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 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
2.
ACOUSTIC LINER AND METHOD OF CONSTRUCTING AN ACOUSTIC LINER
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 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets de résonance
A turbine engine having an engine core, an inner cowl radially surrounding the engine core, an outer cowl radially surrounding the inner cowl and spaced from the inner cowl to form an annular passage between the inner and outer cowls that defines a nozzle, at least one control surface provided on the inner cowl and movable between a retracted position, where the nozzle has a first cross-sectional area, and an extended position where the nozzle has a second cross- sectional area that is less than the first cross-sectional area and an actuator operably coupled to the control surface and configured to move the control surface to control the cross-sectional area of the nozzle.
F02K 1/12 - Variation de la section utile de la tubulure de jet ou de la tuyère au moyen de volets pivotants
F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c.-à-d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p. ex. du type à double flux comprenant une soufflante avant
An aircraft comprises an energy output component (EOC) outputting waste energy. An energy recovery unit (ERU) is operably coupled to the EOC to convert the waste energy into one of electrical energy or mechanical energy. An energy storage unit (ESU) is operably coupled to the ERU to store the one of electrical energy or mechanical energy recovered from the waste energy.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
A fluid supply assembly having a conduit (18) through which a fluid may be supplied. A thermal shut-off (30) may be provided to control the supply of fluid through the conduit (18) in response to an environmental temperature condition.
F16K 31/00 - Moyens de fonctionnementDispositifs de retour à la position de repos
F16K 17/38 - Soupapes ou clapets de sûretéSoupapes ou clapets d'équilibrage fonctionnant sous l'action de circonstances extérieures, p. ex. un choc, un changement de position d'une température excessive
A turbofan engine assembly (10) having a turbine engine (16) and a nacelle (20) that surrounds at least a portion of the turbine engine (16) to define an annular bypass duct (22) that defines a forward-to-aft bypass air flow path. The turbofan engine assembly (10) further comprises a fixed portion (33) and a movable portion (27) which is movable in a direction along the bypass air flow path to an opened position that defines a thrust reversing outlet (28) through which at least a portion of the bypass air flow may be directed. At least one actuator (38) moves the movable portion (27) to the opened position.
A pylon structure (10) for mounting an aircraft engine to a wing. The pylon structure comprises a torque box (12) having a wing mount (14) on the aft portion, a first engine mount (16) on the fore portion and second engine mount (18) 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.
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
B29C 67/00 - Techniques de façonnage non couvertes par les groupes , ou
A latch assembly (10) for a door (12) is provided. The latch assembly (10) includes a latch keep (20) carried by one of the door (12) and the surrounding structure (14) and having a strike seat (22) in which a strike (24) may be removably received, a latch (30) carried by the other of the door (12) and the surrounding structure (14) and having a catch (32) configured to engage the strike (24), and a cable (34) having a first portion (36) secured to the other of the door (12) and the surrounding structure (14) and a second portion (38) carrying the strike (24).
E05C 17/02 - Dispositifs pour tenir les battants dans une position d'ouvertureDispositifs pour limiter l'ouverture des battants ou pour tenir les battants dans une position d'ouverture par une pièce mobile disposée entre le battant et le dormantDispositifs de freinage, butées ou tampons combinés avec ces dispositifs par des moyens mécaniques
B64C 1/14 - FenêtresPortesTrappes d'évacuation ou panneaux de visiteStructures de cadres environnantsVerrièresPare-brise
An aircraft engine pylon comprises an upper fitting, an upper panel located below the upper fitting, a shear pin at least partially coupling the upper fitting to the upper panel, and many tension fasteners at least partially coupling the upper fitting to the upper panel, wherein the shear pin defines a shear force path and the tension fasteners define tension force load paths.
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 process for producing resin-impregnated laminate composite structures that comprise a closed-cell core between resin-impregnated fabric layers, and preliminary and composite structures formed by such a process. The process includes stitching a roving in a preliminary structure that includes the core so as to structurally reinforce the core. The roving passes through through-holes in the core and traverses opposite outer surfaces of the preliminary structure. The outer surfaces of the preliminary structure traversed by the roving may be defined by outer surfaces of the core, or the preliminary structure may further include two or more fabric layers on outer surfaces of the core such that the core is between the fabric layers, the roving passes through one or more fabric layers, and at least one of the outer surfaces of the preliminary structure and traversed by the roving is defined by a fabric layer.
A process and apparatus for producing perforated composite structures, such as acoustic skins suitable few aircraft engine nacelle components. The process includes placing at least one mat member, a non-impregnated fabric member, and a pad member on a tool surface so that pins disposed on the mat member project through the fabric member to define holes therein, the fabric member is between the mat and pad members, and the mat, fabric and pad members yield a non-impregnated stack that conforms to the tool surface. The fabric member is then infused with a resin to yield a resin-impregnated fabric and the resin within the resin-impregnated fabric is partially cured, after which the partially-cured resin-impregnated fabric is removed from the tool surface and from between the mat and pad members. A post cure of the partially-cured resin-impregnated fabric can then be performed to yield composite structure with the holes.
B29C 70/44 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant une pression isostatique, p. ex. moulage par différence de pression, avec un sac à vide, dans un autoclave ou avec un caoutchouc expansible
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
B29C 70/48 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant des moules opposables, p. ex. pour déformer des préimprégnés [SMC] ou des "prepregs" avec une imprégnation des renforcements dans le moule fermé, p. ex. moulage par transfert de résine [RTM]
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.
An anti-icing system (200) includes a component surface (202) having a composite structure including a composite layer (214), aid at least one heating element (220) formed within the composite layer (214), wherein the heating element (220) is configured to provide a transfer of heat to the component surface (202).
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.
Perforated composit structure and method therefore including: (a) forming a laminate structure including a plurality of uncured prepreg sheets (30), wherein the laminate structure comprises an initial substantially planar configuration; (b) subjecting the laminate structure to suitable first curing conditions (34) to provide a partially cured laminate structure while maintaining the substantially planar configuration; (c) providing the.partially cured laminate structure with a plurality of perforations (44) to provide a partially cured and perforated laminate structure (42); (d) shaping the partially cured and perforated laminate structure; and (e) subjecting the partially cured and perforated laminate structure (42) to second curing conditions at least partially simultaneously with or after step (d) to provide a shaped and finally cured laminate structure.
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
B29C 70/42 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
18.
MOLDING PROCESS FOR CORE-CONTAINING COMPOSITES AND COMPOSITES FORMED THEREBY
A process for producing composite structures (10) having a core (14) between resin- impregnated composite layers (18), and composite structures formed by such a process. The process uses non-impregnated fabric layers (18) and a core layer (14) placed on a mold (34) such that the core layer is between at least two fabric layers, a first of which is disposed between the mold surface and a first surface of the core layer, and a second of which is disposed at a second surface of the core layer. The second fabric layer is then infused with a resin, which flows through holes in the core layer into the first fabric layer, such that the first and second fabric layers are uniformly impregnated with the resin and the core layer is not. The resin is then cured to cause the impregnated first and second fabric layers to bond to the core layer.
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
B29C 70/44 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant une pression isostatique, p. ex. moulage par différence de pression, avec un sac à vide, dans un autoclave ou avec un caoutchouc expansible
B29C 70/48 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant des moules opposables, p. ex. pour déformer des préimprégnés [SMC] ou des "prepregs" avec une imprégnation des renforcements dans le moule fermé, p. ex. moulage par transfert de résine [RTM]
B29C 70/08 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement comprenant des combinaisons de différentes formes de renforcements fibreux incorporés dans une matrice, formant une ou plusieurs couches, avec ou sans couches non renforcées
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