Abstract: An exhaust nozzle includes an exhaust duct with an outlet and a row of radial apertures upstream therefrom. A radial frame surrounds the duct upstream from the apertures. A row of flaps are hinged to the frame to selectively cover and uncover the apertures for controlling exhaust flow discharged therethrough. An arcuate unison bar surrounds the duct adjacent to the frame and includes circumferentially spaced apart cam followers engaging corresponding cams affixed to the flaps. An actuator is joined to the bar for selective rotation thereof between opposite first and second directions to pivot open and closed the flaps atop the apertures.

Abstract: A thrust reverser system for jet engine comprising a tailpipe, Square/trapezoidal clamshell doors and actuators, wherein the tailpipe and clamshell doors may be corrugated, the corrugations can be 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 tail pipe a fairing having a movable section.

Abstract: An exhaust nozzle includes an outer duct surrounding an inner duct. The inner duct includes a main outlet, and a row of apertures spaced upstream therefrom. The outer duct includes a row of intakes at a forward end, an auxiliary outlet at an aft end, and surrounds the inner duct over the apertures to form a bypass channel terminating at the auxiliary outlet. A row of flaps are hinged at upstream ends to selectively cover and uncover the apertures for selectively bypassing a portion of exhaust flow from the inner duct through the outer duct in confluent streams from both main and auxiliary outlets. When the flaps cover the apertures, the intakes ventilate the bypass channel and discharge flow through the auxiliary outlet.

Abstract: The invention provides a locking system on a cascade thrust reverser for a bypass turbojet, the reverser (20) comprising guide means (60) for the movable parts (50), and the guide means (60) comprising rails (64) attached to the movable parts (50) and tracks (62) attached to the longitudinal members (36). According to the invention, the locking system (80) comprises locks (82) located at the end (62a) of each track (62) in the opening direction (52), each lock comprising a bolt (110) capable of preventing the rail (64) moving in the opening direction (52).

Abstract: A fan thrust reverser includes a nacelle having radially outer and inner skins. An outer door is disposed in the outer skin, and mounted to the nacelle at a hinge joint. A toggle link is pivotally joined between the outer door and the nacelle for latching stowed the outer door in the nacelle. An actuator is provided for rotating the outer door about the hinge joint for deploying the door outwardly from the nacelle and toggling off the toggle link, and stowing inwardly the outer door upon reverse rotation thereof and toggling on the toggle link to latch the door stowed in the nacelle.

Abstract: A thrust reverser for a turbofan engine having an air duct defined radially inwardly by a wall around the turbofan engine and radially outwardly in part by a fan cowl of the engine. A bulkhead is adapted to be mounted on the fan cowl having a shaped surface defining an upstream wall. A translating cowl is supported for movement axially between a closed position substantially adjacent the bulkhead and an open position spaced axially apart from the bulkhead so as to form an outlet for discharge of air from the air duct. The translating cowl has a first wall and a kicker plate defining a shaped surface. The kicker plate and/or the bulkhead may have a dimension which varies at different radial locations about a circumference of the translating cowl to selectively control the forward component of velocity of the air discharged from the air duct. A plume control device may extend longitudinally across the outlet to divide the air discharged from the air duct into a plurality of plumes.

Abstract: A jet engine nozzle having a pair of pivoting extension arms and a pair of pivoting shells connected to a jet pipe is provided. The first extension arm is pivotally connected to the jet pipe at a first location, while the second extension arm is pivotally connected to the jet pipe at a second location. Each shell is pivotally connected at both the first and second locations. An axis of rotation associated with the first location is coaxial to an axis of rotation associated with the second location. Independent actuation means are provided to rotate the extension arms and the shells, thereby enabling adjustment of the thrust-vector angle or the exhaust area of the nozzle.

Abstract: A lock assembly for a thrust reverser system that prevents thrust reverser deployment when the thrust reversers are in the stowed position, but does not prevent thrust reverser movement, in either the deploy or stow directions, when the thrust reversers are out of the stowed position and the lock assembly is in the locked position.

Abstract: A thrust reverser for a jet engine of a mobile platform. The thrust reverser includes a hinge beam defining a first track and a latch beam defining a second track. The thrust reverser also includes at least one cascade support ring having an upper end portion and a lower end portion. A first fitting is disposed at the upper end portion of the cascade support ring. The first fitting includes an engagement portion slidably positioned within the first track. A second fitting is disposed at the lower end portion of the cascade support ring. The second fitting includes an engagement portion slidably positioned within the second track.

Abstract: A fan thrust reverser includes an outer louver door joined to an inner blocker door by a drive link in a bifold configuration. The louver door is stowed closed in the outer skin of a fan nacelle outside the blocker door stowed closed in the inner skin of the nacelle. An actuator deploys open the louver and blocker doors, with the louver door extending radially outwardly and the blocker door extending radially inwardly for reversing fan exhaust flow during thrust reverse operation.

Abstract: An aircraft having a propulsive power unit supported in a fuselage mounted configuration and including an engine and a nacelle structure housing the engine. The nacelle structure is provided with upper and lower displaceable nacelle portions, such as thrust reverser cowls and fan cowl doors which are displaceable between closed dispositions which they occupy during operational conditions of the aircraft and open dispositions which they take up to provide access to engine components. The upper and lower nacelle portions are so mounted as to be displaceable to their open and closed dispositions in movements in which one is assisted by gravitational force and the other is displaced against gravitational force. A force transfer mechanism is provided for transfer during opening and closing movements of the nacelle portions of gravitational force assisting displacement of one of the nacelle portions to assist in displacement of the other nacelle portion being displaced against gravitational force.

Abstract: An external jet nozzle mixer (20) includes identically formed lobes (48), equal in number those of the internal mixer (42). External mixer (20) works with internal mixer (42), further to mix the engine internal bypass flow with the internal jet engine core flow, to level the disparate exhaust flow velocities, to reduce the peak velocities from the jet engine core and increase the lower bypass velocities of the engine internal bypass flow, and thereby to reduce noise. The internal lobe contours act as lifting flutes, causing mixing of the primary hot and cold flows before exiting the nozzle. The external lobe contours act as venturi chutes, accelerating the cooler ambient air secondary flow. The lobes thus act collectively as an injector to force the cooler ambient secondary flow into the previously mixed primary flow as it exits the nozzle. Also obtained is an increased thrust efficiency and a consequently decreased fuel consumption and engine emissions.

Abstract: A thrust reverser includes forward and aft louvers pivotally mounted in a compartment defining a flow tunnel through the outer and inner skins of a fan nacelle. An aft flap is integrally joined to the aft louver for rotation therewith. A unison link joins together the forward and aft louvers. And, an actuator is joined to the louvers for rotation thereof between a stowed position in which the louvers and flap are closed in the nacelle skins and a deployed position in which the louvers and flap are pivoted open from the skins.

Abstract: A target type thrust reverser is provided for reversing the thrust of jet engines, particularly on aircraft. The thrust reverser preferably has a plurality of doors that occupy a stowed position about the nozzle of the jet engine until deployed. In the stowed position, the doors are out of the exhaust stream of the jet engine. The doors are mounted to pivot joints on the rear portions of the doors. To deploy the thrust reverser, actuators connected to the pivot joints cause the pivot joints to translate linearly aft, and link rods attached to the forward portions of the doors cause the doors to pivot about the sliding pivot joints. In this manner, the distance between the doors and the engine exhaust nozzle is minimized during deployment, which enables significant weight savings due to reduced loads and fewer parts. A novel lock is also provided for simultaneously locking the thrust reverser doors and the actuators.

Abstract: A thrust reverser for a jet engine of a mobile platform. The thrust reverser includes a hinge beam defining a first track and a latch beam defining a second track. The thrust reverser also includes at least one cascade support ring having an upper end portion and a lower end portion. A first fitting is disposed at the upper end portion of the cascade support ring. The first fitting includes an engagement portion slidably positioned within the first track. A second fitting is disposed at the lower end portion of the cascade support ring. The second fitting includes an engagement portion slidably positioned within the second track.

Abstract: The invention provides a locking system on a cascade thrust reverser for a bypass turbojet, the reverser (20) comprising guide means (60) for the movable parts (50), and the guide means (60) comprising rails (64) attached to the movable parts (50) and tracks (62) attached to the longitudinal members (36).

Abstract: A thrust reverser system that includes one or more power drive units operable to supply a drive force. The power drive unit includes a motor and at least two output sections, each operably coupled to transmit the drive force to the thrust reverser movable components. Each of the output sections is operable to decouple the motor from associated thrust reverser movable components upon a torque magnitude being reached in the output section. A deadband coupler is provided to couple the first and second output sections together a time period after the torque magnitude is reached in one of the output sections.

Abstract: A lock assembly for a thrust reverser system that prevents thrust reverser deployment when the thrust reversers are in the stowed position, but does not prevent thrust reverser movement, in either the deploy or stow directions, when the thrust reversers are out of the stowed position and the lock assembly is in the locked position.

Abstract: The invention relates to a dual flow turbojet comprising an engine of axis X housed completely inside a tubular pod whose inside wall co-operates with the case of said engine to define an annular passage for a secondary flow delivered by a fan, said pod having an air inlet upstream of the engine, thrust-reverser means in its middle section, and a common nozzle for ejecting both the primary flow and the secondary flow, the outlet of the nozzle being situated downstream from the engine, said thrust-reverser means being suitable for taking up an active position in which the secondary flow is diverted outwards and forwards from said pod, said nozzle having an enclosure defined by the inside and outside walls of said nozzle.

Abstract: An aircraft thrust reverser system that includes a power drive unit operable to supply a drive force. The power drive unit includes a motor and a torque decoupler that sequentially decouples the power drive unit from a plurality of loads. The torque decoupler includes at least two output sections, each of which is coupled to the motor, and are not coupled to one another under normal operating circumstances. The output sections are each operable to decouple the motor from associated thrust reverser moveable components upon a torque magnitude being reached in the output section. The torque decoupler is configured so that the first and second output sections are coupled together a deadband time period after the torque magnitude is reached in on of the output sections.

Abstract: A thrust reverser system includes one or more actuators each having a locking mechanism that prevents unintended actuator movement, and thus unintended thrust reverser movement. Each of the actuators additionally includes a lock inhibitor assembly that engages the lock and prevents it from moving to its locked position until the actuator is moved into a stow position. Upon movement to the stow position, the lock inhibitor assembly disengages the lock, and the lock automatically moves into its locked position.

Abstract: A thrust reverser for a jet engine of a mobile platform. The thrust reverser includes a hinge beam defining a first track and a latch beam defining a second track. The thrust reverser also includes at least one cascade support ring having an upper end portion and a lower end portion. A first fitting is disposed at the upper end portion of the cascade support ring. The first fitting includes an engagement portion slidably positioned within the first track. A second fitting is disposed at the lower end portion of the cascade support ring. The second fitting includes an engagement portion slidably positioned within the second track.

Abstract: A motor control system is provided for controlling at least one motor driven mechanical actuator. The control system drives the motor according to a function of the actuator position. The system is further arranged to modify the motor speed to ensure that a predetermined power limit is not exceeded.

Abstract: A turbojet thrust reverser comprising two doors each displaceable between an open position and a closed position of the reverser by means of at least one respective control actuator; two electric motors each driving said at least one control actuator for each door; each motor being controlled by an electronic control unit connected to a full authority digital engine control; and two servo-control means for controlling the displacement of corresponding ones of said doors as a function of determined position references, said servo-control means enabling said doors to be displaced synchronously as a function of any variation in the forces exerted on the reverser and as a function of any force difference between the two doors.

Abstract: Each manual control unit for a moving part of a thrust reverser is associated with a maintenance plate that is pivotable between at least two positions: a first or “normal operation” position in which said plate prevents the manual control unit with which it is associated from being driven manually, while allowing it to be driven electrically; and a second or “maintenance” position in which said plate allows the manual control unit with which it is associated to be driven manually while preventing it from being driven electrically.

Abstract: A turbojet thrust reverser has two doors that are displaceable between a reverser open position and a reverser closed position, each door being controlled by a respective electronic control unit connected to a FADEC, and each door having a respective locking device for locking the position of the door associated therewith. Each locking device can be unlocked solely on receiving orders that come simultaneously from both electronic control units.

Abstract: An aircraft engine thrust reverser includes a bi-fold door having a first panel pivotally attached to a nacelle and a second panel hingedly connected to the first panel. The second panel is slidingly received within a pair of tracks disposed within the nacelle. A compression link provides mechanical communication between the second panel and an efflux control assembly such that the bi-fold door is hingedly openable when slidingly urged along the tracks when the compression link responds to the efflux control assembly.

Abstract: A gas turbine engine exhaust nozzle includes coaxial inner and outer conduits. The inner conduit has a main outlet at an aft end thereof, and a row of radial apertures spaced upstream from the outlet. The outer conduit has an auxiliary outlet at an aft end thereof, and surrounds the inner conduit over the apertures to form a bypass channel terminating at the auxiliary outlet. A plurality of flaps are hinged at upstream ends thereof to selectively cover and uncover corresponding ones of the apertures and selectively bypass a portion of exhaust flow from the inner conduit through the outer conduit in confluent streams from both the main and auxiliary outlets.

Abstract: A thrust reverser system that includes one or more power drive units operable to supply a drive force. The power drive unit includes a motor and at least two output sections, each operably coupled to transmit the drive force to the thrust reverser movable components. Each of the output sections is operable to decouple the motor from associated thrust reverser movable components upon a torque magnitude being reached in the output section. A deadband coupler is provided to couple the first and second output sections together a time period after the torque magnitude is reached in one of the output sections.

Abstract: A thrust reverser for a turbofan engine having an air duct defined radially inwardly by a wall around the turbofan engine and radially outwardly in part by a fan cowl of the engine. A bulkhead is adapted to be mounted on the fan cowl having a shaped surface defining an upstream wall. A translating cowl is supported for movement axially between a closed position substantially adjacent the bulkhead and an open position spaced axially apart from the bulkhead so as to form an outlet for discharge of air from the air duct. The translating cowl has a first wall and a kicker plate defining a shaped surface. The kicker plate and/or the bulkhead may have a dimension which varies at different radial locations about a circumference of the translating cowl to selectively control the forward component of velocity of the air discharged from the air duct. A plume control device may extend longitudinally across the outlet to divide the air discharged from the air duct into a plurality of plumes.

Abstract: A thrust reverser assembly comprising at least one thrust reverser element which, during normal use in association with a jet engine, is movable between a stowed position and a deployed position and is so arranged as to experience an assisting load during movement of the element from the stowed position towards the deployed position, a source of hydraulic fluid under pressure, and, a double-acting hydraulic piston and cylinder device for moving said element between said stowed and deployed positions, said hydraulic piston and cylinder device having a first port through which hydraulic fluid under pressure from said source is admitted to one side of said device, said one side of the device being a high pressure side during operation of the device in a thrust reverser element deploy mode, to displace said element from its stowed position, a second port through which hydraulic fluid is displaced from a low pressure side of the device during operation in said deploy mode, a return line through which hydraulic flu

Abstract: A fan thrust reverser includes an outer louver door joined to an inner blocker door by a drive link in a bifold configuration. The louver door is stowed closed in the outer skin of a fan nacelle outside the blocker door stowed closed in the inner skin of the nacelle. An actuator deploys open the louver and blocker doors, with the louver door extending radially outwardly and the blocker door extending radially inwardly for reversing fan exhaust flow during thrust reverse operation.

Abstract: A turbofan exhaust nozzle includes a jet pipe having a pair of thrust reverser doors disposed on opposite sides thereof. Each door has a hinge arm joined to a swing arm, which in turn is joined to the pipe. Each door also includes a latching clip at a forward end, and a deployment clevis between the clip and hinge arm. A common actuator is connected to both doors by corresponding links joined to the clevises for driving the links aft to pivot aft the doors and swing arms. A first lock selectively locks the latching clip and a second lock selectively locks the swing arms in coordination with the first lock for permitting variable area axial movement of the doors, thrust reverser deployment thereof, and retraction to stowed positions of the doors.

Abstract: A backup locking system for a thrust reverser door comprises a catch pivotally mounted by a pivot pin to a fixed structure of the thrust reverser. A hook with a self-locking profile is provided at the free end of said catch for cooperation with a locking interface on the door in the event of failure of the normal locking systems. At its other end remote from said hook, the catch has a heel ending in a part-cylindrical surface which is concentric with said pivot pin. The catch is urged against the locking interface by a piston rod which presses against a front face of said heel under the force of a spring acting on a piston to which said piston rod is attached. When the rod is retracted, a double lever positively moves the catch toward a minimum opening angle, at which point the door can be opened. An unlocking spring causes the full opening of the catch to maximum open position when an opening lever is released.

Abstract: A gearless electric thrust reverser actuator includes an electric motor that is coupled to a jack screw without any intervening gears. The actuator may additionally include all of the actuation and sensing components in a single actuation package. Thus, the actuator is relatively lightweight and compact.

Abstract: A thrust reversing arrangement for an aircraft turbofan propulsive power unit includes a flow redirecting structure which has reverse flow enhancing sub-structures comprising: (i) a cavity which is so dimensioned as to generate a back pressure which supports redirection of flow; (ii) a cascade assembly which provides a flow control slot so dimensioned as to optimize reverse thrust for predetermined fan duct flow conditions; (iii) an obstructing duct wall portion having a leading edge so positioned as to form a leakage slot providing controlled leakage of forward flow; (iv) a box structure, the dimensions of which are such as to optimize back pressure in the cavity; and (v) provision for gaseous fluid under static pressure from the fan duct to load the redirecting structure to the inoperative position.

Abstract: An electromechanical thrust reverser actuation system that is designed with non-symmetric redundant channels is interfaced with an aircraft engine control system that is also redundantly designed. In one embodiment, the engine control system is also designed with non-symmetric redundant channels, and in another embodiment it is designed with symmetric redundant channels.

Abstract: A thrust reverser actuator lock mechanism comprising a rotatable shaft, rotation of which in one direction from a rest position drives an associated thrust reverser from a stowed position towards an operative position in use, retractable abutment means having a rest position abutting an element rotatable with the shaft to prevent rotation of the shaft, resilient means urging said abutment means to said rest position, and, mechanical latch means sensitive to the speed of rotation of said shaft for latching said abutment means in a retracted position against the action of said resilient means when the rotational speed of said shaft exceeds a predetermined value.

Abstract: A thrust reverser system for a jet engine has a thrust reverser sleeve lock, preferably for each thrust reverser sleeve, that provides at least one of the redundant anti-deployment mechanisms of the thrust reverser. The thrust reverser sleeve lock has a lock pin that engages a thrust reverser sleeve when the thrust reverser sleeve is in a stowed position and the thrust reverser sleeve lock is in a lock position to prevent the thrust reverser sleeve from deploying. In an embodiment of the invention, the thrust reverser sleeve lock includes an single-action hydraulically actuated actutor to which the lock pin is affixed, the actuator extending the lock pin through a lock hole in the thrust reverser sleeve when the thrust reverser sleeve is in its stowed position and the thrust reverser sleeve lock is in a lock position.

Abstract: An electric control system and method for operating the cowl doors of an aircraft engine that includes one embodiment with one or more electric motors that are energized to move the cowl doors to the open position. The motor is de-energized and the cowl doors are allowed to close under their own weight, driving the motor and causing it to operate as a generator. An electrical load absorbs the energy generated by the motor while the cowl doors close, thereby limiting the speed at which the doors close.

Abstract: A synchronization cross-feed system for a thrust reverser having at least first and second sides. Each side of the thrust reverser has a thrust reverser actuation system having a plurality of actuators. The actuators in each thrust reverser actuation system are synchronized by a synchronization system. A synchronization cross-feed system couples the synchronization systems of the thrust reverser actuation system of the first and second sides of the thrust reverser allowing an anti-deployment mechanisms of each thrust reverser actuation system to serve as one or more of the redundant anti-deployment mechanism for other the thrust reverser actuation system.

Abstract: In a turbojet thrust reverser comprising, in an annular section of an outer cowling of the turbojet, a number of movable doors which, in an inactive position during operation in a forward thrust configuration, close off passages separating rigid spars of a fixed structure, there is provided, between two adjacent doors, a locking system which allows substantially simultaneous opening of the two doors. The locking system comprises, for each door, at least one hook mounted on the fixed structure so that it can be pivoted by an olive secured to the door between a door locking position and an unlocked position during opening or closing movement of the door. The two hooks of the locking system are rotationally interlinked by a mechanical linkage device, for example link rods, so as to prevent the unlocking of one door if the other door is closed.

Abstract: A gearless electric thrust reverser actuator includes an electric motor that is coupled to a jack screw without any intervening gears. The actuator may additionally include all of the actuation and sensing components in a single actuation package. Thus, the actuator is relatively lightweight and compact.

Abstract: A hook latch antideployment system for a thrust reverser having at least one thrust reverser sleeve that translates between a deployed and stowed positions and a thrust reverser actuation system that translates the thrust reverser sleeve. The thrust reverser has a stationary element that remains stationary with respect to the thrust reverser sleeve when the thrust reverser sleeve translates. The hook latch anti-deployment system has a hook latch a hook member and a latch member. One of the hook and latch members is coupled to the thrust reverser sleeve for translation therewith and the other of the hook and latch members is affixed to the stationary element of the thrust reverser. The hook member engages the latch member when the thrust reverser sleeve is in its stowed position to prevent deployment of the thrust reverser sleeve.

Abstract: The invention relates to a dual flow turbojet comprising an engine of axis X housed completely inside a tubular pod whose inside wall co-operates with the case of said engine to define an annular passage for a secondary flow delivered by a fan, said pod having an air inlet upstream of the engine, thrust-reverser means in its middle section, and a common nozzle for ejecting both the primary flow and the secondary flow, the outlet of the nozzle being situated downstream from the engine, said thrust-reverser means being suitable for taking up an active position in which the secondary flow is diverted outwards and forwards from said pod, said nozzle having an enclosure defined by the inside and outside walls of said nozzle.

Abstract: A thrust reverser system that has one or more moveable thrust reverser components for redirecting the thrust of a jet engine. The thrust reverser system has a torque limiter coupled between synchronization mechanisms that mechanically couple actuators used to drive the thrust reverser. The torque limiter reduces the potential for the transmission of excessive torque between thevdifferent moveable thrust reverser components, and reduces the likelihood of secondary system damage due to a jam in the system. Thus, the cost and/or weight associated with each of the components comprising the system may be reduced.

Abstract: A cascade type thrust reverser for an air duct of a turbofan engine includes a lock mechanism mounted on a track beam that supports the translating sleeve. A locking portion of a lock member of the lock mechanism is engageable with a slider by which the translating sleeve is supported by the track beam to lock the translating sleeve in the forward, closed position.

Abstract: An electromechanical thrust reverser actuation system that is designed with non-symmetric redundant channels is interfaced with an aircraft engine control system that is also redundantly designed. In one embodiment, the engine control system is also designed with non-symmetric redundant channels, and in another embodiment it is designed with symmetric redundant channels.

Abstract: A thrust reverser includes axially adjoining forward and aft cowls defining a fan nacelle for surrounding a fan and core engine with a fan duct therebetween. The aft cowl has a forward face and the forward cowl has an aft face adjoining each other to define a reverser nozzle which converges radially outwardly. The aft cowl is translatable between a stowed position in which the reverser nozzle is closed and a deployed position in which the reverser nozzle is open for discharging fan air in a forward direction for thrust reversal.

Abstract: An acoustically treated bullnose fairing assembly for a thrust reverser of an aircraft, the thrust reverser having an outer fixed structure and a stowable blocker door. The bullnose fairing assembly includes a back sheet, a face sheet and a honeycomb structure positioned between the face sheet and the back sheet—these three items being bonded together and securely affixed to an outer fixed structure of the thrust reverser. The back sheet has a forward end and a back end. The face sheet has a forward portion and a back portion, the back portion being aft of a forward edge of the blocker door when the blocker door is stowed. The forward portion of the face sheet is perforated. The perforated forward portion of the face sheet cooperates with the honeycomb structure to maximize the acoustic performance of the thrust reverser.