounting pylon via a mounting assembly including at least one power drive system. The fan cowl is movable with respect to the engine along the axis toward at least one of the inlet end and the exhaust end.
A process and apparatus for producing perforated composite structures, such as acoustic skins suitable for aircraft engine nacelle and duct components. The process includes placing a mat member, a non-impregnated fabric member, and a resin film on a tool surface so that pins disposed on the mat member project through the fabric member and resin film to define holes therein. The fabric member is between the mat member and resin film, and the fabric member and resin film define a stack that conforms to the mat member and tool surface. A caul member is then placed on the stack so that apertures in the caul member are penetrated by the pins. The stack is heated to melt the resin film and cause molten resin to infuse the fabric member and yield a resin-infused fabric stack, after which the molten resin within the resin-infused fabric stack is at least partially cured.
An anti-icing system and method for an aircraft engine nacelle. The nacelle has an inlet lip that defines a leading edge of the nacelle and has a cross-sectional shape and oppositely-disposed exterior and interior surfaces. An anti-icing system contacts at least the inlet lip of the nacelle. The anti-icing system includes at least one heating element having a cross-sectional shape that conforms to the cross-sectional shape of the inlet lip and in which carbon nanotubes are oriented and arranged to conduct electrical current through the heating element. Passing an electrical current through the heating element causes Joule heating of the heating element and heating of the inlet lip by thermal conduction.
An anti-icing system for a nacelle of an aircraft engine. The nacelle has an inlet lip that defines a leading edge of the nacelle, and further has an annular-shaped cavity adjacent and delimited in part by an interior surface of the inlet lip. An anti-icing system is located within the cavity and includes a manifold with a cross-sectional shape that conforms to the interior surface of the inlet lip. A wall of the manifold faces the interior surface of the inlet lip, and air is conducted to the manifold to cause heating of the inlet lip via the manifold wall.
An anti-icing system for a nacelle of an aircraft engine. The nacelle has an inlet lip that defines a leading edge of the nacelle, and further has an annular-shaped cavity adjacent and delimited in part by an interior surface of the inlet lip. An anti-icing system is located within the cavity and includes a manifold with a cross- sectional shape that conforms to the interior surface of the inlet lip. A wall of the manifold faces the interior surface of the inlet lip, and air is conducted to the manifold to cause heating of the inlet lip via the manifold wall.
An anti-icing system (60,80) and method for an aircraft engine nacelle (50,70). The nacelle (50,70) has an inlet lip (56,76) that defines a leading edge of the nacelle (50,70) and has a cross-sectional shape and oppositely-disposed exterior and interior surfaces (58,59). An anti-icing system (60,80) contacts at least the inlet lip (56,76) of the nacelle (50,70). The anti-icing system (60,80) includes at least one heating element (62,82) having a cross-sectional shape that conforms to the cross- sectional shape of the inlet lip (56,76) and in which carbon nanotubes are oriented and arranged to conduct electrical current through the heating element (62,82). Passing an electrical current through the heating element (62,82) causes Joule heating of the heating element (62,82) and heating of the inlet lip (56,76) by thermal conduction.
A process and apparatus for producing perforated composite structures, such as acoustic skins suitable for aircraft engine nacelle and duct components. The process includes placing a mat member (24), a non-impregnated fabric member (14), and a resin film (16) on a tool surface (20) so that pins disposed on the mat member project through the fabric member and resin film to define holes therein. The fabric member is between the mat member and resin film, and the fabric member and resin film define a stack that conforms to the mat member and tool surface. A caul member (26) is then placed on the stack so that apertures in the caul member are penetrated by the pins. The stack is heated to melt the resin film and cause molten resin to infuse the fabric member and yield a resin-infused fabric stack, after which the molten resin within the resin-infused fabric stack is at least partially cured.
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
54.
Process and apparatus for producing composite structures
A process and apparatus for producing perforated composite structures, such as acoustic skins suitable for aircraft engine nacelle and duct components. The process includes placing a mat member, a non-impregnated fabric member, and a resin film on a tool surface so that pins disposed on the mat member project through the fabric member and resin film to define holes therein. The fabric member is between the mat member and resin film, and the fabric member and resin film define a stack that conforms to the mat member and tool surface. A caul member is then placed on the stack so that apertures in the caul member are penetrated by the pins. The stack is heated to melt the resin film and cause molten resin to infuse the fabric member and yield a resin-infused fabric stack, after which the molten resin within the resin-infused fabric stack is at least partially cured.
An anti-icing system includes a component surface having a composite structure including a composite layer, and at least one heating element formed within the composite layer, wherein the heating element is configured to provide a transfer of heat to the component surface.
B64D 15/00 - De-icing or preventing icing on exterior surfaces of aircraft
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
H05B 3/14 - Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor characterised by the composition or nature of the conductive material the material being non-metallic
H05B 3/34 - Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
A method of assembling a nacelle (200) for a gas turbine engine that includes an inlet end (201), an exhaust end (209), and an axis (x) that extends through the engine from the inlet end through the exhaust end is provided. The method includes providing a cowl (204) sized to cover at least a portion of the engine and coupling the cowl to the engine such that the cowl is slideable along the axis toward at least one of the inlet end and the exhaust end.
A nacelle assembly (12) and a method for assembling the same is provided. The nacelle assembly (12) includes an inner barrel (38) and an outer structure (40) comprising a highlight (42) and an outer aft section (44), wherein the highlight (42) is defined by a forward end of the outer structure (40), wherein the outer aft section (44) includes a point (45) defined by a maximum diameter (36) of the nacelle assembly (12), wherein the nacelle assembly extends at least between the highlight (42) and the point (45).
A process for producing through-holes in a sheet member to form a perforated article, such as an arcuate (non-planar) acoustic skin suitable for use in an acoustic panel of an aircraft engine nacelle. The process includes deforming a sheet member to have an arcuate shape with an arcuate surface, mounting and rotating the arcuate-shaped sheet member on a mandrel and then, while rotating the sheet member, directing an electron beam at the arcuate surface of the sheet member and deflecting the electron beam toward multiple locations on the arcuate surface to produce the through-holes through the sheet member in a defined hole pattern and thereby yield a perforated arcuate-shaped sheet member with holes having axes substantially normal to the arcuate surface. The holes are not subjected to elongation in a nonuniform manner after they are produced, and have the same transverse cross-sectional shape.
A method of assembling a nacelle for a gas turbine engine that includes an inlet end, an exhaust end, and an axis that extends through the engine from the inlet end through the exhaust end is provided. The method includes providing a cowl sized to cover at least a portion of the engine and coupling the cowl to the engine such that the cowl is slideable along the axis toward at least one of the inlet end and the exhaust end.
A nacelle assembly and a method for assembling the same is provided. The nacelle assembly includes an inner barrel and an outer structure comprising a highlight and an outer aft section, wherein the highlight is defined by a forward end of the outer structure, wherein the outer aft section includes a point defined by a maximum diameter of the nacelle assembly, wherein the nacelle assembly extends at least between the highlight and the point.
