Abstract: An exhaust system has an engine exhaust plane associated with an entrance to the exhaust system, an exhaust exit plane associated with an exit of the exhaust system, a forward cap movable relative to the engine exhaust plane and configured to selectively intersect the engine exhaust plane, and an aft cap movable relative to the exhaust exit plane and configured to selectively intersect the exhaust exit plane.

Abstract: A nacelle is provided for an aircraft propulsion system. This nacelle includes a stationary support, a fanlet, a thrust reverser sleeve and an interface assembly providing an interface between the stationary support, the fanlet and the thrust reverser sleeve where the fanlet and the thrust reverser sleeve are respectively in stowed positions. The stationary support extends circumferentially about an axial centerline. The fanlet includes an inlet structure and a fan cowl. The fanlet is configured to translate axially along the centerline. The thrust reverser sleeve is configured to translate axially along the centerline. The interface assembly includes a pair of interlocking components, wherein a first of the interlocking components is mounted to the fanlet at the aft end of the fanlet.

Abstract: A deployable grille with fins for a thrust-reversal system for an aircraft turbine engine. The grille can adopt a rest position and a deployed, active position wherein the fins are axially spaced further apart than in the rest position. At least between two fins, the grille includes resilient return device forcing the two fins to move apart axially from one another.

Abstract: A thrust reverser system having an asymmetric vane assembly is provided. The provided thrust reverser system generates a desired vertical thrust component that at least partially offsets a potential nose-up pitch moment. The provided thrust reverser system employs a single row asymmetric vane geometry that reduces weight and material cost.

Abstract: A method for cooling a rotatable nozzle includes rotating a curved seal about a seal land while maintaining contact therewith. Cooling air is directed through a first diffusion hole in the curved seal to cool the nozzle if the rotatable curved seal is in a first position where higher heat is encountered. Cool air is directed through a second diffusion hole in the curved seal to cool the nozzle if the rotatable curved seal is in a first position where higher heat is encountered and if in a second position where relatively lower heat is encountered.

Abstract: The present disclosure concerns a thrust reverser for an aircraft turbojet engine nacelle including at least one movable thrust reverser cowling, a means for locking the cowling, an outlet nozzle having a variable cross-section that is arranged in the downstream extension of said cowling and that is movable, and at least one actuator that includes an actuating rod capable of moving the variable nozzle and the movable cowling, remarkable in that the reverser is provided with a passive coupler.

Abstract: An aircraft comprises at least first and second gas turbine engines arranged in a line extending generally normally to an aircraft longitudinal axis (A), each engine comprising at least one compressor or turbine rotor disc defining a respective rotational plane (D32-D42). The rotational plane (D32-D42) of at least one of the rotors of at least one of the engines is angled relative to the aircraft longitudinal line (A) such that a burst disc plane of the respective engine is nonintersecting with another engine.

Abstract: A thrust reverser for a nacelle may include a translating sleeve. A plurality of linkless blocker doors may be coupled to the translating sleeve. The translating sleeve may translate along a line of action which is non-parallel to an engine centerline. The non-parallel translation of the translating sleeve may prevent interference between the translating sleeve and surrounding components.

Abstract: In various embodiments, a nacelle may comprise a cowl, an inner panel, a VAFN panel and an overhang. The cowl may define a first portion of an outer surface of the nacelle. The inner panel may be disposed radially inward of the cowl. The VAFN panel may be disposed radially inward of the cowl. The overhang may be attached to the inner panel. The overhang may be positioned radially inward of the leading edge of the VAFN panel.

Abstract: An aircraft (2) comprises at least first and second gas turbine engines (10a, 10b) arranged in a line extending generally normally to an aircraft longitudinal axis (A), each engine (10a, 10b) comprising at least one compressor or turbine rotor disc (32-42) defining a respective rotational plane (D32-D42). The rotational plane (D32-D42) of at least one of the rotors (32-42) of at least one of the engines (10a, 10b) is angled relative to the aircraft longitudinal line (A) such that a burst disc plane of the respective engine (10a, 10b) is nonintersecting with another engine (10a, 10b).

Abstract: An aircraft turbofan engine variable area fan nozzle (VAFN) is disclosed that has a forward end that is continuously supported within a circumferential recess in the wall of the nacelle in front of it. During operation, the VAFN translates back and forth but always has its front end within the recess. Relatively simple seals help seal the recess against the VAFN. An array of openings with aft facing vanes, termed an aft cascade, is built into the VAFN. The openings are hidden within the recess when the VAFN is in the forward-most positions, and they are exposed to allow air to flow from the bypass duct through the cascade when the VAFN is in aft positions. The aft cascades can have different airflow directions based on their locations around the engine.

Abstract: One embodiment includes a pivot thrust reverser with a first pivot door with an upper linkage and a lower linkage and a second pivot door, spaced from the first pivot door, with an upper linkage and a lower linkage. A first actuator is located on a first side of an attachment location to drive the first pivot door. A second actuator is located on a second side of the attachment location to drive the second pivot door. A third actuator is located substantially radially opposite the attachment location to drive both the first pivot door and the second pivot door. The first pivot door is configured to be pivoted from a stowed position to a deployed position by both the first actuator and the third actuator. The second pivot door is configured to be pivoted from the stowed position to the deployed position by both the second actuator and the third actuator.

Abstract: A thrust reverser system includes a translating cascade, a blocker door, and a drive link. The drive link may be pivotably coupled to the translating cascade and the blocker door. The translating cascade may be coupled to a translating sleeve of a nacelle. The drive link may cause the blocker door to deploy in response to the translating cascade moving in an aft direction. The blocker door may be pivotably coupled to a fixed aft portion of the nacelle.

Abstract: Methods are provided for manufacturing a thrust reverser cascade. One of these methods includes providing a first cascade segment and providing a second cascade segment. The first cascade segment includes a first frame rail, a second frame rail and an array of first vane segments laterally between the first and the second frame rails. The second cascade segment includes an array of second vane segments. The second cascade segment is bonded laterally to and between the first and the second frame rails and transversely to the array of first vane segments. In another method, first and second cascade segments are discretely molded. Each of the cascade segments includes an array of vane segments and comprises fiber reinforcement in a polymer matrix. The second cascade segment is bonded to the first cascade segment and is nested into the first cascade segment.

Abstract: A thrust reverser with grids includes a jet engine pylon, a one piece cowl either directly or indirectly slidably mounted on the jet engine pylon between a direct jet position and a reverse jet position, and a system for locking this cowl on a beam. The system has a single tertiary lock, which is positioned on one side of the jet engine pylon being capable of locking a corresponding upper edge of the cowl. In addition, the tertiary lock includes a locker to lock the cowl, a blocker for blocking the locker, and a position detector in order to detect the position of the locker. The system further includes another detector to detect proper closing of the other upper edge of the cowl.

Abstract: The invention relates to an actuation device (1) for moving a movable cover of a thrust reverser. Said actuation device includes: —an actuator including a first element (4), such as a screw, and a second element (5), such as a nut, that engages with the first element such that rotation of the first element causes translation of the second element; —a locking portion (31) rotatable between a locked position, wherein the locking portion prevents the first element (4) from rotating, and an unlocked position, wherein the locking portion (31) allows the first element (4) to rotate; and —an inhibiting part (45) that is translatable between a first position, wherein the inhibiting part (45) allows the locking portion (31) to rotate, and a second position, wherein the inhibiting part (45) prevents the locking portion (31) from rotating into the locked position.

Abstract: A nacelle for an aircraft bypass turbofan engine includes an upstream section via which an airflow enters, a middle section surrounding the fan of the turbofan and a downstream section having an inner structure and an outer structure delimiting a flow duct in which the air flows. The outer structure includes one cowling movably mounted on the inner fixed structure. The nacelle also has a top to accept a pylon for attaching a wing of the aircraft. The nacelle further includes one first panel mounted on the inner structure on one side of the nacelle and one second panel mounted on the other side of the nacelle. The first panel undergoes a physical interference with a part of the wing. The second panel increases the air removed from this other side of the nacelle during thrust reversal.

Abstract: The invention relates to a method for controlling a plurality of actuators (9a, 9b, 9c) for a movable thrust reverser cowl (1), characterized remarkable in that the position deviation between adjacent actuators is measured in real time, and in that the speed profile of the actuator or actuators in question is adjusted by a position deviation exceeding a predetermined threshold.

Abstract: An air discharging device (20) for an aircraft turbine engine, comprising at least one door (24) displaceable between an open and a closed position of a corresponding orifice (30) and comprising two valves (26, 28), which delimit between them a conduit (68) for guiding a portion (74) of the secondary flow (76) outwards in the downstream direction, and which are integral with each other and are hinged around a pivot axis (58), so that in said open position, the upstream end of said internal valve (26) protrudes from the inner side relative to the internal surface (12), the downstream end of said external valve (28) protrudes from the external side relative to the external surface (14), and said internal valve (26) is spaced away from the fixed structure (22) so that an air passage exists downstream of said internal valve (26), between the latter and said fixed structure (22).

Abstract: A thrust-vectoring nozzle is disclosed that includes a cylindrical case and a flow director. The flow director includes a cylindrical ring having a dimension to fit within the cylindrical case. The cylindrical ring has an inner wall and an outer wall and a plurality of fixed vanes are coupled to the inner wall of the ring. The flow director is configured to rotate about first and second mutually perpendicular axes.

Abstract: The present invention relates to a jet engine nacelle (1) comprising an aft section (5) having an internal structure (9) intended to surround an aft portion of an engine compartment and to define, with an exhaust nozzle (6), a calibrated outlet section for the ventilation of the engine compartment by way of spacing means arranged in the outlet section, characterized in that the spacing means are divided into rigid spacing means (11) designed to provide a constant spacing and into compensating means (13) designed so as to be able to adapt to the relative movements of the jet engine with respect to the nacelle.

Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a fan nacelle that includes a first fan nacelle section and a second fan nacelle section, the second fan nacelle section movable relative to the first fan nacelle section. A cascade array is mounted to the first fan nacelle section for movement relative thereto between a stored position and a deployed position, the stored position locates the cascade array at least partially within the first fan nacelle section.

Abstract: A gas turbine engine is provided having an offtake passage that in one form is capable of extracting a bypass flow from the engine. The airflow traversing the offtake passage is introduced to an exhaust flow of the gas turbine engine through an offtake outlet. The offtake outlet includes an airflow member that is moveable. A nozzle is also provided for exhaust from the gas turbine engine. In one form the nozzle includes moveable duct members. Flows exiting the offtake outlet and the nozzle can be combined after passing the airflow member and the moveable duct members, respectively.

Abstract: The present invention relates to a jet engine nacelle comprising a forward air inlet section, a mid-section intended to surround a jet engine fan, and an aft section equipped with at least one thrust reversal system comprising, on the one hand, means for deflecting at least part of an air flow of the jet engine and, on the other hand, at least one cowl (12) mounted translatably along at least one guide rail (15) in a direction substantially parallel to a longitudinal axis of the nacelle, said movable cowl being able to switch alternately from a closed position, in which it provides the nacelle with aerodynamic continuity and covers the deflection means, to an open position in which it opens a passage in the nacelle and uncovers said deflection means, the nacelle being characterized in that the aft section is equipped with at least one stud (18) mounted such that it can move over a fixed structure of the aft section in the region of the guide rail between a retracted position, in which said stud is withdrawn f

Abstract: A nacelle, for an aircraft jet engine having a high bypass ratio, in which a jet engine having a longitudinal axis is mounted. The nacelle includes a wall that concentrically, and at least partially, surrounds the jet engine and together defines an annular duct. The nacelle further includes a displacement device that controllably displaces a portion of the nacelle wall in order to modify the section of the flow outlet passage and form at least one longitudinally extending opening. A device for forming a fluid barrier along the at least one longitudinally extending opening is provided to counteract the natural exhaust.

Abstract: A turbine engine exhaust nozzle includes a core gas duct, a nozzle duct, and a thrust vectoring duct system having a duct valve, a first vectoring duct and a second vectoring duct. The nozzle duct directs a first portion of core gas from the core gas duct through a nozzle duct outlet along a centerline. The duct valve connects the core gas duct to the first vectoring duct during a first mode of operation, and connects the core gas duct to the second vectoring duct during a second mode of operation. The first vectoring duct directs a second portion of core gas from the core gas duct through a first vectoring duct outlet along a first trajectory. The second vectoring duct directs a third portion of core gas from the core gas duct through a second vectoring duct outlet along a second trajectory that is angularly offset to the first trajectory.

Abstract: A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating thrust reverser sleeve with a trailing edge. The thrust reverser sleeve is movably disposed aft of the nacelle's aft edge and is movable between a forward position and an aft position. A translating fan nozzle having a forward edge is movably disposed behind the trailing edge, and is movable between a stowed position and a deployed position. An upstream bypass flow exit is defined between the trailing edge and the forward edge when the fan nozzle is in the deployed position. An extendable actuation system is configured to move the fan nozzle between the stowed position and the deployed position.

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: An assembly for an aircraft gas turbine propulsion engine includes an engine nacelle and a thrust reverser. The engine nacelle is configured to have at least a portion of an aircraft gas turbine propulsion engine mounted therein, and includes an intake end, an exhaust end, and an outer surface that extends between the intake end and the exhaust end. At least the engine nacelle outer surface proximate the exhaust end has a semicircular section and a noncircular section. The thrust reverser includes a forward end, an aft end, and an outer surface that extends between the forward and aft ends. The thrust reverser forward end is coupled to the engine nacelle exhaust end. At least the thrust reverser outer surface proximate the forward end has an arc section and a noncircular section. The arc section subtends an angle greater than ? radians.

Abstract: A turbofan engine (10) includes a fan variable area nozzle (FVAN) (50) which effectively changes the physical area and geometry within a fan bypass flow path (40) to manipulate the pressure ratio of the bypass flow. The FVAN generally includes a multitude of aerodynamically shaped inserts (52) circumferentially located about the core nacelle (12). The FVAN at a fully stowed position (takeoff/landing) takes up a minimum of area within the fan bypass flow path to effectively maximize the fan nozzle exit area (44) while in the fully deployed position (cruise) takes up a maximum of area within the bypass flow path to effectively minimize the fan nozzle exit area. By separately adjusting each of the multiple of inserts relative the other inserts the FVAN provides an asymmetrical fan nozzle exit area to selectively vector the fan bypass flow.

Abstract: An outlet device for a jet engine comprises a number of fixed ducts, each with a gas intake and a gas outlet for conducting a gas from the jet engine, at least two of the outlets of said gas ducts open in different directions, and a gas distribution arrangement is arranged at the gas intakes for selective distribution of the gas to the ducts.

Abstract: A method for exhausting gas from an aircraft engine assembly is provided. The method includes coupling a first exhaust duct in fluid communication only to a first engine. The first exhaust duct includes a primary outlet and a secondary outlet. The method further includes coupling a second exhaust duct in fluid communication only to a second engine. The second exhaust duct includes a primary outlet and a secondary outlet. The method also includes aligning a portion of the first engine secondary outlet concentrically within a portion of the second engine secondary outlet.

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: An exhaust nozzle includes a conical duct terminating in an annular outlet. A row of vortex generating duplex tabs are mounted in the outlet. The tabs have compound radial and circumferential aft inclination inside the outlet for generating streamwise vortices for attenuating exhaust noise while reducing performance loss.

Abstract: The present invention relates to a door (9) for a door-type thrust reverser able to be hinged to a fixed structure of a thrust reverser comprising an internal surface designed to integrate with a stream of an airflow generated by a turbojet and an outer surface designed to provide the external aerodynamic continuity of a nacelle to which said thrust reverser is to be fitted, said door being fitted with airflow deflection means located at an upstream end of the door and mounted movably in a plane approximately perpendicular to the plane of the door between a first, retracted position in which the deflection means do not enter the stream when the door is closed and a second, deployed position in which the deflection means project from the door, said door being characterized in that the deflection means are rotatable in the said plane about a corresponding shaft.

Abstract: A V/STOL aircraft includes an aft by-pass powerplant 28 having an aft, rearwardly directed nozzle 30 and twin transverse vectorable nozzles 32. A duct 29 extends forwardly of the powerplant and terminates in a vectorable nozzle 16. The duct supplies relatively cool by-pass air to the nozzle.

Abstract: A nacelle for an aircraft high-bypass jet engine, in which a jet engine having a longitudinal axis is mounted, the nacelle including a wall concentrically and at least partially surrounding the jet engine and defining with the latter an annular duct for fluid inner flow, including at the downstream end of the nacelle wall a passage section of a flow outlet. The nacelle includes a displacement mechanism displacing on request a portion of the nacelle wall to modify the passage section of the flow outlet through which a major portion of the flow escapes, the displacement forming in the nacelle wall at least one opening through which a small portion of a leak flow, naturally escapes. The nacelle further includes a fluid device that uses a fluid for compelling the leak flow to flow along the outer face of the portion of the nacelle wall located downstream relative to the at least one opening.

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 present invention provides an air-oil separator comprising a first region having a mixture of air and oil, a second region wherein separation of at least some of the oil from the air-oil mixture occurs and at least one multi-directional injector plug located on a rotating component in flow communication with the first region and the second region, the multi-directional injector plug having a discharge head that is oriented such that at least a part of the air-oil mixture discharged therefrom has a component of velocity that is tangential to the direction of rotation of the rotating component.

Abstract: A pivot arrangement for a thrust reverser door of a gas turbine engine, the pivot fitting having a base and a shaft projecting from a main side of the base. The shaft receives a preferably curved pivot arm of the door to provide a low profile arrangement which improves performance when the doors are stowed.

Abstract: The thrust reverser is used with an aircraft gas turbine engine and includes upper and lower doors pivotable between a stowed position and a deployed position. When deployed, the doors redirect a portion of the efflux to generate a nose-down pitching moment on an aircraft to improve handling during thrust reversing on a runway.

Abstract: An exhaust nozzle for use in a gas turbine engine comprises a flow body for receiving exhaust gas from the turbine engine and includes a leading edge and a trailing edge. The leading edge connects with the gas turbine engine such that the flow body surrounds a centerline of the engine. The trailing edge comprises a serrated portion and a non-serrated portion. The serrated portion is formed from a plurality of tabs for mixing exhaust gas exiting the flow body with gases passing by an exterior of the flow body. The non-serrated portion is positioned along a lower portion of the trailing edge with respect to the engine centerline.

Abstract: An injector includes a nozzle hole formation part having a nozzle_hole formation area and nozzle holes in at least one circle shape in the formation area. The formation area is divided into central and peripheral regions by a predetermined circle, the former inward from the predetermined circle and the latter in the periphery of the central region. The nozzle holes include outputting nozzle holes in the peripheral region and at least one cooling nozzle hole in the central region. Fuel through the outputting nozzle holes contributes to engine output. A smaller amount of fuel than a fuel amount through the outputting nozzle hole is injected through the cooling nozzle hole to cool the central region. A ratio of a second total fuel amount through the cooling nozzle hole to an overall total fuel amount ranges from 0.05 to 0.37.

Abstract: The braking method for an aircraft propelled by at least one ducted fan jet engine, the latter comprising a fan, a jet engine core in which the primary flow circulates, a secondary flow exhaust nozzle, encased in a nacelle, comprises the step, in low-power operation, of unloading at least part of the secondary flow so as to reduce the residual thrust of the jet engine without producing any thrust. With the method of the invention, aircraft braking can be achieved without any thrust reverser device using the braking force generated by the drag of the jet engine or engines completed by reduction of residual thrust by unloading the secondary flow.

Abstract: This patent concerns VTOL propulsion systems that develop a forward flow of air through the air intake duct(s), by the methods of a internal duct system, reversing the rotation of the fan, or a variable pitch (thrust reversing) fan.

Abstract: An apparatus for providing propulsive power that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which the fuel is introduced. The swirl generator effects a toroidal outer recirculation zone and a central recirculation zone, which is positioned within the outer recirculation zone. These recirculation zones are configured in a backward-flowing manner that carries heat and combustion byproducts upstream where they are employed to continuously ignite a combustible fuel/oxidizer mixture in adjacent shear layers. The swirl generator is compatible with the throttle range of conventional gas turbine engines, provides smooth combustion with no instabilities and minimum total pressure losses, enables significant reductions the in L/D ratio of the combustor and is readily packaged into various applications.

Abstract: A pneumatic inhaler that is able to deliver a controlled burst or dose of aerosol from a reservoir of liquid medication. The inhaler is suitable for the aerosolization of liquid medication that is in solution or suspension form. The inhaler is also ideal for the delivery of unique and specialty liquid medications in short aerosol bursts because no additional formulation development is needed and has the further advantage of being able to deliver multiple medications, as mixed by the patient, doctor, or pharmacist, with a single burst at a repeatable output. Because medication and propellant are not mixed until aerosolization occurs, the inhaler is appropriate for more pharmaceutical agents than the current inhalers available and at a substantial cost savings.

Abstract: A thrust reverser system includes one or more actuators each having an integrated locking mechanism that prevents unintended actuator movement, and thus unintended thrust reverser movement. Each of the actuators with the integrated locking mechanism includes a housing, a drive shaft, and a lock. The drive shaft includes an outer surface, is rotationally mounted within the housing, and is operable, in response to the operation of the one or more motors, to rotate in a first rotational direction, to thereby move the thrust reverser to the deploy position, and a second rotational direction, to thereby move the thrust reverser to the stow position. The lock is movably mounted within the housing and is operable to move between at least a first position and a second position, and includes at least a side surface and a bottom surface. One or more gears are provided on the outer surface of the drive shaft, each of which is adapted to mesh with gears that are operably coupled to the thrust reverser.