Abstract: The invention relates to a thrust reverser (1) for the nacelle of a dual-flow turbine engine, in which the bypass means (4) and the actuation jacks (22) of the sliding cowling (2) and of the reverse flaps (20) are arranged in two substantially parallel planes arranged above one another in the radial direction of the nacelle. The invention also relates to a nacelle for a dual-flow turbine engine that comprises such a thrust reverser.

Abstract: A thrust reverser with doors having at least one stationary structure is provided, on which at least one door is mounted pivoting between a closed position in which the door closes the reverser and makes up an outer cowling part, and an open position in which the door opens a passage in the stationary structure and can at least partially block a flow of air generated by a turbojet engine so as to reorient the door. The stationary structure includes at least two sets of cascade vanes that can be covered by the door when in the closed position.

Abstract: A thrust reversal device for a turbojet engine nacelle is provided that includes a deflection means and at least one cowl moveable relative to at least one fixed structure including at least one at least partly peripheral front frame and equipped with means for connection to a corresponding upstream portion. The front frame has a deflection edge having an upstream extension forming a deformable flap intended to become an aerodynamic interface with the corresponding upstream portion to which is attached the front frame, and in that a portion of the moveable cowl is conformed so as to, in the closing position, interface with said upstream attachment portion by forcing withdrawal of the deformable flap.

Abstract: A variable area fan nozzle for use with a gas turbine engine system includes a nozzle having a cross-sectional area associated with a discharge air flow from a fan bypass passage. The nozzle is selectively moveable between multiple static positions for varying the cross-sectional area and multiple thrust reverse positions that are different from the static positions for reversing a direction of the discharge flow from the fan bypass passage to produce a thrust reversing force.

Abstract: A device for opening and closing a thrust reverser door (3) of a jet engine includes at least one actuator and at least one locking mechanism (10) including at least one first locking element (11) arranged on the thrust reverser door (3) and at least one second locking element (13) arranged on the thrust reverser structure (5). To open the locking mechanism (10) against higher internal pressures in the thrust reverser (1) without increasing a power of the actuator or requiring the operation of the latter, the device includes, in addition to the actuator, at least one unloading mechanism (20) which is coupled to the locking mechanism (10).

Abstract: The invention relates to a turbojet engine nacelle that includes a power supply source (113) for a system for actuating and controlling a thrust reverser device (121), and for a system for actuating and controlling a variable nozzle device (120), characterised in that the power supply can be switched between a first position in which it powers the system for actuating and controlling the thrust reverser device, and a second position in which it powers the system for actuating and controlling the variable nozzle device, wherein the switching is carried out under the action of a control output from a computer (103) capable of receiving a thrust reverser opening control (100).

Abstract: A nacelle assembly for a bypass gas turbine engine includes a variable area fan nozzle having a first fan nacelle section and a second fan nacelle section. The variable area fan nozzle is in communication with a fan bypass flow path, the first fan nacelle section defines an intermittent trailing edge which defines a multiple of ports and the second fan nacelle section defines a multiple of doors, each of the multiple of doors match each of the multiple of ports such that a fan nacelle trailing edge is continuous when the second fan nacelle section is selectively translated to a closed position relative to the first fan nacelle section.

Abstract: An example thrust reverser blocker door includes a blocker door that is movable from a stowed position to a deployed position. Flow moves through an area of a bypass flowpath when the blocker door is in the stowed position. The blocker door blocks no less than about 70% and no more than about 85% of flow through this area when the blocker door is in the deployed position, wherein the area does not extend circumferentially past the blocker door.

Abstract: A by-pass turbojet including a thrust reverser is disclosed. The thrust reverse includes a deflector device which deflects all or part of the primary stream gas in such a manner that the deflected primary stream gas encounters the secondary stream, thereby reducing the injection speed of the secondary stream in an aft direction, and thus generating the thrust-reversal effect. The secondary stream escapes from the aft end of the nacelle. In the thrust-reversal position, the deflector device is inscribed radially substantially within the section of the primary nozzle cowl at the aft end of the nacelle. Such a thrust reverser is particularly simple in design, inexpensive, and makes it possible to avoid having moving parts present on the outside portion of the nacelle, thus simplifying the design of the turbojet.

Abstract: A nozzle locking assembly is provided for an aircraft with a thrust reverser actuation system (TRAS) having a transcowl and a variable area fan nozzle (VAFN) system having a nozzle.

Abstract: A turbomachine including at least one thrust reverser and a device for actuating the thrust reverser, which includes at least one hydraulic engine supplied with pressurized fluid by a fuel circuit of the turbomachine, is disclosed.

Abstract: A device is provided for pivoting at least one pivotable element in a gas turbine engine between a first and a second position in order to influence a gas flow in an annular gas duct in at least one of the positions. The device includes a moveable annular member which is arranged externally around the gas duct and is connected to the pivotable element in order to effect the pivoting of the pivotable element. The annular member is more specifically arranged to be displaced in a substantially axial direction and arranged to pivot the pivotable element when it is displaced axially.

Abstract: The invention relates to a jet engine nacelle reverse thrust device (10) including a means for diverting at least one portion of a jet engine air flow and moreover includes at least one cowl (20) that is translatable in a direction substantially parallel to a longitudinal axis of the nacelle, the device having at least one flap (30) that is pivotably mounted, by one end, onto the translatable cowl, said translatable cowl (20) being capable of passing alternately from a closed position, wherein said cowl, with the flap (30) in a retracted position, ensures the aerodynamic continuity of the nacelle and covers the diverting means, to an open position, wherein said cowl opens a passage in the nacelle and uncovers the diverting means, the flap (30) being in a pivoted position wherein it is capable of sealing off a portion of an annular channel of the nacelle.

Abstract: The present invention relates to a thrust reversal device (1) for a turbojet engine nacelle, characterized in that: (i) the movable cowl (3) is provided with at least one driving lead screw (30) having at least one peripheral groove over at least part of the length thereof, whereby said groove can engage with a stationary guide means (31) of the nacelle so as to rotate the lead screw during the translational movement of the movable cowl; and (ii) the lead screw is associated with at least one means for transmitting (32, 35, 36) the rotational movement thereof towards at least one drive system (33, 34, 25) of the flap.

Abstract: Track beams for the cowling of a jet engine for aircraft are formed of a base body with at least one slide for displaceably mounting a thrust reverser of the jet engine. A connection is provided for an inner engine cowling and fittings for detachably and pivotally attaching to a supporting structure or for connecting to another track beam. To provide such a track beam which has a particularly low weight yet, nevertheless, is sufficiently stiff, the base body is formed by a hollow profile section with a substantially closed cross-section. The hollow section is produced of a carbon-fiber-reinforced synthetic material by way of a resin-infusion process. Two flanges are provided on the hollow section of the base body of the track beam for providing a connection to the inner engine cowling.

Abstract: A missile in which a nose portion is rotatably mounted on a main body portion of the missile and is subjected to thrust to bring it to a demanded roll attitude and to apply to it a demanded lateral steering force. The thrust is produced by a propellant gas and supplied to discharge ducts in the nose portion which provide for the discharge of the propellant gas tangentially with respect to the nose portion. The discharge ducts are selectively opened and closed by relative axial displacement of the nose portion and a valve spool which controls the flow of propellant gas. An actuator responsive to guidance control signals causes a predetermined roll torque to bring the nose portion to a demanded roll attitude and a predetermined lateral steering force on the missile.

Abstract: Aircraft nacelle including a cowling and an engine, the cowling including a fixed portion and a mobile portion able to slide in order to define a radial opening with the mobile portion, a thrust reverser system including a plurality of flaps intended to be deployed in order to seal at least partially an annular channel surrounding the engine, the mobile portion of the cowling including an annular housing extending longitudinally in order to receive the flaps in rest position. Each flap is linked to the fixed portion by a pivot joint and is linked to the mobile portion by a sliding-pivot joint, in such a way that a sliding of the mobile portion in separating from the fixed portion provokes a rotation of each flap around the axis of rotation of the joint with the fixed portion.

Abstract: Aircraft nacelle which includes a cowl with a longitudinal axis, an engine housed in the cowl, an annular channel surrounding the engine and designed to receive a secondary flow, wherein the cowl includes a fixed part and a moving part which slides along the longitudinal axis to define a radial opening between the moving and fixed parts, a thrust reverser system which includes internal flaps mounted so that they rotate and which are designed to block the annular channel, at least partially, in the deployed position, where the moving part of the cowl includes a radial housing to receive the internal flaps in the at-rest position and where a system of applying an elastic force on each flap towards deployment is provided. Thus control over the position of the internal flaps is obtained directly by sliding the moving part.

Abstract: The thrust reverser includes, in one aspect, an interior flow deflector which defines a portion of a substantially continuous and uninterrupted nozzle interior surface with the interior of a jet pipe when the door is in a stowed position, thereby reducing aerodynamic losses and improving efficiency. In another aspect, improved sealing arrangement between the jet pipe and the door provides increased performance when the doors are stowed.

Abstract: A system that allows for quick and easy adjustment of the position of a thrust reverser pivot door comprises an actuator rod end bolt and a pair of pivot door hinge pins, all of which have an eccentric element. The actuator rod end bolt includes a cylindrical portion along the center of the length of the bolt that has an eccentric element which protrudes beyond the outer surface of the cylinder. Each pivot door hinge pin includes a cylindrical portion along the center of the length of the pin that has an eccentric element which protrudes beyond the outer surface of the cylinder. Rotation of either the actuator rod end bolt or the pivot door hinge pins or both the actuator rod end bolt and the pivot door hinge pins adjusts the position of the pivot door.

Abstract: A ducted propulsion vector system that vectors thrust generated from ducted fan powered aircraft. The system has hinged duct flaps may be vectored from +10 degrees up and turned through ?90 degrees downward. Vectored downward 90 degrees, the flaps vector thrust enabling vertical/short takeoff and landing of an aircraft. Hover control is facilitated by internal mounted vanes in line of the thrust stream. The duct flaps are transitioned at operator's input to enable the aircraft to achieve forward flight.

Abstract: A gas turbine engine comprising a bypass duct defined radially outwardly by a nacelle and radially inwardly by a core engine casing. The nacelle comprises a thrust reverser unit having at least one blocker door rotatably attached to a static part and slidably connected to a translating part. The translating part is arranged to move between a stowed position and a deployed position and in the deployed position the blocker door spans the bypass duct. In the stowed position the blocker door is stowed inside the translating part and does not form part of an airwash surface of the bypass duct.

Abstract: The thrust reverser is used with a gas turbine engine and includes first and second doors pivotable between a stowed position and a deployed position. When deployed, pivoting fairings on the first door are moved so as to give room to the second door as its trailing edge moves within the first door. When stowed, the second door preferably provides the locking mechanism to the pivoting fairings of the first door.

Abstract: Aircraft systems including cascade thrust reversers are disclosed herein. An aircraft system in accordance with one embodiment includes a cascade thrust reverser having a fixed reverser ramp and a nozzle outer wall section at least partially aft of the fixed reverser ramp. The nozzle outer wall section is movable between a deployed position and a stowed position. The nozzle outer wall section includes a forward portion with a leading edge section. The fixed reverser ramp has a portion forward of and adjacent to the nozzle outer wall section when the nozzle outer wall section is in the stowed position. The portion of the fixed reverser ramp has a first slope. The forward portion of the nozzle outer wall section that is aft of the leading edge section has a second slope different than the first slope.

Abstract: Aircraft nacelle which includes a cowl with a longitudinal axis, an engine housed in the cowl, an annular channel surrounding the engine and designed to receive a secondary flow, wherein the cowl includes a fixed part and a moving part which slides along the longitudinal axis to define a radial opening between the moving and fixed parts, a thrust reverser system which includes internal flaps mounted so that they rotate and which are designed to block the annular channel, at least partially, in the deployed position, where the moving part of the cowl includes a radial housing to receive the internal flaps in the at-rest position and where a system of applying an elastic force on each flap towards deployment is provided. Thus control over the position of the internal flaps is obtained directly by sliding the moving part.

Abstract: A thrust reverser actuation system is provided that includes a synchronization system that synchronizes the actuation of at least two actuators coupled to at least two power drive units. The synchronization system includes a first synchronization shaft coupling the first power drive unit to the second power drive unit and a second synchronization shaft coupling the first power drive unit to the second power drive unit. The at least two actuators are adapted to receive a drive force and configured, in response to receipt of the drive force, to move between a stowed position and a deployed position. The synchronization system is configured to transfer power between the first power drive unit and the second power drive unit, thereby eliminating a mismatch in power and provide uniform deployment of the at least two actuators.

Abstract: Apparatus including an exhaust nozzle assembly having a translatable structure operable to open and close a flow diverting port in an exhaust duct. The translatable structure includes a forward region partly defining a converging nozzle region. The translatable structure includes a rearward region partly defining a diverging nozzle region. The forward region and the rearward region join at an inner edge that partly defines a throat constriction. The translatable structure is translatable between a plurality of operational positions each associated with a longitudinal position of the throat constriction. In a first operational position, the flow diverting port is fully closed. In a second operational position, the flow diverting port is fully opened. In a first intermediate operational position, the flow diverting port is fully closed. In a second intermediate operational position, the flow diverting port is at least partly opened.

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 fluidic diverter valve includes valve element freely disposed within a valve bore. The valve bore has a cross sectional area that varies. As a result, the clearance between the valve element and an inner surface of the valve bore also varies. This variation in cross sectional area, and thus clearance, is such that a force of sufficient magnitude to move the valve element from a seated position is initially applied to the valve element, but the force on the valve element is reduced once it is moved from the seated position. Thus, the impact force upon attaining another seated position is reduced.

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 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: 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: 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 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 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: 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: 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 thrust reverser for a turbofan engine having an air duct defined radially inwardly by a cowl around a gas turbine and radially outwardly in part by a fan case of the engine includes a bulkhead that is adapted to be mounted on the fan case. A translating sleeve is supported for movement axially between a closed position adjacent the bulkhead and an open position spaced apart axially to the rear of the bulkhead so as to form a outlet opening for discharge of air from the air duct. A cascade array fixed in the outlet opening has a substantially conical portion, the forward end of which is of a diameter substantially smaller than the diameter of the rearward end.

Abstract: A system for controlling one or more jet engine thrust reversers includes a motor, a position sensing device, and a controller circuit. The motor is coupled to one or more jet engine thrust reverser moveable components for moving the one or more thrust reverser moveable components to at least a stowed position. The position sensing device is operable to sense at least when the one or more thrust reverser moveable components attain a predetermined position relative to the stowed position. The controller circuit has an output coupled to the motor so the motor rotates at a variable speed in response to a position sensing device that senses when the predetermined position is attained. The system controls the stowage operation of the jet engine thrust reversers such that structural damage is avoided, and/or a limit cycle condition is prevented, and/or engagement of stow locks is assured.

Abstract: A thrust reverser includes a pair of doors covering corresponding portals in an exhaust duct between an inlet and outlet nozzle at opposite ends thereof. The duct also includes a pair of side beams having actuators mounted thereon, and operatively joined to the doors for selective rotation thereof about corresponding pivots. Blister fairings are disposed inside the duct and sealingly join the doors to the beams around respective ones of the pivots.

Abstract: A thrust reverser for a turbojet engine is provided with at least one displaceable assembly including a displaceable cowling portion and a flap. The displaceable cowling portion and the flap each subtend stationary upstream and downstream cowling portions such that the displaceable cowling portion forms a portion of the external engine cowling covering a reverse thrust opening and the flap forms a portion of the outer boundary of the gas flow in a forward thrust position. In a reverse thrust position, the reverse thrust opening is uncovered, and the displaceable cowling portion and the flap are displaced downstream such that the displaceable cowling portion extends downstream, parallel to the longitudinal engine axis and above, without interference, the downstream cowling portion.

Abstract: An integrated system for missile steering, which uses both jet reaction control (JRC) and aerofin control systems, is provided with a variable coupling mechanism for adjusting the relative responsiveness of the two systems in accordance with the pressurization state of the JRC system pressure chamber. In one embodiment, the pivoting action of a joystick which actuates the gas flow control pintles of the JRC system is permitted only under sufficient pressurization of the pressure chamber. In a second embodiment, the extent to which the pintles protrude from their controllable housings is adjusted according to the pressure in the pressure chamber. In this manner, when JRC is undesirable or is unavailable, the missile aerofins are permitted their full range of motion without being constrained by the pintles.

Abstract: A cascade thrust reverser for use with a mixer/ejector noise suppressor has a set of internal blocker doors controllably moveable between a stowed position, where engine exhaust passes through and out the tailpipe, and a deployed position, where engine exhaust is blocked and redirected out a pair of cascades or louvers. External cascade doors cover the cascades from the outside during flight, but are moved aft, exposing the cascades, when the blocker doors are deployed subsequent landing. In a preferred embodiment, the cascade doors and the blocker doors are interconnected through a pair of actuation mechanisms, whereby movement of the cascade doors is sequenced to the motion of the blocker doors. The blocker doors and the cascade doors are shaped to provide a clean aerodynamic profile when stowed, so that the noise suppressor functions optimally. The actuation mechanisms also preferably include lock mechanisms for only allowing the thrust reversers to be deployed just subsequent landing.

Abstract: A hinge arm for a thrust reverser door may be mounted to an exhaust nozzle using an aft mount. The mount includes a frame for attachment to the nozzle. A swing link has a first pin pivotally joined to the frame, and a second pin for pivotally joining the hinge arm to the link to permit both swinging and pivoting of the hinge arm from the frame. The aft mount thusly permits the reverser doors to be reliably stowed around the nozzle.

Abstract: A thrust reverser for a turbofan jet engine having a stationary structure defining an upstream part of a fan cowling and an axially displaceable, annular structure located downstream of the stationary structure, wherein the inner surface of the fan cowling is spaced from an outer surface of an engine cowling to form an annular duct. A plurality of flaps form a portion of the inner surface of the fan cowling during a forward thrust position, and in a reverse thrust position, the flaps pivotably rotate about a stationary pivot so that their first edges are adjacent with the outer surface of the engine cowling to block the annular duct. A plurality of thrust reverser baffle portions are covered by the flaps during the forward thrust position, and during the reverse thrust position, the thrust reverser baffle portions cover a passageway in the fan cowling between the stationary structure and the displaceable structure.