Abstract: This actuator for an aircraft engine nacelle mobile structure (9) comprises a motor (1) intended to be mounted on a fixed part of the said nacelle, an endless screw (21) able to be turned by this motor (1), a slideway (5) intended to be connected to the said mobile structure (9) and comprising a nut (29) in mesh with the said endless screw, and a first ball end (15) allowing an angular offset between the axis of the said endless screw (21) and the said slideway (5). This actuator is notable in that it comprises a sleeve (19) able to accommodate the said screw (21) and extending with clearance inside the said slideway (5), the said nut (29) being mounted on that end of the said sleeve (19) that is closest to the said motor (1), and the said first ball end being interposed between the other end of the said sleeve (19) and the said slideway (5).

Abstract: A thrust reverser actuation system (TRAS) for a case assembly of an aircraft is provided. The TRAS includes a fuel-driven motor; one or more actuators coupled to the fuel-driven motor; and a transcowl coupled to the actuators such that the fuel-driven drives the transcowl during operation.

Abstract: A method of assembling a thrust reverser assembly for use in an aircraft gas turbine propulsion system. The method includes coupling a translating cowl to a fixed cowling, such that the translating cowl at least partially covers an engine, and is movable between an open position and a closed position. A rod end assembly is coupled to the translating cowl and an actuator is coupled to the rod end assembly, such that the actuator is movable between a first position and a second position. A torque bracket is coupled to the rod end assembly. The torque bracket includes at least two arms that each extend outward from the rod end assembly, such that a bending loading induced to the rod end assembly is induced to the translating cowl by the torque bracket.

Abstract: A nacelle includes a downstream structure having an outer structure, a concentric inner structure surrounding a downstream portion and an upstream section having a relatively small diameter and a downstream section having a relatively large diameter, the inner and outer structures define an annular flow channel. The nacelle includes a guiding system for connecting the inner structure and downstream portion or a portion of a suspension mast, the system combines a translation and rotation movement of at least a portion of the inner structure between a working position, where the inner structure is used as a cowling for the turbojet downstream portion, and a maintenance position where the inner structure exposes the turbojet downstream portion and enable movement of the portion of the inner structure along the profile of the upstream section having a relatively small diameter, and the downstream section having a relatively large diameter.

Abstract: An aircraft nacelle in which a power plant is arranged delimits a duct for a flow which assists the thrust. The nacelle includes a device for reducing, canceling, or reversing the thrust that includes at least one flap that can have an active position in which it deflects—in the direction of a radial opening—at least a portion of the flow and an at-rest position in which the flap does not interfere with the flow, whereby the wall of the nacelle delimiting the duct includes at least one moving part that can occupy a first position in which it is interposed between the flow to be deflected and the flap and another position in which it releases the flap so as to allow the flap to change position and to move from the at-rest position to the active position.

Abstract: A gas turbine engine system includes a first nozzle section associated with a gas turbine engine bypass passage and a second nozzle section that includes a plurality of positions relative to the first nozzle section. In at least one of the positions, there is a gap between the first nozzle section and the second nozzle section. A movable door between the first nozzle section and the second nozzle section selectively opens or closes the gap.

Abstract: A variable area fan nozzle for a high-bypass gas turbine engine includes a first track slider movable relative to the hinge beam along a first interface. A second track slider is movable relative to the first track slider along a second interface that includes a bearing assembly. A VAFN cowl is mounted to the second track slider.

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 thrust reverser nozzle for a gas turbine engine nacelle includes opposite and asymmetrically pivoting first and second doors defining a nacelle aft section, first and second trailing edges of the first and second doors adjacent to a propulsive jet nozzle outlet of the nacelle, the doors being pivotable simultaneously between a stowed position and a deployed position such that the first trailing edge is positioned behind the second trailing edge when the doors are in the deployed position, and the first and second fairings attached to the first and second doors in relative fixed positions to the first and second doors respectively. Male contour middle portions of the first fairings may complementarily match female contour middle portions of the second fairings and are received within the female contour middle portion when the doors are in the stowed position. The fairings may be removably attached to the doors.

Abstract: A jet propulsion unit of an aircraft, which comprises a turbofan engine (3) faired by a nacelle (1), further comprising a thrust reverser device in two parts: one part and including a means for flowing back the air (15) towards the outside of the propulsive unit, in a first angular sector of the nacelle; one part including internal backflow means which can be removed and controlled, suitable for channeling the secondary air flow, circulating in a secondary duct between the propulsive unit and the nacelle, in a second angular sector of the nacelle such as to offset the latter angularly in the secondary duct towards some external thrust reverser means.

Abstract: A nacelle for a turbojet engine of an aircraft is provided that includes a fan case, an internal structure positioned upstream from the fan case, and a thrust reverser positioned downstream from the fan case. The thrust reverser includes a cowl delimiting an external line (LE) and including two removable half cowls. A device for absorbing circumferential stresses are shaped so as to lock the half cowls in the closed position when it occupies a locking configuration on the one hand and for allowing the opening of the half cowls when it occupies an unlocking configuration on the other hand. The stress absorbing device is positioned under an upstream portion of a pylon and is exclusively attached to the half cowls in order to allow the opening of the two half cowls independently of the opening/closing of an external fan cowl.

Abstract: A nozzle for use in a gas turbine engine includes a nozzle door having a first end, a second end opposed from the first end, and a first pivot on the door between the first and second ends. A linkage connects to the nozzle door and to an actuator. The actuator is selectively operative to move the linkage about a second pivot to in turn move the nozzle door about the first pivot between a plurality of positions, such as stowed, intermediate, and thrust reverse positions to influence bypass airflow through a fan bypass passage. The fan bypass passage has a radially outward side defined by a nacelle in at least one position. At least a portion of the nozzle door is radially outward of the nacelle and includes a lip extending from the nozzle door between the first pivot and one of the first end and second end.

Abstract: A nacelle assembly includes an inlet lip section and an airfoil adjacent to the inlet lip section. The airfoil is selectively moveable between a first position and a second position to adjust the flow of oncoming airflow and to influence an effective boundary layer thickness of the nacelle assembly.

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 variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating nozzle segment having a forward edge and a first end. The nozzle segment is movably disposed behind the aft edge such that an upstream bypass flow exit is defined between the aft edge and the forward edge when the nozzle segment is in a deployed position. A deflector is disposed between the aft edge and the forward edge proximate to the first end. The deflector substantially prevents bypass flow from exiting the upstream bypass flow exit in a region that is proximate to the first end.

Abstract: A thrust reverser includes a slider movable along an actuator shaft. An inner linkage is mounted to the slider and the inner thrust reverser door and an outer linkage is mounted to the slider and the outer thrust reverser door.

Abstract: A fan case of a gas turbine engine includes a fan blade containment section defined about an engine axis, a thrust reverser cascade section downstream of the blade containment section and a Fan Exit Guide Vane section downstream of the thrust reverser cascade section.

Abstract: A control system of a hydraulic type for a thrust reversal device with which a jet engine nacelle is equipped, and associated with a nozzle variation device, is provided by the present disclosure. The control system includes at least one additional control unit hydraulically connecting actuators together, wherein hydraulic supply lines from the control unit in a nozzle mode and from the control unit in a reverser mode are then able to communicate hydraulically with each other. A plurality of control valves are laid out so that when the unit for driving the actuators in a nozzle mode is active, a corresponding hydraulic signal controls the valves of the control unit in a position such that the hydraulic supply lines of the actuators from the driving unit according to a reverser mode are cut off.

Abstract: A turbine engine includes an engine core bounded by a bypass duct, a first portion of the bypass duct defined by a fan casing having a radially inner wall and a radially outer wall, a second portion of the bypass duct defined by a radially inner wall and a radially outer wall, a third portion of the bypass duct provided as at least one access door comprising a flow guide structure; and a thrust reverser mechanism coupled to the fan casing.

Abstract: An engine unit for an aircraft including an engine, a device for hooking the engine, and a nacelle surrounding the engine and provided with fan cowls, the device for hooking including a rigid structure and a front aerodynamic structure whereon the fan cowls are articulated, the front aerodynamic structure including a cradle with a rear mechanism of hooking mounted on the rigid structure. The cradle also includes a front mechanism of hooking mounted on an air inlet of the nacelle.

Abstract: A ducted fan gas turbine assembly has a propulsive fan driven by a core engine. The turbine assembly has an annular bypass duct which receives an airflow from the fan and is bounded on the radially inward side by the core engine and on the radially outward side by an engine nacelle. The turbine assembly has a thrust reverser assembly having a vane arrangement including a first set of turning vanes for channelling airflow from the duct in a rearward direction, a second set of turning vanes for channelling airflow from the bypass duct in a forward direction. The thrust reverser assembly includes a plurality of blocker doors which are deployable to block the bypass duct. The nacelle has stationary and movable cowl portions that cooperate with the thrust reverser assembly to provide several operational configurations.

Abstract: The invention relates to a propulsion system including a nacelle and, inside said nacelle, a dual flow turbojet engine that itself includes a fan casing (10) in which a fan and a flow-rectifying vane assembly (15) are located. Said propulsion system includes a reverse thrust means (17) that is located between said fan and said vane assembly (15).

Abstract: A coaxial injection device for injecting and dispersing reagents into a reactor, including an exterior duct for high-velocity gas injection; an outer-middle injector with at least one nozzle for liquid injection; an inner-middle duct for low-velocity gas injection; and an interior injector with nozzle for liquid injection; wherein, the exterior duct is formed by the internal wall of an insert and the external wall of the outer-middle injector; and is located externally to and circumferentially surrounds all other injectors and ducts; the outer-middle injector is formed by two concentric cylinders with end plate and injector nozzles; the inner-middle duct is formed by interior wall of the outer-middle injector and the exterior wall of the interior injector; the interior injector is formed by a cylinder with an endplate, the endplate having a nozzle; thereby ensuring the mixing and dispersion of the liquids and gases into the reactor to increase reaction homogeneity, reaction efficiency, reactor efficiency and

Abstract: An integrated variable area fan nozzle (VAFN) and thrust reversing actuation system (TRAS) system includes movable surfaces for adjusting an exit area for bypass flow and cowls moved for directing discharge flow in a reverser manner. The movable surfaces of the VAFN and TRAS systems are both coupled for movement by a common actuator arrangement. A power drive unit drives each of the actuators on each of the actuators through a gearbox or other linkage such that one common motor or motor combination is utilized for driving all of the actuators. A series of redundant and separately actuateable locks control deployment of the surfaces of the thrust reverse system such that thrust reversing system can move to an open or deployed position only in response to each of the locks being actuated to an unlocked condition.

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: A method and system suitable facilitating the connection and disconnection of a thrust reverser assembly to a fan case of a nacelle of a gas turbine engine. The method and system entail operating a clamping system to simultaneously engage and disengage flanges associated with the fan case and flanges associated with the fixed structure of the thrust reverser assembly. The clamping system includes a plurality of over-center clamping mechanisms, each of which is movable to simultaneously clamp together complementary flanges of the thrust reverser assembly and the fan case.

Abstract: Latch beams and hinge beams of an aircraft thrust reverser and a method for manufacturing the beams. The latch and hinge beams may comprise a plurality of hollow composite tubes joined with a plurality of machined metal fittings in alternating succession. The metal fittings may comprise at least one of hinge fittings and latching fittings. The latch and hinge beams may further comprise slider tracks configured to slidably attach to a translating sleeve of the thrust reverser. The hinge beams may each be rotatably attached to an engine strut or pylon of the aircraft, and the latch beams may each be mechanically latched with each other. Each of the latch and hinge beams may also be fixedly attached to an inner engine cowling of the thrust reverser.

Abstract: A thrust reverser comprises a translating sleeve, a torque beam, a plurality of cascades, a plurality of blocker doors, and a plurality of actuators. The translating sleeve is positioned at the rear of an aircraft nacelle and is translated rearward during thrust reverser deployment. The torque beam is positioned within the nacelle and configured to prevent airflow into the nacelle during thrust reverser deployment. The plurality of cascades are positioned around the circumference of the torque beam during thrust reverser stowage and are translated rearward during thrust reverser deployment. The plurality of blocker doors are positioned in alignment with the plurality of cascades and direct airflow through the plurality of cascades during thrust reverser deployment. The plurality of actuators are coupled to the forward edge of the sleeve and configured to translate the sleeve rearward during thrust reverser deployment.

Abstract: An inner fixed structure of a thrust reverser includes an inner skin, an outer skin, a cellular core disposed between the inner skin and the outer skin, and at least one crack and delamination stopper extending radially between the inner skin and the outer skin.

Abstract: A gas turbine engine system according to an exemplary aspect of the present disclosure may include a core engine defined about an axis, a fan driven by the core engine about the axis to generate bypass flow, and at least one integrated mechanism in communication with the bypass flow. The bypass flow defines a bypass ratio greater than about six (6). The at least one integrated mechanism includes a variable area fan nozzle (VAFN) and thrust reverser, and a plurality of positions to control bypass flow.

Abstract: A rear fan case for a gas turbine engine includes a main body and a discrete joining arrangement mounted on the outside of the main body towards its rear end. The joining arrangement provides a substantially radial groove around the main body, which can receive a joining blade on a thrust reverser unit to form a joint between the rear fan case and the thrust reverser unit. The joining arrangement may be made of metal while the main body is made of composite material. Features may be provided to ensure proper alignment and location of the joining arrangement.

Abstract: An example method of replacing an aperture in a component includes placing layers of a filler material into a first aperture. The layers of the filler material arranged in a stacked relationship relative to each other within the first aperture. The method cures the filler material and establishes a second aperture that is at least partially defined by the filler material.

Abstract: The invention relates to a method for controlling at least one actuator for actuating the cowlings of a thrust inverter in a turbojet engine, the actuator being driven by an electric motor including a relative position sensor providing information on the evolution of the movement thereof, wherein the motor is controlled based on the instantaneous position of the cowling in at least one portion of the movement thereof between an open position and a closed position, the instantaneous position of the cowling being determined from at least one reference position absolute data and relative position data relative to said reference position provided by the relative position sensor of the motor, wherein in case the actuation is resumed after an interruption, a new determination of the reference position is initiated.

Abstract: The method of the invention for monitoring a thrust reverser of a turbojet having an actuator controlled by an electric motor consists in determining a maintenance notice from a weighted combination of provisional notices, each provisional notice relating to a category of parameters associated with at least one phase of an operating cycle of the reverser, the category being selected from a category of parameters representative of a duration of said phase, of an energy seen by the motor during said phase, of a torque seen by the motor at a predefined instant of said phase, and of a duration during which the setpoint speed of rotation and the measured speed of rotation of the motor differ during said phase, each provisional notice being generated by analyzing values obtained during at least one cycle for at least one parameter of said category relative to a degradation threshold.

Abstract: A fan cowl support for an aircraft having an engine pylon, an engine fan case and an engine fan cowl. The fan cowl support includes a support having a forward end connected to the engine fan case and an aft end connected to the engine pylon. At least a portion of the engine fan cowl is connected to the support.

Abstract: An example core nacelle for a gas turbine engine includes a core cowl positioned adjacent an inner duct boundary of a fan bypass passage and having a pocket and an airfoil received within the pocket. The airfoil is moveable between a first position and a second position to adjust a discharge airflow cross-sectional area of the gas turbine engine.

Abstract: A turbofan engine includes a fan variable area nozzle having a multiple of vents through a fan nacelle and a sleeve system movable relative to the vents by an actuator system. The fan variable area nozzle changes the effective area of the fan nozzle exit area to permit efficient operation at predefined pressure ratios. The vents include a grid structure which directs and smoothes the airflow therethrough as well as to reduce noise generation.

Abstract: A power unit for providing propulsive thrust includes an efflux duct defining a first fluid flow path along which gaseous fluid travels for discharge from a first fluid exit opening to provide propulsive thrust. The power unit also has a thrust reversing structure which, when in a deployed position, redirects the flow of gaseous fluid along a second fluid flow path to discharge from a second fluid exit opening to provide reverse thrust. The thrust reversing structure includes longitudinally translating cowl portions, which are moveable from a stowed position to the deployed position where the translating cowl portions block a major portion of the first fluid exit opening to cause gaseous fluid to efflux from the second fluid exit opening. The translating cowl portions move in a generally longitudinal direction towards the deployed position along a path which is inclined to the power unit axis.

Abstract: A thrust reverser assembly for use in a turbofan engine assembly. The engine assembly includes a core gas turbine engine and a core cowl which circumscribes the core gas turbine engine. A nacelle is positioned radially outward from the core cowl to define a fan nozzle duct between the core cowl and a portion of the nacelle. The nacelle includes a stationary cowl. The thrust reverser assembly includes a first translating cowl that is slidably coupled to the nacelle. The first translating cowl is positionable with respect to the stationary cowl. A second translating cowl is slidably coupled to the nacelle such that the first translating cowl is positioned between the stationary cowl and the second translating cowl. The second translating cowl is positionable with respect to the first translating cowl. A positioning assembly is coupled to the first translating cowl. An actuator assembly is operatively coupled to the second translating cowl for selectively moving the second translating cowl.

Abstract: A thrust reverser for a jet engine comprises a translating wall section moveable between a stowed position and a deployed position. The translating wall section is adjacent an annular fan duct wall or other fixed portion of the jet engine when in the stowed position and is separated from the annular fan duct wall when in the deployed position, thereby creating an aperture through which a fluid stream passes. A fluid flow reverser element directs the fluid stream in a direction generally forward relative to the jet engine when the translating wall section is in the deployed position. The fluid flow reverser element extends only partially into the fluid stream such that only a first portion of fluid of the fluid stream engages the fluid flow reverser element. A second portion of the fluid stream is entrained in the first portion and is thereby directed forward relative to the jet engine.

Abstract: There is provided an actuation system for a gas turbine engine including a thrust reverser and a variable area fan nozzle. The system has a plurality of linear actuators each having a first outer piston concentric with a second inner piston. The first outer piston is operatively connected to a thrust reverser. The second inner piston is operatively connected to a variable area fan nozzle. The system further has a piston lock assembly for selectively locking the first outer piston to the second inner piston. The system further has a control system coupled to the plurality of linear actuators for operating the variable area fan nozzle between a stowed position and a deployed position.

Abstract: A system to provide differential movement between a first surface, a second surface and a fixed surface includes a first surface movable between a first position and a second position; a second surface movable with the first surface and further movable beyond the first surface; a shaft connected to the second surface to move the second surface; and a drive unit connected to the fixed surface to drive the shaft to move the second surface relative to the first surface and to allow the shaft to move through the drive unit when the second surface is being moved by the first surface.

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: A slider apparatus integral with a slidable member and a method for integrating the slider apparatus with the slidable member. The slider apparatus integrated with the slidable member may be configured to slidably couple with and be structurally supported by a fixed structure. The slider apparatus may comprise a primary slider component made of composite material and at least one chamfered element bonded to the primary slider component. The slidable member may comprise the slider apparatus, a core assembly, a plurality of composite material plies wrapped around the slider apparatus and core assembly and cured therewith, and at least one low-friction slider shoe removably attached to the primary slider component outward of the plurality of composite material plies.

Abstract: A fluid-powered thrust reverser actuation speed control system and method are provided. A drive fluid is supplied to a fluid-powered drive mechanism that is coupled to a thrust reverser movable component to thereby move the thrust reverser movable component at a first movement speed. A determination is made as to when the thrust reverser movable component attains a predetermined position. In response to the thrust reverser movable component attaining the predetermined position, the drive fluid supplied to the fluid-powered drive mechanism is controlled to thereby move the thrust reverser movable component at a second movement speed that is less than the first movement speed.

Abstract: A nacelle for double-flow engine with a cowling and at least one thrust reverser, the thrust reverser having an internal door and an external door arranged in the cowling, and means for simultaneously shifting these doors between a stable retracted position in which the doors are integrated in the cowling and a stable deployed position in which the internal and external doors are positioned at least partially inside and outside of the nacelle, respectively, to deflect the secondary flow and to generate a thrust reversal. The means for simultaneously shifting the doors comprise an actuator, one extremity of which is linked to one of the doors to shift this door between the extreme positions, and at least one linkage element linked to the doors to pivot by its extremities, so that the shifting of the door entails the shifting of the other door between these extreme positions.

Abstract: The invention relates to a control method for opening or closing a turbojet engine thrust reverser (1) by using at least one mobile cowl (2) displaceable by means of at least one electric motor (7) consisting in analyzing at least one parameter representative for a pressure in the turbojet engine jet and in carrying out an operating sequence in which the operating parameters of the electric motor (7) are adjusted to a situation.

Abstract: A nozzle for use in a gas turbine engine includes nozzle doors coupled with a fan nacelle wherein the nozzle doors move in unison between a plurality of positions to influence a bypass airflow through a fan bypass passage. A linkage connects the nozzle doors and an actuator. A louver section coupled with the linkage moves in unison with the nozzle doors between a plurality of louver positions to direct a portion of the bypass airflow in a selected direction.

Abstract: A thrust reverser assembly includes a first cowl member and a second cowl member repositionable relative to the first cowl member and operable to open a gap between the first cowl member and the second cowl member. A movable member is in supported connection with the second cowl member. The movable member is passively actuatable to move between a generally axially extending disposition and a generally radially extending disposition to direct bypass airflow of a turbofan engine.

Abstract: An assembly for a turbofan engine includes a first cowl member comprising an aft portion and a translatable cowl member comprising a forward portion configured to be received within the aft portion. The translatable cowl member is configured to be moveable with respect to the first cowl member between a first operational position wherein the forward portion is received within the aft portion of the first cowl member, and a second operational position wherein a smaller portion of the forward portion is received within the aft portion than in the first operational position. The translatable cowl member is configured to cooperate with a core cowl of the turbofan engine to define a portion of a fan duct having an exit nozzle, and the translatable cowl member is configured to define a flow control location near the exit nozzle that is associated with a controlling fan duct area.