Abstract: A structure to provide a variable nozzle for the fan air flow of a turbofan aircraft gas turbine engine with the nozzle being defined by the exit throat area defined by the aft edge of a trailing edge portion of the fan cowl and the core engine housing. A trailing edge cowl portion is slidably positioned in a rearwardly opening annular cavity in the aft end of the fan cowl for reciprocal axial translation between a deployed position to provide an enlarged exit throat area to provide enhanced performance of the aircraft engine during take off and climb to a cruising altitude and a stowed position to provide an optimum exit throat area for cruise condition of the engine. The trailing edge portion is sealably secured within the core cowl cavity to preclude any air leakage from the fan air stream of the fan duct around the trailing edge portion.

Abstract: A thrust reverser is disclosed for a turbojet engine having an outer cowling and an inner cowling forming a generally annular gas flow duct therebetween, the thrust reverser having at least one thrust reverser door pivotally attached to the outer cowling so as to pivot about a first stationary axis to move between a forward thrust position and a reverse thrust position, a thrust reverser panel pivotally attached to the inner cowling so as to pivot about a second stationary axis to move between a forward thrust position and a reverse thrust position, and a connector connecting the thrust reverser door and the thrust reverser panel such that when the thrust reverser door is in the reverse thrust position, the thrust reverser panel is in the reverse thrust position and when the thrust reverser door is in the forward thrust position, the thrust reverser panel is also in the forward thrust position.

Abstract: An improved target-type thrust reverser for use with an aircraft jet engine. Jet engines typically are housed in a nacelle and the engine terminates with an exhaust nozzle. The thrust reverser includes an upper door having a shape of a segment of a hollow frusto-conical member with an inner and outer surface, opposed longitudinal edges that taper towards each other, a forward semi-circular edge and a rearward semi-circular edge. The lower door is substantially identical. A pair of linkage arms pivotally support each of the upper and lower doors so that the doors are translatable between stowed and actuated positions. When in the stowed positions, the exterior surface of the doors form a part of the exterior surface of the engine nacelle. When in the actuated position, the doors are positioned rearwardly of the engine exhaust nozzle with their rearward edges in abutment.

Abstract: A thrust reverser system including a reverse thrust airflow duct (44) extending through an outer structure (46) of an aircraft engine aft nozzle (32) is disclosed. The reverse thrust duct (44) connects a nozzle exhaust duct (34) with the surrounding atmosphere (46). The duct (44) includes an inlet (72) and an outlet (70). A plurality of slats (50) are located within the reverse thrust duct to direct nozzle exhaust (38) from the nozzle exhaust duct (34) in an outward and/or forward direction. One or more outer doors (54) are formed near the outer structure exterior surface (90) for closing off the reverse thrust duct outlet (70) to the atmosphere. One or more inner doors (56) are provided for closing off the duct inlet (72) at the exhaust duct (34). An actuation system moves the inner and outer doors (56), (54) between open and closed positions. In the open position, the inner and outer doors (56), (54) are moved away from the duct (44) to open the airflow duct inlet and outlet.

Abstract: A thrust reverser for a turbojet engine is disclosed having a rear duct portion extending about a longitudinal axis with a rearmost edge lying in a plane extending at an oblique angle to the longitudinal axis. The thrust reverser also has a single thrust reverser baffle pivotally attached to the rear duct portion to move between a forward thrust position and a reverse thrust position. The single thrust reverser baffle has rearmost, planar edge which, in the forward thrust position, forms the downstream or rearmost end of the engine nozzle. The planar edge eliminates the aerodynamic losses of the known thrust reverser devices. The thrust reverser baffle also has an oblique edge that faces in a forward direction and is parallel to the rearmost edge of the rear duct portion when the baffle is in its forward thrust position.

Abstract: A thrust reverser for a turbojet engine is disclosed having a thrust reverser door and a thrust reverser panel pivotally attached to a housing so as to pivot in opposite directions about the same pivot axis. An epicyclic gear mechanism interconnects the housing, the thrust reverser door and the thrust reverser panel such that the thrust reverser door and the thrust reverser panels move in opposite directions about the common pivot axis when moving between their forward thrust and reverse thrust positions.

Abstract: The invention provides alternative flight control methods and structures which can prevent a crash of a passenger or a cargo aircraft under stall/spin and adverse flight conditions, failing Conventional ?aerodynamic! Flight Control ?CFC!, low landing speeds, asymmetric icing and partial loss of propulsion. That air-safety capability is provided by integrating roll-yaw-pitch engine-nozzle-nacelle thrust vectoring flight control ?TVFC! retractable/rotatable vane-doors, collectively operated in individual TVFC-sectors, with modified ?conventional! thrust-reversing ?TR! door-structures ?in one method!, or with novel retractable/rotatable TR vane-door sectorial structures ?a second method! to form various TVFC/CFC/TR systems. The methods and structures are intended for transport jets, except one configuration which is intended for turbo-prop transports. Another configuration replaces heavy and complex conventional TR doors and TR-nacelle-grids with an integrated, simpler and lighter TVFC/CFC/TR-systems.

Abstract: A thrust reverser is disclosed for a turbojet engine having a central axis and an exhaust nozzle wherein the thrust reverser has a plurality of deflectors pivotally attached to the turbojet engine so as to pivot about axes extending generally traverse to the central axis between a forward thrust position, wherein the plurality of deflectors form a downstream end of the exhaust nozzle, and a reverse thrust position wherein the deflectors deflect gases emanating from the engine to generate a reverse thrust. Each of the movable deflectors has a downstream trailing edge located such that all of the trailing edges of the deflectors lie in a common plane extending substantially transverse to the central axis.

Abstract: A gas turbine engine (10) includes a translating sleeve (38) disposed within a downstream portion of an outer nacelle (20). A variable area fan exhaust nozzle (30) is defined between the trailing edge (32) of the translating sleeve (38) and a conical core cowl (26) disposed radially inwardly of the outer nacelle (20) and spaced apart therefrom. The translating sleeve (38) translates downstream to cooperate with the decreasing diameter of the core cowl (26) to increase the area of the fan exhaust nozzle (30).

Abstract: A thrust reverser for a turbofan-type turbojet engine in which the axial length of the fan housing is less than that of the turbojet engine cowling such that the movable thrust reverser baffles may be attached to the jet engine cowling and moved to an extended position wherein the cold flow gases emanating from the cold flow exhaust duct are redirected to provide a thrust reversing force. The baffles are movably attached to the engine cowling by a plurality of linkrods forming a deformable parallelogram kinematic linkage. Each of the linkrods has opposite ends pivotally attached to the movable baffle and to the engine cowling, respectively.

Abstract: A thrust reverser with doors (5, 6) for an aircraft jet engine includes a radial stop which includes elements (16, 28) integral with the front end of each door (5, 6) and capable of interacting with mating elements (15, 3) that are integral with the engine. The radial stop is designed to prevent the deployment of the door in an advanced position of its axis of pivoting (P--P) and to allow this deployment in a retreated position of the axis of pivoting (P--P).

Abstract: The present invention relates to a thrust reverser for a turbojet engine having at least one thrust reverser door pivotally attached to a cowling so as to pivot about a first pivot axis between a forward thrust position, wherein the thrust reverser door closes a thrust reverse opening in the cowling, and a reverse thrust position in which the thrust reverse opening is opened. The thrust reverser door moves from the forward thrust position to the reverse thrust position about its pivot axis in a first pivot direction. The invention also includes a thrust reverser panel pivotally attached to the cowling so as to pivot about a second pivot axis between a forward thrust position and a reverse thrust position. In pivoting from the forward thrust position to the reverse thrust position, the thrust reverser panel pivots in a second direction about its axis, the pivoting direction of the thrust reverser panel being opposite to the pivoting direction of the thrust reverser door.

Abstract: A lock for a thrust reversal system of a gas turbine engine includes a pivotal locking member which is moved into the locking position by the engagement of a part of the thrust reversal system as the latter is moved to the inoperative position. The locking member is held in the locking position by a pin which engages within an opening formed in the locking member. The pin is biased by a spring and is movable by a hydraulic piston against the action of the spring to withdraw the pin from the opening.

Abstract: An aircraft propulsive power unit having an engine (20), a nacelle structure (12) which houses the engine (20) and which has an exterior low drag boundary surface (16) which is subjected to exterior air flow in a boundary layer adjacent the boundary surface (16) and an air flow disruption device (19) activatable to cause at a control location in the boundary surface disruption of exterior air flow in the boundary layer at the control location without reversal or deflection of engine thrust gaseous flow. Where the power unit is a turbofan and the nacelle structure includes a fan duct (22) with inner and outer fan duct walls (25,26) the air flow disruption device (19) is additionally or alternatively activatable to cause at a control location in the outer fan duct wall (26) disruption of air flow in the boundary layer at the control location.

Abstract: A fairing for aerodynamically covering the actuation mechanism of a variable area exhaust nozzle, comprising an upper and a lower longitudinally extending half-fairing member and having a generally arcuate cross-section, each of the half-fairing members having an upstream and a downstream end, and two longitudinal edges, the half-fairing members being pivotally connected to each other at a pivot point near the upstream edges and a connection along one of the longitudinal edges of each of said half-fairing members for interengaging the other of the half-fairing members and allowing the half-fairing members to rotate about the pivot point for changing the aerodynamic surface area of the fairing upon variation of the area of the exhaust nozzle.

Abstract: A thrust reverser for a turbofan-type turbojet engine is disclosed having an inner housing with a rear, downstream edge, a fan cowling extending around a portion of the inner housing so as to define a bypass gas flow duct, the fan cowling having a rear edge portion disposed forwardly of the rear edge of the housing. The thrust reverser also includes a thrust reverser flap assembly having a carriage slidably connected to the rear edge portion of the fan cowling so as to move in an axial direction between first and second positions, a thrust reverser flap having a rear flap edge disposed forwardly of the rear edge of the inner housing and pivotally attached to the carriage, and a link rod pivotally connected to the thrust reverser flap and to a stationary structure such as the inner housing.

Abstract: A turbofan, preferentially with separated-flows or short nacelle, comprises two thrust reversal doors normally housed in casings formed in the nacelle and located totally outside the inner enclosure of the nacelle. When a thrust reversal effect is sought, the doors are directed in the prolongation of the fan channel, behind the rear end of the nacelle. Thus, the doors are not submitted to the engine bypass air of the jet engine when the aircraft is in flight and the inner enclosure of the nacelle presents neither leak nor discontinuity and may be totally anti-noise treated.

Abstract: A thrust reverser with pivoting doors for a jet aircraft engine, with a system for security against in-flight deployment of a thrust reverser. The system has two independent locking assemblies, the first being a primary lock and the second being a safety lock that is positioned away from the first lock to avoid damage from a ruptured piece of the engine turbine disk. The first lock is hydraulically controlled and the second lock is electrically controlled and entirely independent, thus assuring an in-flight inadvertent deployment will not occur as a result from failures, faulty commands or inadequate maintenance.

Abstract: The reverser includes a partition (28) exhibiting openings (19) and separating the cavity (16) which exists, when the doors (2) are in the closed position, between the front part (7) of the internal panel (11) of the door and the stream of gaseous flow (15) flowing in direct jet mode through the jet pipe CA, thus overcoming the aerodynamic losses which result from the presence of this cavity.

Abstract: The present invention is a thrust reversing apparatus for diverting purely rearwardly directed air flowing through an engine nacelle to combined rearward-and-radially-outward flow, and then to a combination of various radially outward angles and forward flow, where in the latter states thrust reversal is effected. The apparatus includes parallel inner and outer air flow blocking members driven by actuators which are coupled to the blocking members for effecting synchronous movement. The inner member includes a first door having fixed vanes and a solid second door pivotably coupled to the first door. The inner member has a closed position in which the two doors are collinear, and various open positions in which the two doors are pivoted relative to one another. The outer member comprises an array of pivotable, parallel vanes, and has a closed position in which the vanes tightly overlap, and various open positions in which the vanes are pivoted out of contact with each other through various amounts of rotation.

Abstract: A thrust reverser comprised of two pivoting doors for engines mounted on an aircraft rear fuselage. For thrust reversal, the two pivoting doors are rotated into the mixed flow by two actuators, one actuator per door. On the extremities of each pivoting door, efflux flow turning devices are installed. These devices are removable boxes comprised of deflectors that can be oriented to turn the flow. Two boxes are required for each pivoting door.

Abstract: A thrust reverser is provided for both modulating and reversing bypass flow discharged from a fan through a bypass duct of a turbofan gas turbine engine. The reverser includes an aft cowl joined to a forward cowl and having an aft end surrounding a core engine to define a discharge fan nozzle of minimum flow throat area. The aft cowl is axially translatable relative to the forward cowl from a first position fully retracted against the forward cowl, to a second position partially extended from the forward cowl, and to a third position fully extended from the forward cowl. A plurality of cascade turning vanes are disposed between the forward and aft cowls, and a plurality of thrust reversing deflector doors are pivotally mounted to the aft cowl and bound the bypass duct. The deflector doors are selectively deployed from a stowed position corresponding with the first and second positions of the aft cowl for allowing unrestricted flow of the bypass flow through the fan nozzle.

Abstract: A thrust reverser for a fan-type turbojet engine is disclosed for use in a turbojet engine structure having an engine housing defining a primary gas flow duct and a fan housing generally coaxially arranged about the jet engine housing and defining therebetween a generally annular secondary gas flow duct. The thrust reverser has at least one thrust reverser door attached to the fan housing by a forward linkrod pivotally attached to a forward portion of the thrust reverser door and pivotally attached to the fan housing, and a rear linkrod pivotally attached to a rear portion of the thrust reverser door and also pivotally attached to the engine housing. The linkrod attaching mechanism enables the thrust reverser door to be movable between a forward thrust position wherein the door outer surface is substantially flush with an outer surface of the fan housing and a reverse thrust position wherein the thrust reverser door redirects the gases flowing through the secondary gas flow duct to provide a reverse thrust.

Abstract: A thrust reverser system for jet engine comprising a tailpipe, clamshell doors and actuators, wherein the tailpipe and clamshell doors may be corrugated, the corrugations mating, the actuators may be situated out of the external free air flow, the doors may be stowed out of contact with internal engine gas flow and that may include a tailpipe aft fairing having a movable section and a pressure booster system for the actuators.

Abstract: A thrust reverser synchronization shaft lock system that includes a sync lock control valve (50) and two hydraulically controlled sync locks (60) attached to the synchronization shafts (5) of a jet engine thrust reverser system, is disclosed. The thrust reverser system further comprises an isolation valve (45), a directional control valve (47), a plurality of actuators (19), and synchronization shafts (5). The sync locks (60) are capable via the synchronization shafts (5) of preventing the actuators (19) from deploying the thrust reversers of the jet engines. The sync locks (60) remain in a locked state until an independent control signal sent from the flight deck positively instructs the sync lock control valve (50) to unlock the sync locks (60), ensuring that the unlocking of the sync locks (60) corresponds to a valid thrust reverser deploy signal.

Abstract: A ducted fan turbine engine includes a nacelle and an outer discharge nozzle mounted on an aircraft wing by a pylon. The nacelle includes to parts which are hinged to the pylon for pivoting movement between an open position and a closed, operational position. Each nacelle part contains a bypass air duct. Spaced spigot locators and blade locators are positioned at the forward edge of the discharge nozzle and spigots and blades are correspondingly located round the rear edge of the nacelle parts. The locators and their corresponding spigots and blades are arranged so that on closure of the nacelle parts they engage one another and transmit the flight loads through the nacelle.

Abstract: A ducted fan gas turbine engine is provided with a thrust reverser which comprises doors which deflect the fan exchaust efflux. Each door is pivotably attached at its downstream end to a common support member by a frangible coupling. In the event of an unintended in-flight deployment of the thrust reverser, the frangible couplings fracture to permit the doors to move to a non-thrust deflecting position.

Abstract: A hush kit for jet aircraft engine includes a respaced inlet guide vane to provide an increased space between the fixed guide vanes of the inlet and the rotating fan blades of the fan connected to the core engine, a mixer for mixing hot exhaust gas from the core engine with colder bypass fan air, and an acoustic barrel to reduce the noise generated by the mixed air flowing through the thrust reverser downstream of the core engine. The acoustic barrel includes an outer imperforate layer, an inner perforate layer and a multi-cellular core sandwiched therebetween. The ratio of the thickness of the multi-cellular core to the open area defined by the holes in the inner perforate skin of the acoustic barrel is designed to reduce noise of a particular frequency range generated by the aircraft engine. In combination, each of the components of the hush kit described herein reduce noise generated by the jet engine for compliance with Federal Aviation Administration noise reduction requirements.

Abstract: The invention is a shroud for a reversible thrust fan, the shroud having a inlet duct and an exhaust nozzle with the fan located there between. In general terms, the shroud includes a system for increasing the efficiency of the exhaust nozzle when acting as an inlet duct when the fan is providing reverse thrust. The system comprising a plurality of auxiliary inlet duct systems spaced about the circumference of the exhaust nozzle in proximity to the rear end thereof, the auxiliary inlet duct systems extending from the exterior surface of the exhaust nozzle to the interior surface thereof. The auxiliary inlet duct systems are movable from a closed position to an open position wherein air can be drawn from the exterior surface of the exhaust nozzle to the interior thereof when the fan is providing reversed thrust.

Abstract: The invention concerns a dual-flow turbine engine equipped with a thrust reversal system and at least one device for restricting the annular channel for the ejection of cold gases. According to the invention, each restriction device, consisting of a fitting (7) and a shutter (8) pivoting with respect to the said fitting, has sealing means disposed between the said shutter and fitting, adapted for defining at least one airtight chamber (12, 13) between these last two, each fitting (7) having, in line with each chamber, at least one orifice. Furthermore, elastic means are arranged so as to act on the shutter (8) in such a way as to produce an initial release of the latter. These devices aim to guarantee the holding of the shutter (8) in its closed position, where it is clamped against the fitting (7), during flight, whilst ensuring the opening of this shutter after landing, under the effect of the elastic means.

Abstract: Thrust reverser blocker doors which include a syntactic film to protect the blocker doors from heat is disclosed. The blocker doors include first and second spaced layers of composite material. A first adhesive layer is disposed on the second layer and is used to bond the syntactic film to the second layer of composite material. To prevent surface erosion a protective layer can be bonded to the syntactic film by a second adhesive layer.

Abstract: A thrust reverser for use with a jet engine comprising a pair of symmetrical thrust reverser door, each of the doors being pivotally attached to the jet engine so as to be pivotally movable between reversing and non-reversing positions, each of the doors having a scarfed trailing edge portion so that in the reversing position, the trailing edge portions of the doors are in abutting contact, the thrust reverser doors comprising an inner skin and an outer skin, with the inner skins forming a portion of the jet flow boundary extending from said jet engine pipe to the trailing edge of the door, a pair of half-shells, one being associated with and surrounding the trailing edge portion of each of the doors, the half-shells each comprising inner and outer skins and the inner skin of the half-shells forming the jet flow boundary from the trailing edge of the doors to the exhaust outlet.

Abstract: The invention relates to thrust reversers with doors for a jet engine. The upstream edge of the reverser doors is equipped with a deflecting structure consisting of a rigid frame (10, 12, 13) fixed to the door and delimiting a space (14) capped by a stiffener (15). In the space (14) are housed vanes (16) with aerodynamic profile in the form of a wing which is inclined by an angle a with respect to the plane of the frame (10, 12, 13) in order to orient laterally the flow of the gases which is diverted by the reverser. This arrangement makes it possible to reduce, or even to prevent, re-ingestion by the engine of the diverted gases, or interference of the latter with the wing structure of the aircraft.

Abstract: A jet exhaust pipe for aircraft jet engines comprising a fixed structure, a pair of movable shells surrounding the gas discharge end of the fixed structure, the shells being connected to the fixed structure on opposite sides thereof, a pair of thrust reverser doors pivotally connected to the fixed structure, and an actuator for moving the thrust reverser doors and the shells between a first, non-reversing position and a second, reversing position, wherein the shells form a portion of the gas flow surface of the jet exhaust pipe in the first position, and are out of the gas flow in the second position.

Abstract: A thrust reverser system for a turbine engine of the type having a central relatively hot gas generator nozzle conducting a core flow and a relatively cold duct conducting a fan flow and surrounding the hot flow, a pair of thrust reverser door, each of the doors being pivotally mounted on an axis which is substantially diametrically positioned with respect to the exhaust nozzle of the engine so as to pivot between a stowed position in which the doors are out of the direct path of exhaust from the engine and a deployed position in which the doors are in the path of the engine exhaust for deflecting the exhaust and creating a braking thrust, a flow modifying arrangement acting on the hot gas generator nozzle for simultaneously decreasing the total pressure of the core flow and increasing the total pressure of the fan flow by increasing the area of the hot gas generator nozzle at the discharge end thereof and moving the boundary between the hot gas and cold gas flows radially outwardly.

Abstract: An improvement made to jet-engine thrust reversers and, more particularly, to reversers called tilting-door reversers. The doors are equipped, on their upstream portion, with a flow-deflecting overlay 90 which, in the open-door position, is in a position close to a line PM parallel to the axis of the engine 1, the overlay making with the inner door skin an angle B greater than 90.degree., preferably between 105.degree. and 110.degree.. The invention is more particularly applicable to dual-flow engines.

Abstract: An engine has a shroud which surrounds one of a propfan and a propeller having blades. The shroud has a variable geometry. A direction of the air flow inside a duct of the shroud is reversible via an adjustment of the blades for the reversal of the thrust of the engine. A separately movable nozzle ring forms a rearward end of the shroud. The nozzle ring is axially displaceable to an extent such that its trailing edge forms wherein air flow is promoted around the end of the shroud.

Abstract: An aircraft bypass turbofan engine subassembly for ground deceleration (e.g., thrust reversal). A fan nacelle has a through passageway connecting its inner exterior surface and outer exterior surface. A passageway end is located on the inner exterior surface aft of the aft-most row of fan rotor blades. A row of pivotable fan outlet guide vanes is located radially between the fan and core nacelles and longitudinally aft of the flow splitter and the passageway end. Apparatus is provided to pivot the vanes to block passage of bypass air and to open the passageway for ground deceleration.

Abstract: A thrust reverser for a long duct mixed flow fan jet engine having a nacelle formed by a fixed forward structure surrounding the fan, a rear fixed structure and a translatable inner and outer cowl therebetween, the nacelle surrounds the engine and forms a long by-pass duct therewith, a common actuator fixed to the translatable cowls to simultaneously displace them over the rear structure, blocker doors coupled to the inner translating cowls for deployment during thrust reversal into the by-pass duct into a blocking position to divert the airflow through the cascades placed into an opening uncovered when the translatable cowls are axially displaced.

Abstract: A jet engine for an aircraft has a thrust reverser including one or more doors which define at least a part of the throat of the engine's nozzle. The engine further includes a latch mechanism for retaining the doors in a stowed position. The doors may be deployed for reversal of engine thrust, but are also capable while stowed of being pivoted in a limited way to change the cross-section area of the throat of the nozzle.

Abstract: A cascade type fan jet engine thrust reverser system. A radially arranged opening is provided along the aft edge the of fan cowl of a fan jet engine. Cascade sets each including a plurality of turning vanes are fixedly positioned in each opening. A blocking door and an actuating linkage system are positioned flush with the inner wall of the fan cowl adjacent to the openings, with the linkage system substantially out of the air flow path during normal engine operation. A sleeve like member covers the outer surface of the cascade sets and at least partially covers the stowed linkage system. When reverse thrust is desired, the sleeve is caused to translate aft, uncovering the cascade set and linkage. The linkage system is caused to move the blocking doors to positions where air flow through the fan cowl is substantially blocked and diverted out through the cascade sets in an outward and reverse direction. Upon completion of thrust reversal operation, these components are returned to the stowed position.

Abstract: A thrust reverser for a turbofan-type turbojet engine assembly is disclosed having a deflector defining an upstream edge of a reverse thrust opening formed in the turbofan housing so as to control the direction and shape of the gases passing through the reverse thrust opening. The deflector has a deflector edge portion defining a deflector edge wherein the curvature of the deflector edge portion, as measured in a longitudinal radial plane passing radially through a longitudinal axis of the engine, varies in a direction from one side of the reverse thrust opening to the opposite side of the opening. The curvature of the deflector edge portion is defined as being positive when the center of curvature of the deflector edge portion lies radially outwardly of the deflector and is defined as being negative when the center of curvature of the deflector edge portion lies radially inwardly of the deflector.

Abstract: A thrust reverser for a turbofan engine is disclosed in which the pressure of the gases passing through the cold flow air duct act on a downstream segment of the thrust reverser door so that the door is normally biased toward its closed, forward thrust position. This positively eliminates any possibility of the thrust reverser door inadvertently opening into its reverse thrust position. The thrust reverser according to the present invention is thus self-closing regardless of the position and/or functioning of the typical closing and locking mechanisms. The thrust reverser door assembly has internal and external doors separately pivotally attached to the turbofan housing so as to each be movable between closed, forward thrust positions, and opened, reverse thrust positions. A single actuating mechanism may be utilized to move both of the internal and external doors between their respective closed and opened positions.

Abstract: In a nozzle reverser assembly for a gas turbine engine, a swinging vane pack reverser is provided in place of the prior art array of cascade vanes in reverser ports of such engines. The present invention includes a door flap that is hinged on the aft side of a reverser port, which door flap has sidewalls attached thereto that extend into such port. The reverser assembly of the invention also includes a vane pack that is hinged at the forward end of such reverser port and has a roller attached its aft end, which roller engages a track within the door flap for sliding engagement therewith. Forward of the vane pack hinge, a boundary layer trip fence is hinged to the engine housing. In operation, air flow directed into the reverser cavity, e.g. by a convergent flap, is guided further by the above door flap and its sidewalls.

Abstract: A thrust reverser for a turbofan engine having a very high bypass ratio is disclosed having a plurality of baffles pivotally attached to a gas turbine engine housing so as to extend into a cold flow air stream emanating from the turbofan exit. The baffles are pivotally attached to the gas turbine engine housing and may be moved into extended, thrust reversing positions in which some of the baffles form a greater angle with the gas turbine engine housing than the remainder of the baffles. By moving the baffles located generally on opposite upper and lower portions of the gas turbine engine housing to the greater angles, the requisite thrust reversing force may be developed while at the same time minimizing the overall vertical dimension of the engine housing so as to provide the maximum amount of ground clearance for the turbofan engine. Secondary baffles are provided between the main baffles to close open spaces between the main baffles.

Abstract: A fail-safe pivot door-type aircraft turbine engine thrust reverser which includes a plurality of pairs of pivoting doors on the blocker and deflector sides of openings in a fan jet nacelle. The doors form a flush surface along the nacelle exterior and the fan duct flow path when stowed during normal engine operation in flight. When the doors are deployed in thrust reversing mode, an extensible actuator causes them to translate aft in the opening, with one end of the blocker door moving to at least partially block airflow through the duct and divert it out along the door through the opening uncovered by door deployment. The deflector door pivots outwardly to extend the door length and further direct airflow out and forward along the outside of the nacelle. Upon initiation of deployment, a cooperating pin and track assembly causes the door to initially translate inwardly, then rearwardly, after which the pivoting action begins.

Abstract: A one-piece composite material torque box for the thrust reverser assembly of a jet engine. The torque box is made up of three composite material subassemblies, a generally planar flange subassembly, a tubular torque tube subassembly, and a cap subassembly. The flange subassembly is configured to transmit tension loads from the cascades of the reverser assembly to the V-blade ring which engages the engine, and the fibers in the composite material are aligned with these load paths. The torque tube subassembly is mounted to the flange subassembly, and is configured to transmit torsion loads from the actuators of the reverser assembly to the upper and lower latch members of the engine assembly; the fibers of the composite material therein are aligned at 45.degree. angles to the tube axis, so as to be in alignment with paths of the tension/compression components of the torsion loads.

Abstract: A thrust reverser for use with fan jet type aircraft gas turbine engines. A ring around the aft edge of the nacelle is translatable aft to uncover a series of cascade sets, each of which includes a plurality of turning vanes that direct air passing through the cascades in a reverse direction. The actuation system includes a hydraulic cylinder or the like in islands between cascade sets. A blocker door assembly is positioned within the nacelle adjacent to each cascade set during normal engine operation, with the blocker door forming a portion of the inner streamlined wall of the nacelle. The forward end of the door is hingedly secured to a cascade door support and does not move during deployment of the ring. The aft end of the door is hingedly secured to a link, the other end of which is secured to the moving ring. As the ring is translated aft, the door pivots to a position blocking at least part of the air flow through the duct between nacelle and engine core and directs it outwardly though the cascade set.

Abstract: A thrust reverser for jet engines comprising a pair of thrust reverser doors pivotally mounted on an axis which is substantially diametrically positioned with respect to the exhaust nozzle of a jet engine so as to pivot between a stowed position in which the doors are out of the direct path of exhaust of the engine but subjected to the static pressure of the jet engine over substantially the entire length of the doors, and a deployed position in which the doors are in the path of the engine exhaust for deflecting the exhaust and creating a braking thrust, a latch mechanism for securing the doors in the stowed position, a suitable port for directing a portion of the static pressure of the jet engine toward the doors for exerting the static pressure against the doors, an actuator for releasing the latch mechanism so that the doors may pivot to the deployed position, a valve operatively associated with the latch mechanism for relieving at least a portion of the static pressure of the jet engine acting on an upst

Abstract: A thrust reverser system for fan jet type aircraft gas turbine engines using a rack and pinion arrangement for moving blocker doors between the stowed and deployed positions. Blocker doors fill a plurality of circumferentially arranged openings.