Abstract: The invention relates to a flap system for an aircraft high lift system or an engine actuation with a rotary shaft system, one or more drive stations as well as elements for transmitting the drive energy from the rotary shaft system to the one or more drive stations, wherein at least one drive station includes at least two independent load paths with at least one rotational transmission each for actuating the flap kinematics, and per load path at least one mechanically coupling-free synchronization unit is provided for compensating regular load fluctuations between the load paths. The invention furthermore relates to a method for monitoring a flap system with at least two redundant load paths which each comprise at least one rotational transmission, wherein it is cyclically checked whether the difference of the output-side torques of the at least two load paths exceeds a defined threshold value and/or lies within a defined limit range.

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 thrust reverser device for a turbojet engine nacelle includes a mobile cowl movably mounted to translate between a closed position which the mobile cowl covers grids deflecting some of the air flow of the turbojet engine and an open position in which it opens a passage and uncovers the grids. The mobile cowl is associated with a blocking flap to pivot between a retracted position and a blocking position corresponding to the open position of the mobile cowl. The blocking flap is fitted with at least one lever forming a drive mechanism which includes at least one adjustable-stiffness shock absorber.

Abstract: A high-bypass gas turbine engine includes a variable area fan nozzle with an acoustic system having an acoustic impedance.

Abstract: The control system of the invention includes at least one actuator (6) for a cowling (2), driven by at least one electric motor (7), and control means (9) for the electric motor (7) and the actuator (6). The control system includes an electric circuit (C) that comprises: a plurality of electric components; a plurality of measuring means (16-18) adapted for measuring respectively a characteristic magnitude of an electric component or a group of electric components in the electric circuit; a failure detection means (19) adapted for detecting a failure at a component of the electric circuit when the characteristic magnitude measured at said component exceeds a predetermined value or is in a range of predetermined values.

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: The invention relates to a method for the self-calibration of electric jacks (6a, 6b) capable of actuating a mobile member (2) of a turbojet nacelle (1) and connected to at least one position measuring member, characterized in that it comprises the steps of: moving the jack(s) into a retracted position corresponding to a first position of the mobile member, storing one or more position values fed back by the position measuring member for the jack(s) in said retracted position; moving the jack(s) into an extended position corresponding to a second position of the mobile member; storing one or mom position values fed back by the position measuring member for the jack(s) in said extended position.

Abstract: The invention relates to a linear telescopic actuator for moving a first (10b) and a second (10a) element relative to a stationary element (102). Said actuator comprises a base (101) that is to be connected to the stationary element (102) and is used as a cavity for a first rotationally locked rod (106) which can be translated by a drive shaft (104) that is to be connected to rotational driving means (107). One end (108) of said first rod is to be connected to the first element that is to be moved. The actuator is characterized in that the first rod (106) supports a second rod (117) which is aligned therewith and one end (118) of which is to be connected to the second element that is to be moved. Said second rod (117) can be rotationally locked and can be translated by a second drive shaft (112, 115) which extends through the base and is connected to rotational driving means (113, 111).

Abstract: The invention relates to a rear section (11) of an aircraft nacelle, that comprises two halves (13a, 13b) defining: a central portion (C) for receiving a turbojet engine (7), a cool-air annular passage (31) provided around said central portion (C), and at least one six-hour cavity (15) provided under said central portion (C). The rear section is characterized in that it comprises at least one duct (29a, 29b) for the fluidic communication between said annular passage (31) and said six-hour cavity (15) for maintaining the temperature inside the six-hour cavity (15) within a relatively low range.

Abstract: A nacelle for a turbojet engine includes an air inlet forward section, a median section surrounding a fan of the turbojet engine, an aft section equipped with a thrust reverser system, a power control unit able to convert a high voltage electric supply into an electric supply towards an electromechanical actuator, and a drive unit for the power control unit which is distinct and separate from the latter and has a control input and a drive output to be connected to the power control unit. The thrust reverser system includes a mobile cowl which, under action of an electromechanical actuator, is able to move from a closed position to an open position in which the mobile cowl opens a passage in the nacelle.

Abstract: The present invention relates to an aircraft gas-turbine engine with a core engine surrounded by a bypass duct, with a radially outer engine cowling enclosing the bypass duct and being provided at its rear region with a thrust-reversing device which is moveable relative to the engine cowling, with at least one cooler element extending over at least part of the circumference being arranged in the intermediate area between the engine cowling and the thrust-reversing device.

Abstract: A thrust reverser for a turbojet engine includes a telescopic linear actuator for a moving cowl and a nozzle-forming end part. The telescopic linear actuator has a base attached to a fixed frame, acting as a housing for a first rod prevented from rotating but able to be translationally driven by a first drive shaft connected to a rotational-driver. The first rod is attached by one end to the moving cowl and supports a second rod, which is attached by one end to the nozzle-forming end part that is to be moved. The second rod is prevented from rotating and translationally driven by a second drive shaft passing through the base and connected to a rotational-driver. In particular, the rotational-driver of the rods includes a motor to drive an input shaft of a differential having two output shafts.

Abstract: A nacelle is configured to be coupled to an underside of a wing and forms a clearance space between the nacelle and a leading edge slat of the wing. A portion of an outlet cowling moves longitudinally aft when a reverse thrust configuration is activated and the leading edge slat is deployed toward the nacelle. The outlet cowling also includes another portion located adjacent to the leading edge slat that does not move when the reverse thrust configuration is activated and thus maintains its clearance space from the leading edge slat.

Abstract: The present disclosure relates to a thrust reverser including at least one translatably movable cowl capable of alternately shifting between a closed position in which same ensures the aerodynamic continuity of the nacelle and which covers the deflecting means, and an open position in which same opens a passage in the nacelle and uncovers the deflecting means, said thrust reverser likewise including at least one variable nozzle section arranged in the extension of the movable thrust-reversing cowl and provided with at least one locking means capable of engaging with a complementary locking means of the movable reversing cowl so as to optionally mechanically link the movable nozzle section of the movable reversing cowl.

Abstract: A control system for controlling a plurality of distinct functions of a turbojet engine, each function being associated with a respective actuation device. The system includes: an electric motor adapted to supply mechanical energy to each of the actuation devices; an electronic control unit for the electric motor; and at least one switching device interposed between the motor and the actuation devices, the switching device(s) serving to distribute the mechanical energy supplied by the electric motor selectively to one of the actuation devices.

Abstract: A turbojet engine with a fan and a nacelle element forming the secondary duct downstream of the fan is provided. The turbojet engine includes an intermediate casing with an outer shroud to which the nacelle element is fixed by a connecting member. The connecting member includes a cylindrical element secured to the shroud while at the same time being capable of a rotational movement with respect to the axis of the engine and connected to the nacelle element by a bayonet-type fitting.

Abstract: A turbine engine system includes a nacelle and a thrust reverser. The nacelle includes a first portion and a second portion that are arranged along an axis. The second portion of the nacelle moves axially relative to the first portion of the nacelle. The thrust reverser includes a blocker door and a linkage that links the blocker door to the first portion of the nacelle. The blocker door is located within and pivotally connected to the second portion of the nacelle.

Abstract: A method of varying a fan duct throat area of a gas turbine engine may include non-pivotably moving a fan nozzle outwardly relative to a longitudinal axis of the gas turbine engine during axially aft translation of the fan nozzle without activating a thrust reverser.

Abstract: An apparatus and method comprising a fan nozzle sleeve, a plurality of slider mechanisms, and a fan nozzle actuator system. A flow of gases generated by an engine moves through and exits the engine at an aft end of the fan nozzle sleeve. The plurality of slider mechanisms is configured to connect the fan nozzle sleeve to a translating sleeve for a thrust reverser for the engine. The fan nozzle actuator system is configured to activate the plurality of slider mechanisms to move the fan nozzle sleeve in an aft direction to change a direction of the flow of gases exiting the engine at the aft end of the fan nozzle sleeve.

Abstract: A thrust reverser for aircraft turbojet engine nacelle includes at least one upstream door and a downstream door. The upstream and downstream doors move in concert between a direct jet position and a reverse jet position. In the direct jet position, two doors are closed, and in the reverse jet position the two doors are open and able to deflect a part of a cold air flow circulating inside the nacelle. The thrust reverser further includes a curved downstream edge of the upstream door to make adapted a part of cold air flow circulating between an upper camber of the upstream door and a lower camber of the downstream door.

Abstract: A thrust reverser assembly and operation suitable for high-bypass turbofan engines. The thrust reverser assembly includes a translating cowl mounted to a nacelle of an engine and adapted to translate in an aft direction of the engine. The translating cowl has a radially inner wall that defines a radially outer flow surface of a bypass duct of the engine. The thrust reverser assembly includes blocker doors axially guided adjacent first ends thereof by a fixed structure and pivotally and slidably connected along lengths thereof to the inner wall of the translating cowl so that translation of the translating cowl in the aft direction causes each blocker door to move from a stowed position to a deployed position as a result of the blocker door sliding at its first end relative to the fixed structure and sliding along its length relative to the inner wall of the translating cowl.

Abstract: A thrust reverser for the nacelle of a turboreactor includes at least one fixed front frame that can be mounted downstream of a fan casing of the turboreactor and directly or indirectly supports at least one flow deviation vanes, in which at least part of the flow deviation vanes can be detached from the front frame and moved in translation independently therefrom when a maintenance operation is being carried out on the reverser.

Abstract: A virtual blocker door for use in an aircraft thrust reverser is provided. The virtual blocker door may be capable of creating a wall of air to inhibit fan air flow through a fan air duct. The wall of air may direct the fan air flow through a cascade to provide a reverse thrust. Moreover, the virtual blocker door provides for improved aerodynamic efficiency in the fan air duct by replacing traditional brackets, drag links, and doors with a wall of air.

Abstract: The present invention relates to a nacelle (1) for a jet engine (4) comprising a forward air inlet section (5), a mid-section (6) intended to surround a jet engine fan, and an aft section (9), at least one portion forming the aft section being connected to the mid-section via an at least partially peripheral radial knife-edge (31) capable of engaging by complementarity of shape with a corresponding groove (32) belonging to a portion (6a) of the mid-section, characterized in that the knife-edge comprises at least one reinforcing segment (35, 36) situated in a region for accommodating high loads, said reinforcing segment being made from a material which is stronger than the remainder of the knife-edge and tailored to the loads which are to be borne by said segment in this region.

Abstract: A monitoring system and a monitoring method applied to the monitoring system, in which the monitoring system includes detectors detecting a state of a turbojet thrust reverser, a monitoring computer device controlling the reverser monitored by the computer as a function of information from the detectors provided to the computer by way of the control device, and a device regulating the turbojet monitored by the computer as a function of the information from the detectors provided to the computer by way of the control device.

Abstract: A split cascade comprises a fixed portion and a translating portion. The translating portion may be coupled to, mounted on, or otherwise attached to a translating sleeve of an aircraft nacelle. The fixed portion and the translating portion form a cascade assembly, in response to the translating sleeve being in the active position (e.g., when the thrust reverser is active). Moreover, the split cascade provides a smaller overall package when stowed (e.g., when the translating sleeve is in a forward position and seals or joins the nacelle), providing more room in the nacelle for access and equipment.

Abstract: In various embodiments, the thrust vectoring systems described herein create variable reverse thrust during a landing event. The reverse thrust may be varied based on manual inputs, dynamically changing operating events, or a landing duty cycle. In various embodiments, the thrust vectoring systems comprise a movable shelf that is capable of adjusting a directing a fluid flow to create a variable reverse thrust which may reduce the risk of foreign object ingestion in the engine at lower ground speeds.

Abstract: An arrangement is provided that includes a thrust reverser flap link rod on an internal fixed structure of a turbojet engine nacelle. The link rod is connected to the internal fixed structure by an elastic means that is a spring.

Abstract: A guide system for translating components of an aircraft engine nacelle includes a track assembly and a slider assembly. The track assembly includes a track guide member and a track liner engaged therewith. The track guide member includes a track channel configured to receive the track liner. The track liner defines an interior surface and includes a projection portion projecting inwardly of the track channel to define a convex surface. The slider assembly translatably engages the track assembly and includes a slider member having a head portion configured to be received within the track channel. The head portion defines a concave surface substantially corresponding to the convex surface of the track liner and is configured to mate therewith. The slider member further includes an extension portion extending from the head portion and outwardly of the track assembly.

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. A lip extends from the nozzle door between the first pivot and one of the first end and second end.

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 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 reverse flow combustor has an inlet end. A flowpath extends downstream from the inlet end through a turn. The turn directs the flowpath radially inward and reversing an axial flow direction. A large exit duct (LED) is along the turn. A small exit duct (SED) is along the turn and joined by a joint to a mounting structure to resist separation in a first axial direction. The joint comprises: a first surface on the SED facing partially radially inward; and a mounting feature engaging the first surface.

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: This strut (9), designed to support an aircraft turbojet engine, has, on the one hand, a connecting part (11) for connection between the casing (1) of the fan (3) or the casing of the gas generator (5) of the said turbojet engine and a wing of the said aircraft and, on the other hand, a Y-shaped box-section part (19), secured to the said connecting part (11) and designed to form the upper part of the inner fixed structure of the said nacelle.

Abstract: A stub frame for a cascade vane thrust reverser structure of an aircraft nacelle is attached to one or more cascade vanes. The stub frame includes an integral primary structure with a C-shaped longitudinal section, a secondary structure acting as a cascade edge and attached to the primary structure at one end, and transverse stiffeners connecting the two ends of the primary structure.

Abstract: A door for a thrust reverser of a nacelle of an aircraft being pivotally amounted on a fixed structure of the nacelle, in particular, the door being fitted with deflectors deflecting air flow is disclosed. The deflectors are arranged at an upstream end of the door and mounted such that they can move in a deflection plane perpendicular to the plane of the door. Each deflector is associated at its ends with an articulation arm capable of rotating about a pivot axis perpendicular to the deflection plane, allowing the deflectors to move in a straight line in the deflection plane. The present disclosure also relates to a thrust reverser system including the door and a fixed structure on which the door is pivotally mounted between a closing position and an open position.

Abstract: A locking/unlocking device for a thrust reverser with sliding cover and adaptive nozzle is provided that includes a fixed pin secured to a fixed structure of the reverser, a first sleeve secured to the sliding cover and able to accommodate the pin, a second sleeve slidably mounted on the first sleeve, a third sleeve secured to the adaptive nozzle and slidably mounted on the second sleeve, first locking means able to lock the first sleeve with respect to the pin, second locking means able to lock the second sleeve with respect to the first sleeve, and third locking means able to lock the third sleeve with respect to the second sleeve.

Abstract: A gas turbine engine for mounting under a wing of an aircraft has a propulsor that rotates on a first axis, and an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section. The engine core is aerodynamically connected to the propulsor and has a second axis. A nacelle is positioned around the propulsor and engine core. The nacelle is attached to the wing of the aircraft. A downstream end of the nacelle has at least one pivoting door with an actuation mechanism to pivot the door between a stowed position and a horizontal deployed position in which the door inhibits a flow to provide a thrust reverse of the flow.

Abstract: In one embodiment, a gas turbine engine for mounting to a rear of an aircraft fuselage has a propulsor that rotates on a first axis, and an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section. The engine core is aerodynamically connected to the propulsor and has a second axis. A nacelle is positioned around the propulsor and engine core. The nacelle is attached to the wing of the aircraft. A downstream end of the nacelle has at least one pivoting door with an actuation mechanism to pivot the door between a stowed position and a vertical deployed position in which the door inhibits a flow to provide a thrust reverse of the flow.

Abstract: A thrust reverser for a turbojet aircraft engine nacelle includes a pair of twin doors including an upstream door and a downstream door which is connected to the upstream door by a connecting rod. The thrust reverse also includes an actuating cylinder for operating the upstream door between a direct jet position in which the two doors are closed and a reversed jet position in which the two doors are open and deflects a portion of a cold air stream flowing inside the nacelle. A locking system of the thrust reverser locks the upstream and downstream doors relative to one another by the operation of the actuating cylinder alone.

Abstract: The invention relates to a thrust reverser for a turbofan engine nacelle including a stationary portion (15) downstream from which is mounted at least one cowl (9) movable between a direct-jet position, in which the cowl (9) is aligned with the stationary portion (15), and a thrust-reversal position, in which the mobile cowl (9) is spaced apart from the stationary portion (15) so as to define an opening for the passage of a secondary flow (F), a means for deflecting (16) the secondary flow (F) through the passage opening, an actuator means (45) and a means (24) for guiding the mobile cowl (9) relative to the stationary portion (15), at least a first and a second adjacent cascade vane (13), positioned at an angle (B) relative to the movement axis (A) of the mobile cowl (9), arranged opposite the passage opening such that the deflected secondary flow (F) at least partially passes through the first and second vanes (13) in order to increase the deflection of said secondary flow (F) in the upstream direction, sai

Abstract: An exemplary gas turbine engine assembly includes a thrust reverser that is selectively moveable between a stowed position and a thrust reversing position. The thrust reverser includes an outer surface having a first outer surface area when the thrust reverser is in the stowed position and a second, smaller outer surface area when the thrust reverser is in the thrust reversing position.

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: Disclosed is a structure for a grid-type thrust reverser, the reverser including an upper beam, a lower beam, and two half-frames fastened to the upper beam and the lower beam, and hollow structures defined by the two half-frames, the hollow structures each having upper ends and lower ends, wherein at least one of the upper and lower beams includes integral parts delimited by walls, the walls forming casings fitted into and blocking corresponding ends of the half-frames.

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 mobile cowl for a cascade-type thrust reverser includes an interior wall having an anterior zone, a movably mounted shutter and a link rod of which one end is connected to the shutter to actuate the shutter from one position to other. One of the positions may be a direct-jet position in which the shutter is situated facing the anterior zone, and other position may be a reverse-jet position in which the shutter is situated away from the anterior zone. The interior wall has, in the anterior zone, a part able to allow the link rod end to move beyond a normal position in the event of abnormal movements of the link rod end, without wrecking the interior wall.

Abstract: A thrust reverser system and operation suitable for high-bypass turbofan engines. The thrust reverser system includes a cascade system adapted to be translated with a translating cowl in an aft direction of an engine to expose a circumferential opening. The cascade system is deployed from a stowed position as the translating cowl and the cascade system are translated in the aft direction. During deployment of the cascade system, a fore end thereof translates in the aft direction and an aft end thereof initially translates in the aft direction and then subsequently rotates about the fore end so that further translation of the cascade segment in the aft direction causes the cascade segment to move to a deployed position and divert bypass air within a bypass duct of the engine through the circumferential opening.

Abstract: A bypass turbojet engine nacelle that forms a fan casing includes a first, upstream, streamlining element and a second streamlining element that forms a jet pipe. The second element can move translationally between a position ensuring aerodynamic continuity of the nacelle and a downstream position uncovering flow reversal openings. A thrust reverser device is housed in the nacelle and includes flow reverser flaps and cascades of vanes providing radial guidance for the flow. The cascades of vanes providing radial guidance for the flow can move in translation along the axis of the nacelle between a retracted position into the first steamlining element and an active flow-guidance position, the second streamlining element being secured to the cascades of vanes, the reverser flaps being mounted to rotate about axes that are transverse with respect to the axis of the nacelle and secured to the cascades of vanes.