Abstract: An actuator for an aircraft turbine engine nacelle with a one-piece annular rear part, includes an engine assembly having a nut which is capable of rotating but not of translational movement, and a shaft for turning this nut. The actuator also includes a screw assembly having a screw capable of translational movement without rotating, in mesh with the nut, and a ball joint at one end of this screw intended to be fixed to the annular rear part.

Abstract: An aircraft engine variable area fan nozzle structure disposed abaft a thrust reverser, including a sleeve translatable over a cascade array, comprises two semi cylindrical segments that can be axially translated and radially tilted to enlarge the fan duct exhaust area in order to optimize exhaust pressure and associated noise in high thrust circumstances such as on take-off, and to constrict that area under lower thrust conditions such as cruise. A pair of angularly adjacent segments can be moved by an actuator anchored to the fixed engine framework and independently of the thrust reverser translating sleeve. The tilting movement is imposed by the pivoting links of each segment to carriages that ride in a non-linear trackway secured to a thrust reverser translating sleeve. The actuator can be of a dual concentric type which can independently drive the trust reverser and nozzle segments.

Abstract: A flow control panel in an aircraft engine two-dimensional, convergent/divergent nozzle adjusts a throat area of the nozzle and is configured to be self-sealing, thereby requiring fewer parts and providing a more simplified construction of the throat area of the nozzle.

Abstract: A nacelle drag-link assembly for a thrust reverser of a propulsion system includes a drag-link fitting, a drag link, a coupling assembly, and a vibration damping assembly. The drag-link fitting includes a base region and a coupling socket extending from the base region. The coupling socket has a first coupling aperture and a second coupling aperture. The drag link includes an inner structure end, an outer structure end, and a link body. The outer structure end includes a pivot area to link with a blocker door of the thrust reverser. A coupling assembly is installed through an aperture of the inner structure end and between the first coupling aperture and the second coupling aperture of the coupling socket. The vibration damping assembly is installed in contact with the drag-link fitting and one or more of: the drag link and the coupling assembly.

Abstract: A nozzle system includes a static structure including a multiple of convergent flap rails and a synchronization ring including an inner ring radially spaced from an outer ring via a multiple of struts. The multiple of convergent flap rails extend at least partially between the inner ring and the outer ring.

Abstract: A thrust reverse variable area nozzle system for a nacelle of an aircraft engine system may include a reverse thrust opening disposed in the nacelle, and a thrust reverser door pivotally movable relative to the nacelle for selectively covering the reverse thrust opening, wherein the thrust reverser door is pivotally movable between a first position for completely covering the reverse thrust opening, a second position for partially uncovering a forward portion of the reverse thrust opening and discharging a bypass airflow through the forward portion of the reverse thrust opening in a forward direction, and a third position for partially uncovering an aft portion of the reverse thrust opening and discharging the bypass airflow through the aft portion of the reverse thrust opening in an aft direction.

Abstract: A nozzle including a frame having a plurality of deflecting elements arranged in an array, the array extending about a longitudinal axis, and a skin positioned over the frame.

Abstract: This disclosure relates to a variable area nozzle of a gas turbine engine. The variable area nozzle includes, among other things, a control unit, a translatable structure, and a plurality of actuators configured to adjust the position of the translatable structure. The plurality of actuators are fluidly coupled to a common fluid source. The control unit is configured to provide instructions to at least one of the actuators to compensate for an asymmetric load from the translatable structure.

Abstract: A gas turbine engine has a core engine and a nacelle having a cowl translatable along the axis of the engine from a stowed position to a deployed position, A thrust reverser cascade extends circumferentially about the engine axis. To obviate the need for additional blanking cascades the cowl has a forwardly extending tongue that in the deployed position of the cowl is at the same axial position as the thrust reverser cascade.

Abstract: Systems and methods are provided that employ an IR suppression system to alter the signature of a vessel during a missile engagement with the objective of confusing a seeker of an incoming missile so as to increase the probability that the seeker is seduced by a flare. The flare is launched and IR suppression is enabled or set to an increased level, with coordinated timing, such that the IR signature of the target vessel is changed at about the same time that the flare is launched.

Abstract: A fan section for an engine has a fan which rotates about an axis, the fan has an inlet for ingesting ambient air, and a non-axisymmetric nozzle for providing the fan with non-uniform back pressure.

Abstract: A feed injector for a circulating fluid bed reactor is fitted with a discharge nozzle with a circular, radially notched discharge orifice to improve the surface-to-volume ratio of the spray pattern formed by the nozzle. The feed injector is useful for injecting fluids into various types of circulating fluid bed reactors in which good contact between the components of the fluidized bed and the injected fluid is required. It is particularly useful in fluid coking reactors.

Abstract: A bypass turbine engine including: an inner casing, an inter-duct casing, and an outer casing so as to define a primary duct between the inter-duct casing and the inner casing, and a secondary duct between the inter-duct casing and the outer casing; a rotary shaft including a movable fan including radial blades of which free ends face the outer casing of the turbine engine to compress an air flow in the secondary duct; a plurality of variable-pitch radial stator vanes mounted upstream of the movable fan so as to deflect the incident axial air prior to it being axially rectified by the movable fan in the secondary duct; and a system for individually regulating the pitch of the variable-pitch radial vanes if heterogeneity of the air flow in the secondary duct is detected, is provided.

Abstract: A bypass turbine engine including: an inner casing, an inter-duct casing and an outer casing so as to define a primary duct between the inter-duct casing and the inner casing, and a secondary duct between the inter-duct casing and the outer casing; a rotary shaft including, at an upstream end, a movable fan with radial blades of which the free ends face the outer casing to compress an air flow at least in the secondary duct; a plurality of variable-pitch radial stator vanes mounted upstream of the movable fan so as to deflect the incident axial air prior to it being axially rectified by the movable fan in the secondary duct; and a system for individually adjusting the pitch of the radial vanes including a single control ring and rods for connecting the control ring to each of said radial vanes, is provided.

Abstract: An actuating assembly for an aircraft engine thrust reverser includes a drive shaft bearing a master pinion; a ball screw bearing a slave pinion engaging with the master pinion; a nut capable of translating over the ball screw as a result of the rotation of the ball screw; an extension tube rigidly secured to the nut and a lock assembly to block the rotation of the drive shaft in a so-called direct jet position of the reverser. The extension tube includes, at its free end, a member for connecting to a portion of the reverser prior to being actuated. In particular, the lock assembly includes an abutment secured to the drive shaft, and a cotter moveable between a locking position and an unlocking position. The reduction ratio (R) between the slave and master pinions is even.

Abstract: Disclosed herein is a blocker door for use in a thrust reverser portion of a nacelle. The blocker door includes a structural frame having a plurality of connected and crossing ribs. The blocker door also includes a front sheet positioned on an airflow side of and attached to the structural frame. The blocker door also includes at least one acoustic core positioned between the ribs of the structural frame and comprising a plastic material.

Abstract: The subject of the disclosure is an aircraft comprising at least one left motor generator, at least one right motor generator, a control device for a jet pipe nozzle with variable cross-section of the aircraft comprising at least one control member powered by a first airplane electrical power supply linked to at least one right or left motor generator, the control member powered by a second electrical power supply linked to an electrical power source of the aircraft independent of the first airplane electrical power supply.

Abstract: One embodiment includes a pivot thrust reverser. The pivot thrust reverser includes a first tandem pivot door subassembly comprising an inner panel and an outer panel. The inner panel and the outer panel are connected so as to rotate simultaneously about respective pivot axes that are each positionally fixed axes relative to the gas turbine engine assembly. A second tandem pivot door subassembly is included, spaced from the first tandem pivot door subassembly and comprising an inner panel and an outer panel. The inner panel and the outer panel are connected so as to rotate simultaneously about respective pivot axes that are each positionally fixed axes relative to the gas turbine engine assembly.

Abstract: An engine system with a multi-gas-generator, tip-turbine driven lift fan with pressurized air circulation control for use on vertical and short-take-off and landing (V/STOL) aircraft is disclosed. Gas generators located around the periphery of the fan drive the fan through action on a fan blade-tip turbine or provide compressed gas (hot or cold) to circulation control devices. Variable pitch fan blades improve part-power cruise performance. Enclosed in a nacelle, the engine employs circulation control to enhance V/STOL performance. In some embodiments, a core cruise turbine gas generator mounted in the center of the fan duct powers the fan during cruise mode. In some hybrid gas and electric power embodiments, the core cruise gas generator is replaced by an electric motor that draws power from a battery in the fuselage. The battery may be charged by an electric generator driven by a gas generator around the periphery of the fan.

Abstract: An apparatus comprises a surface that is configured to be exposed to a fluid stream and a cavity wall that forms at least a portion of a cavity. A first channel opening is formed in the surface, and a second channel opening is formed in the cavity wall. A channel extends from the first channel opening in the cavity wall to the second channel opening in the surface.

Abstract: A variable nozzle is comprised of: an exhaust duct vectoring a flow of the exhaust gas to the aft end; a plurality of primary flaps arranged to define a primary flow path converging toward the aft end, each of the primary flaps being swingably pivoted on the exhaust duct to regulate a degree of opening the primary flow path and including a first section and a second section forming an angle axially outward relative to the first section; and a plurality of secondary flaps arranged to define a secondary flow path in communication with the primary flow path, the secondary flow path being capable of divergent toward the aft end, the secondary flaps being respectively swingably pivoted on the second sections of the primary flaps to regulate a degree of opening the secondary flow path.

Abstract: One embodiment includes a pivot thrust reverser comprising a first tandem pivot door subassembly comprising an inner panel and outer panel connected. A second tandem pivot door subassembly is included comprising an inner panel and outer panel connected. Also included are a first actuator located on a first side of an attachment location to pivot the first tandem pivot door subassembly, a second actuator located on a second side of the attachment location to pivot the second tandem pivot door subassembly, and a third actuator located substantially radially opposite the attachment location to pivot both the first tandem pivot door subassembly and the second tandem pivot door subassembly. The first tandem pivot door is configured to be pivoted from stowed to deployed by the first actuator and the third actuator, and the second tandem pivot door is configured to be pivoted from stowed to deployed by the second actuator and the third actuator.

Abstract: A pivot thrust reverser includes a first tandem pivot door subassembly comprising an inner panel and an outer panel. The inner panel and outer panel are connected by a first sliding rail. A second tandem pivot door subassembly is included comprising an inner panel and an outer panel. The inner panel and outer panel are connected by a second sliding rail.

Abstract: The thrust vectoring apparatus has a nozzle, a jet tab arranged behind the nozzle, a rotation shaft 30 connected to the jet tab, and a gas seal member arranged on an outer circumferential surface of the rotation shaft. The rotation shaft is connected to the jet tab, and has the protrusion in the redial direction out of the rotation shaft on the rear side of the gas seal member. The protrusion restrains that the combustion gas exhausted from the nozzle flows toward the gas seal member.

Abstract: A thrust reverser system deployable from a core cowl is provided. The thrust reverser system may comprise one or more doors that are configured to overlap to reduce leakage and increate reverse thrust while deployed. The doors may be configured to vanes that are configured to split and/or direct airflow.

Abstract: A multi-surface blocker door system for a thrust reverser of an aircraft is provided. The system may comprise one or more first blocker doors coupled to the inner fixed structure. The first blocker doors may be configured to obstruct a fan duct area adjacent the engine. The system may also comprise one or more second blocker doors coupled to a translating sleeve. The second blocker doors may be configured to obstruct a fan duct area adjacent to an inlet of the nacelle.

Abstract: A method and apparatus for reducing noise generated during operation of an engine. In one illustrative embodiment, a nozzle system comprises a first nozzle and a second nozzle at least partially surrounded by the first nozzle. An outer surface of an aft portion of the second nozzle has a shape configured such that a radial cross-section of the outer surface of the aft portion of the second nozzle has a curve that is different from at least one other curve for another radial cross-section of the outer surface of the aft portion of the second nozzle and such that an axial cross-section of the outer surface of the aft portion of the second nozzle has a wavy shape.

Abstract: A gas turbine engine includes a core engine, a first bypass passage disposed about the core engine and a second bypass passage disposed about the first bypass passage. A flow control is disposed within the second bypass for controlling bypass airflow through the second bypass. The flow control translates axially between an open position and a closed position to vary and control airflow through the second bypass passage.

Abstract: A jet engine nacelle has one thrust reverser device which includes a deflection means and one cowl translatable in a direction substantially parallel to a longitudinal axis of the nacelle. The cowl can translate between a closed position and an open position. In the open position, the cowl ensures the aerodynamic continuity of the nacelle and covers the deflection means. In the open position, the cowl opens a passage into the nacelle and uncovers the deflection means. The thrust reverser device moreover includes one blocking flap pivotably mounted by one end attached to a rear portion of the deflection means, and slidingly connected to the moving cowl. The pivoting end is also translatably connected to the rear portion of the deflection means.

Abstract: A space launch apparatus comprising a solid triangular space frame constructed of a plurality of connected truss members that are attached to each other at nodes and are also attached to at least one rocket motor and to at least one payload whereby the force produced by the operation of the rocket motor is transferred to the payload and aerodynamic and vibration loads are distributed through the truss members and their nodes.

Abstract: The present disclosure relates to a self-mounted cascade for a thrust reverser of an airplane jet engine nacelle. The cascade includes an upstream portion and an opposite downstream portion, along with respective connection means so that two adjacent cascades are directly connected to one another only in the respective downstream portions by downstream connection means thereof. The downstream portion corresponds to an area extending from a downstream side edge over a length less than or equal to N times the length of the last cavity located along said downstream side edge, where N is less than 3. The present disclosure is of use in the field of airplane jet engine nacelles.

Abstract: A high-lift system for a wing of an aircraft is provided. The high-lift system includes movably held high-lift flaps, at least one drive unit, at least one transmission shaft connected to the drive unit, and several actuator devices, distributed on the transmission shaft and connected to the high-lift flaps, for moving the high-lift flaps. The actuator devices each comprise a driven element and a torque limiting means. In one example, the driven elements of two adjacent actuator devices are interconnected in a non-rotational manner with the use of a separate torque transmitting means. If one actuator device is blocked, for example as a result of a defective tooth arrangement or some other defect, the torque to be produced by the intact actuator device increases and triggers its torque limiting means. This ensures synchronous operation and in the case of malfunction prevents damage to or detachment of a flap.

Abstract: The present invention relates to a centrifugal fan assembly and a HVAC-system, comprising a housing, a blower wheel comprising a plurality of fan blades, the blower wheel being rotatably mounted in the housing and constructed to generate an airflow flowing axially into the blower wheel and radially out from the blower wheel, a guiding vane device including a plurality of guiding vanes, the guiding vane device being coupled to the blower wheel and configured to guide the airflow into the blower wheel.

Abstract: The present invention relates to a jet engine including protrusions (1) for preventing the increase of the velocity gradient of a fluid in a mixed layer of a jet flow and an external air flow by bending the mixed layer, when viewed from the side of a jet flow injected.

Abstract: A variable area fan nozzles comprising an array of rigid petals hinged to a lip area at the downstream end of a thrust reverser sleeve (or half-sleeve). In one embodiment, the actuation system comprises a rotatable ring segment, a drive system for rotating the ring segment, a plurality of cams attached or integrally formed with the ring segment, a plurality of cam followers, and a plurality of petal linkages which operatively couple the petals to the cam followers. This actuation system controls the deflection of the petals, thereby controlling the amount of opening and the rate at which the fan nozzle throat area changes. Each cam may have forward- and rearward-facing camming surfaces that interact with the cam followers to force the petals to pivot outward or inward respectively.

Abstract: A turbofan engine (10) employs a flow control device (41) that changes an effective exit nozzle area (40) associated with a bypass flow path (B) of the turbofan engine. A spool (14) couples a fan (20) to a generator (52). The turbofan emergency power system includes a controller (50) that communicates with the flow control device (41). Upon sensing an emergency condition, the controller manipulates the flow control device to reduce the effective nozzle exit area (40) of the bypass flow path, which chokes the flow through the bypass flow path thereby increasing the rotational speed of the fan. In this manner, the generator is driven at a higher rotational speed than if the flow through the bypass flow path was not choked, which enables a smaller generator to be utilized.

Abstract: A propulsion system of an aircraft is described herein. In this system, the inner fixed structure (IFS) and the outer sleeve may be separately coupled to the pylon. For instance, the inner fixed structure and the outer sleeve may be hinged separately and attached to different locations of the pylon. Thus, portions of the pylon are exposed to the fan duct air flow path.

Abstract: An exhaust nozzle for a gas turbine engine may include a plurality of flap trains in the exhaust stream of the gas turbine engine. The flap trains are operable to selectively control three separate flow paths of gas that traverse the engine. A first stream of is the core airflow. The second stream of air is peeled off of the first stream to form a low pressure fan bypass air stream. The third stream of air traverses along the engine casing and is passed over a flap assembly to aid in cooling. The flaps are operable converge/diverge to control the multiple streams of air.

Abstract: A flap for a convergent/divergent nozzle system includes an ejector door movably mounted to an inner skin at a hinge.

Abstract: Systems and methods are provided that lock thrust reversers and also drive fan nozzles of an aircraft. One system includes a coupling configured to selectively engage and disengage. While engaged, the coupling is configured to rotate to drive a Variable Area Fan Nozzle (VAFN), at least a portion of which is on a translating portion of a thrust reverser of an aircraft. Furthermore, while engaged the coupling is configured to prevent displacement of the translating portion.

Abstract: One embodiment includes a pivot thrust reverser comprising a first tandem pivot door subassembly comprising an inner panel and outer panel connected. A second tandem pivot door subassembly is included comprising an inner panel and outer panel connected. Also included are a first actuator located on a first side of an attachment location to pivot the first tandem pivot door subassembly, a second actuator located on a second side of the attachment location to pivot the second tandem pivot door subassembly, and a third actuator located substantially radially opposite the attachment location to pivot both the first tandem pivot door subassembly and the second tandem pivot door subassembly. The first tandem pivot door is configured to be pivoted from stowed to deployed by the first actuator and the third actuator, and the second tandem pivot door is configured to be pivoted from stowed to deployed by the second actuator and the third actuator.

Abstract: An apparatus installed on an aircraft, comprising: a sleeve or duct having a trailing lip area; a plurality of petals arranged side by side with gaps therebetween, one end of each petal being attached or pivotably coupled to the lip area; and a plurality of elastomeric seals configured and disposed to close the gaps between adjacent petals. Each elastomeric seal comprises a first portion that moves with a portion of a first petal that is in contact therewith, a second portion that moves with a portion of a second petal that is in contact there, and a third portion which is stretched as the first and second petals move further apart from each other. Petal deflection is actuated by a system comprising a flexible member, a motor, a shaft driven by the motor, and an arm projecting from the shaft. One end of the flexible member is attached to the arm, the flexible member being movable to deflect the petals inward in response to a shaft rotation.

Abstract: A gas turbine engine that has a fan case radially surrounding a fan hub, and plural fan exit guide vanes rotatably connected between the fan hub and the fan case. The fan section also has a thrust reverser opening within the case, axially upstream of the guide vanes. The gas turbine engine also has a core case containing a core engine.

Abstract: A door for a door-type thrust reverser is able to move between a direct jet mode of a nacelle and a reverse jet mode. The door includes an inner wall being integrated into a flow path of an air flow generated by a turbojet engine, an outer wall, at least one side wall connecting the inner wall to the outer wall of the door, and a deflector to deflect the air flow. In particular, the deflector includes a cavity of the door which is shaped to convey a fraction of the air flow from one air inlet rigidly secured to the inner wall of the door to one air outlet rigidly secured to the side wall of the door, so as to redirect, during operation of the nacelle in the reverse jet mode, a part of the air flow upstream from the inner wall of the door.

Abstract: A thrust reverser actuator gimbal assembly for mounting a thrust reverser actuator to fixed structure of the thrust reverser is disclosed. The thrust reverser actuator gimbal assembly may comprise a gimbal, first and second gimbal pins mounted to the gimbal and defining a first pivot axis, the first and second gimbal pins adapted to form a pivotal joint with the fixed structure of the thrust reverser, third and fourth gimbal pins mounted to the gimbal and defining a second pivot axis normal to the first pivot axis, the third and fourth gimbal pins adapted to farm a pivotal joint with the thrust reverser actuator, wherein the first and second gimbal pins each include a shaft and a flange integrally formed together, the flange including a pair of bores for receiving a fastener to fasten the respective gimbal pin to the thrust reverser fixed structure.

Abstract: A hydraulic circuit for a jet engine thrust reverser is disclosed. The hydraulic circuit may comprise a primary hydraulic actuator cylinder assembly and a secondary hydraulic actuator cylinder assembly. The primary hydraulic actuator cylinder assembly may be hydraulically coupled to the secondary hydraulic actuator cylinder assembly, in a master-slave relationship, and the secondary hydraulic actuator cylinder assembly may drive a thrust reverser blocker door. The primary hydraulic actuator cylinder assembly may comprise a rod, and the rod may comprise a channel through which hydraulic fluid is capable of flowing. The hydraulic circuit may further comprise a group of secondary hydraulic actuator cylinder assemblies, wherein the group of secondary hydraulic actuator cylinder assemblies may be coupled to the primary hydraulic actuator cylinder assembly.

Abstract: A thrust reverser track beam is disclosed. The thrust reverser track beam may comprise a recess defined by a reception surface and/or a perimeter surface surrounding the reception surface and extending away from the reception surface, wherein the reception surface and the perimeter surface bound a recess that is configured to receive a noise suppressing structure. The thrust reverser track beam may further comprise the noise suppressing structure. The recess is generally triangular in shape and may extend away from a plane. The noise suppressing structure may be generally triangular in shape and may extend away from a plane. The noise suppressing structure may be coupled within the recess of the track beam and/or to the track beam.

Abstract: A “U” shaped inverted track beam flange for a thrust reverser is described. The geometry of the inverted track beam flange increases the total noise cancellation capabilities of a nacelle structure comprising the inverted track beam flange. An inner fixed structure is coupled to an inverted track beam flange. The inner fixed structure is coupled to the inverted track beam flange along an attachment flange. The coupling is along a commercial jet aircraft engine fan duct airflow surface.

Abstract: A fan ramp for use in a thrust reverser portion of a nacelle is disclosed. The nacelle is included in a propulsion system. The fan ramp extends circumferentially about an axial fan ramp centerline. The fan ramp includes a forward edge, an aft edge, and a noise suppression feature. The forward edge is disposed proximate an aft end of a fan case. The fan case at least partially surrounds a fan section of a gas turbine engine. The aft edge is disposed proximate a forward end of an array of cascades. The array of cascades is operable to permit a bypass airstream to pass there through during a thrust reversing operation. The noise suppression feature is operable to suppress noise within the propulsion system.

Abstract: The invention relates to a torque limiter for an actuator including a screw (101), a nut mounted on said screw, an actuation tube (105) rigidly connected to the nut and means (109, 133) for rotating said screw, said limiter being characterized in that it includes an abutment (115, 110) capable of: preventing the rotation of said tube (105) by friction simply by an axial force exerted by said screw (101) onto said nut during the movement thereof; and enabling the rotation of said tube (105) when said nut arrives at an axial abutment of said screw beyond a predetermined torque threshold defined by the axial force.