Abstract: Seals for gimbaling and/or fixed rocket engine nozzles, and associated systems and methods are disclosed. A representative rocket propulsion system includes a rocket engine having an exhaust nozzle, a seal plate carried by the exhaust nozzle, and a seal engaged with the seal plate. The seal includes at least one support, multiple pivotable first flaps, carried by the at least one support and positioned to contact the seal plate, and multiple pivotable second flaps, with an individual second flap positioned to shield a corresponding individual first flap. At least one forcing element is operatively coupled to at least one of the individual first flap or the individual second flap, to apply a pivoting force to the at least one of the individual first flap or the individual second flap.

Abstract: A propulsor includes an electric motor, a fan unit, and a thrust system positioned downstream of and coupled to the fan unit. The electric motor converts electrical power to mechanical rotation to rotationally drive the fan unit and create an air stream directed towards the thrust control system.

Abstract: The invention relates to a bellcrank for a turbomachine having a first bore, a second bore and a third bore, the first bore being connected to the second bore by a first branch, the second bore being connected to the third bore by a second branch, the third bore being connected to the first bore by a third branch, a fourth branch connecting the first branch to the second branch.

Abstract: A thermal bridge forms a connection between a cold side and a hot side that is capable of withstanding a large temperature differential while high-pressure gas (e.g., air) flows between the two sides within an internal passageway. A cold-side region and hot-side region of the thermal bridge may each have a flange with a plurality of holes. The cold-side region may also include a conical fillet with counterbore recesses to provide access to each of the plurality of holes from a low radial position.

Abstract: Described herein is essentially a high-efficiency, hybrid fluid-aeolipile. In operation, this hybrid device is placed in the stream of a moving fluid, preferably air. Energy is extracted from the fluid stream by directing a portion of the stream through and, optionally, around the device. As the fluid-flow moves through the device, it is directed into nozzles. These nozzles, which are free to pivot in a cyclical manner, employ the established phenomenon of “nozzle-effect” to accelerate the velocity of the air-flow passing through them, which is ultimately ejected from each nozzle tip, producing thrust. This thrust, amplified by nozzle-effect, drives the nozzles to pivot around a shared axis. The wind energy, thereby converted into cyclical motion, that may be used to perform useful work, is converted with greater efficiency, than is possible in conventional blade-type wind turbines.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a target-type thrust reverser and a tubular trailing edge body. The target-type thrust reverser includes a plurality of thrust reverser doors. Each of the thrust reverser doors is configured to pivot between a stowed position to a deployed position. The tubular trailing edge body is configured to at least partially form a gas path nozzle for the aircraft propulsion system. The tubular trailing edge body is configured to be displaced when the thrust reverser doors pivot from the stowed position to the deployed position.

Abstract: A thickened robot joint transmission structure comprises a shell, dual gear rings and a planet carrier, wherein the planet carrier is fixed to the shell through a crossed roller bearing. Planet gears are dual thickened planet gears free of a sun gear. The input ends are a pair of gears or spiral bevel gears with a variable velocity ratio and are fixed to the shell through deep groove ball bearings. The dual thickened planet gears serve as a hollow for a cable, a related shaft or a line object to pass through after the sun gear is removed.

Abstract: A thrust vectoring exhaust nozzle is disclosed. The nozzle includes an inner nozzle for changing a first degree-of-freedom of exhaust gas, an outer nozzle for changing a second degree-of-freedom of exhaust gas, a mounting bracket, a first linear actuator, a second linear actuator, a first double universal joint, and a second double universal joint. The inner nozzle is coupled to the outer nozzle. The inner nozzle is coupled to the mounting bracket. The outer nozzle is coupled to the first and second joint. When the nozzle is mounted, the inner nozzle, the outer nozzle, and the exhaust are coaxially aligned in neutral position. Actuation of the first and second linear actuators drives the first and second double universal joints independently to each other. The independent motion of the first and second double universal joints rotates the inner and outer nozzles simultaneously about the exhaust in a horizontal direction and vertical direction enabling thrust vectoring.

Abstract: The proposed technology relates to a thrust control apparatus of a propulsion system, and more particularly, to a thrust control apparatus of a solid propulsion system equipped with an aerospike pintle nozzle. The present invention is to simultaneously control the magnitude and direction of thrust by installing a pintle and a thrust vectoring unit at the rear end of a combustion tube of a solid propulsion system.

Abstract: A thruster nozzle (24) includes a throat (28) and a nozzle end portion (30) that is integral with the throat. The nozzle end portion includes an outer wall (32) that has a plurality of circumferentially-disposed nozzle features or connectors (34). A brace (26) may be disposed at least partially around the thruster nozzle and mated with the nozzle features to restrict relative movement between the thruster nozzle and the brace. The brace may be attached with a vehicle body (22) of a vehicle.

Abstract: A nozzle (1) for a space vehicle engine (M), the nozzle comprising a stationary portion (2) and a movable portion (3), the nozzle (1) including a pneumatic deployment system (4) comprising: a deployment actuator (5) for deploying the movable portion (3) of the nozzle (1); a high unlocking actuator (6); a low unlocking actuator (7); and an ejector (41); the deployment system (4) including a feed system (8) configured so as to, sequentially: move the deployment actuator (5) from its support position towards its deployment position; move the high and low unlocking actuators (6, 7) into their high and low unlocking positions; and actuate the ejector so as to eject the deployment system (4) from the nozzle (1).

Abstract: An exhaust system for reducing infrared emissions of a rotary wing aircraft includes a duct assembly having an inlet portion and an outlet portion; the inlet portion configured to receive exhaust from an engine of the aircraft; and the outlet portion coupled to the inlet portion, the outlet portion having an outlet duct with an outlet opening, the outlet duct configured expel an emission containing engine exhaust proximate to a tail fairing of the rotary wing aircraft.

Abstract: An aircraft with at least one engine that generates a hot air flow in operation of the aircraft, wherein at least one hot air exhaust is provided for exhausting the generated hot air flow, the at least one hot air exhaust comprising at least one first exhaust section that is mounted in a rotatable manner to at least one second exhaust section via an associated off-axis swivel joint, wherein an actuating member is provided that is adapted for applying a turning moment to the at least one second exhaust section in operation of the aircraft in order to displace a longitudinal axis of the at least one second exhaust section with respect to a longitudinal axis of the at least one first exhaust section by a predetermined displacement angle.

Abstract: A cascade assembly of a nacelle for a turbofan engine includes a one-piece cascade fixed to a translating sleeve constructed and arranged to move between forward and aft positions along a centerline. A hook device of the cascade assembly includes a first catch fixed to a stationary structure and a second catch fixed to the one-piece cascade. The first catch is adapted to mate with the second catch for translating load when the cascade assembly is in a deployed state and the translating sleeve is in the aft position.

Abstract: A method for producing a propulsion nozzle, wherein the nozzle is produced from an ablative resin, the method including a step of pre-polymerization wherein an innovative aldehyde compound is used.

Abstract: A vertical take-off and landing (VTOL) aircraft is provided and includes a fuselage with first and second wings extending outwardly from opposite sides of the fuselage, nacelles with proprotors respectively disposed on the first and second wings, the proprotors being rotatable to generate lift in vertical flight and thrust in horizontal flight and exhaust deflectors disposed proximate to trailing ends of the nacelles. The exhaust deflectors are disposed to assume at least first, second and third configurations respectively associated with first, second and third flight conditions.

Abstract: A rotary joint includes a socket rod having a socket rod flange with a basically spheroid con-cave bearing surface at a first end, a housing nut encircling the socket rod and having a threaded wrenching head, a ball rod having a basically spheroid convex bearing surface and threaded side walls around the convex bearing surface, and a joint actuator configured to actuate relative movement of the socket rod flange and the ball rod. A diameter of the threaded side walls of the ball rod corresponds to a diameter of the threaded wrenching head of the housing nut.

Abstract: An adjustable attachment for a landscaping air blower includes a mounting tube, a nozzle and a connecting ring that rotatably couples the mounting ring and the nozzle. The upstream end of the nozzle defines a circle aligned at an acute angle to the axis of the nozzle and the downstream end of the mounting tube defines a circle aligned at an acute angle to the axis of the mounting tube. Rotation of the nozzle about its axis changes the alignment of the axis of the nozzle relative to the axis of the mounting tube.

Abstract: An exemplary nozzle having a variable internal exhaust area for a gas turbine engine can have a plurality of flap trains extending around a periphery of the gas turbine engine. Each flap train can include a convergent flap pivotally attached to an engine body and a divergent flap pivotally attached to the engine body downstream of the convergent flap. The nozzle can further have a fluid circuit in communication with the convergent and divergent flaps and configured to pivot the convergent and divergent flaps between a radially inward position and a radially outward position.

Abstract: A method and apparatus to control movement of a vehicle using a plurality of thrust-producing devices formed in at least one control surface is disclosed. A supply of power to the plurality of thrust-producing devices that are configured to propel gas through the control surface to produce thrust is controlled such that a physical displacement of the control surface is generated. The physical displacement is in accordance with the supply of power to the plurality of thrust-producing devices and controls the movement of the vehicle.

Abstract: The invention relates to a mounting assembly for a rocket nozzle for an engine that may be operable in rocket mode, in which the engine combusts stored oxygen and hydrogen, or in air-breathing mode, in which the engine combusts air from the atmosphere and stored hydrogen. A plurality of ducts and pipes are connected to the nozzle to supply fuel and other fluids. As it is desirable to allow the nozzle to pivot, the mounting assembly may include flexible couplings on the ducts and pipes about selected pivot points allowing the desired freedom of motion. The flexible couplings are designed to withstand various pressure forces in the rocket/aircraft flight environment, and may be composed of spaced annular elements, wherein a partial toroid element connects consecutive pairs of annular elements.

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

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

Abstract: A nacelle assembly for a turbofan engine includes a forward nacelle portion having an aft edge and defining a bypass duct that transports bypass airflow of the turbofan engine, a translatable sleeve that is translatable aft of the forward nacelle portion, and a variable area fan nozzle (VAFN) airfoil that is movable between a stowed position, a VAFN flow position, and a thrust reverse position. Blocker doors for the thrust position are integrated into the VAFN airfoil.

Abstract: A nozzle assembly for a gas turbine engine includes a door axially slidable relative to a passage in communication with a secondary flow path to regulate the secondary flow though the passage.

Abstract: A nozzle effective exit area control system is created with a convergent-divergent nozzle with a divergent portion of the nozzle having a wall at a predetermined angle of at least 12° from the freestream direction. Disturbance generators are located substantially symmetrically oppositely on the wall to induce flow separation from the wall with the predetermined wall angle inducing flow separation to extend upstream from each disturbance generator substantially to a throat of the nozzle pressurizing the wall and reducing the effective area of the jet flow at the nozzle exit.

Abstract: A gas turbine engine comprising a compressor, a combustion chamber, and at least two turbines mounted oppositely to the combustion chamber, such that the gas turbine engine is capable of generating multidirectional thrust.

Abstract: A nozzle device defines a passageway including an outlet to discharge working fluid to produce thrust. This device includes a vectoring mechanism having three or more vanes pivotally mounted across the passageway and a linkage pivotally coupling the vanes together. This linkage includes a first arm fixed to a first one of the vanes to pivot therewith about a first pivot axis, a second arm and a third arm fixed to a second one of the vanes to pivot therewith about a second pivot axis, and a fourth arm fixed to a third one of the vanes to pivot therewith about a third pivot axis. A first connecting link pivotally couples the first arm and the second arm together, and a second connecting link pivotally couples the third arm and the fourth arm together. The relative angular positioning of the arms with respect to the corresponding pivot axes and/or the arm links can be varied to define different vectoring schedules with the mechanism linkage.

Abstract: An exhaust duct assembly includes a cooling liner spaced apart from an exhaust duct case that articulate for use in a short take off vertical landing (STOVL) type of aircraft. The cooling liner assembly is attached to the exhaust duct case through a foldable attachment hanger system. The foldable attachment hanger system provides a low profile (foldable up/down) for a limited access installation envelope typical of a three bearing swivel duct (3BSD) which rotates about three bearing planes to permit transition between a cruise configuration and a hover configuration. In this way, each cooling liner segment may be formed as a complete cylindrical member requiring joints only between the swivelable duct sections.

Abstract: An actuator arrangement for moving a first component relative to a second component, the arrangement comprising: an actuator chamber for receiving a fluid under pressure, a side wall of the chamber being fixed relative to the first component; an actuating element fixed relative to the second component and located inside the chamber for sliding movement along the chamber, relative to the side-wall; and a sealing element which provides a corresponding sliding seal between the actuating element and the sidewall for maintaining an actuating fluid pressure differential across the actuating element thereby to drive the actuating element relative to said side-wall, under said fluid pressure differential, for driving said relative movement of the first and second components; wherein the arrangement further comprises an external side-wall brace connected to the second component for corresponding movement with the actuating element along the outside of the sidewall, the brace being slidably or rollably braced against t

Abstract: An exhaust duct assembly includes an attachment hanger system having at least one component manufactured by metal injection molding (MIM).

Abstract: A propulsion gas exhaust assembly is presented for use in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator. The assembly may include a first cylindrical duct, two second ducts, two third ducts, and two axial gas-ejection nozzles. The first cylindrical duct element receives the gases downstream of the gas generator. The gasses flow downstream from the first cylindrical duct element to two second duct elements. These two second duct elements are divergent in a first geometric plane. Each of the two second duct elements may guide the flow to their own respective third duct and nozzle. The third ducts may include elbows to assist in stealth. The nozzles may include the means to steer the aircraft.

Abstract: A vectorable nozzle includes convergent and divergent sections and a throat therebetween. Heightwise spaced apart upper and lower walls outwardly bound a nozzle flowpath and extend aftwardly through the convergent and divergent sections from the nozzle inlet to the nozzle outlet. The upper wall includes triangular left and right side convergent upper panels pivotably mounted to a triangular convergent upper ramp in the convergent section along left and right side convergent angled hinge lines respectively. The upper wall further includes triangular left and right side divergent upper panels pivotably attached to a triangular divergent upper ramp in the divergent section along left and right side divergent angled hinge lines respectively. The left and right side convergent upper panels are in sealing engagement with the left and right side divergent upper panels along left and right side upper interfaces, respectively.

Abstract: Provided is a variable-throat exhaust turbocharger in which a nozzle assembly including a nozzle mount and nozzle vanes has a firm support structure without affection by a thermal deformation of a turbine casing and an external force exerted to the turbine casing, and a scroll portion is formed in a substantially opened configuration so that the nozzle assembly can be simply formed in order to reduce the number of mold cores for a scroll during casting of the turbine casing, thereby it is possible to enhance the productivity of the turbine casing.

Abstract: An apparatus for driving a body with 3-degree of freedom angular motion, comprises: a body connected to a fixing part so as to be rotatable centering around a pitch axis, a yaw axis, and a roll axis; a pitch axis driving unit for rotating the body centering around the pitch axis; and a yaw axis driving unit for rotating the body centering around the yaw axis. Since one of the pitch axis driving unit and the yaw axis driving unit restricts the body from rotating centering around the roll axis fixed to the body, the conventional roll-rotation restricting link is not needed between the body and the fixing part. Accordingly, a size of the apparatus is reduced.

Abstract: An adapter device for controlling a rocket engine nozzle under conditions of external pressure that can lead to the jet separating inside the nozzle, the nozzle being fitted with a diverging portion that is movably mounted relative to a stationary portion of the nozzle, thrust deflection then being achieved by swivelling the diverging portion so as to deflect the jet of combustion gas in contact with the inside wall of the diverging portion. The device includes a structure disposed inside the diverging portion in such a manner as to reduce the diverging nature of the flow section thereof and to increase the bearing area of pressure forces exerted by the jet on the diverging portion during swivelling thereof.

Abstract: A non-invasive system, method, and apparatus for control input prediction and state verification of an aircraft's fluidic vectoring exhaust is disclosed. The control system derives a desired vector state, then predicts and sets the fluidic injection input required to produce the desired vector state. A vectored state verification routine is used to determine the resulting vector state for feedback to the control system.

Abstract: The invention relates to a ventilation system for a convergent divergent exhaust nozzle in a bypass turbojet comprising an afterburn chamber surrounded by an annular passage through which circulates a stream of cooling air, a convergent divergent axisymmetric nozzle arranged downstream of said afterburn chamber, each circle of flaps comprising alternately a plurality of controlled flaps, and a plurality of follower flaps, a circle of cold flaps arranged radially outside said nozzle and hinged at their upstream end to a conical shell linked to the downstream part of the casing.

Abstract: An embodiment of the invention is a technique to suppress noise in a jet engine. A noise suppressor includes an exhaust duct to exhaust a first stream from an air stream taken from an inlet. The exhaust duct has an exit end. The air stream is divided into the first stream and a second stream. The second stream has an axis. A stream director attached to vicinity of the exit end directs the first stream to a direction that is away from or sideward relative to the axis.

Abstract: A nozzle for a jet engine generally includes a nozzle rim and a bendable duct for communicating an exhaust flow generated by the engine to the nozzle rim. A gimbal joint pivotably couples the nozzle rim to supporting structure. The gimbal joint allows the nozzle rim to be pivoted about a first axis and a second axis, thereby allowing changes to the vector at which the exhaust flow is discharged from the nozzle rim.

Abstract: A controlled hot flap shutter for a turbojet nozzle includes a friction surface made of metal, and including straight lateral flanks to reduce the gap between each controlled hot flap shutter and the tracking flap shutters adjacent thereto.

Abstract: A jet engine nozzle having a pair of pivoting extension arms and a pair of pivoting shells connected to a jet pipe is provided. The first extension arm is pivotally connected to the jet pipe at a first location, while the second extension arm is pivotally connected to the jet pipe at a second location. Each shell is pivotally connected at both the first and second locations. An axis of rotation associated with the first location is coaxial to an axis of rotation associated with the second location. Independent actuation means are provided to rotate the extension arms and the shells, thereby enabling adjustment of the thrust-vector angle or the exhaust area of the nozzle.

Abstract: A vectorable variable area nozzle is formed by a pair of parallel sidewalls, a pair of opposed clamshell elements arranged between the sidewalls and each able to rotate about an axis perpendicular to the sidewalls and a pair of flaps each pivotally lined to the downstream end of one of the clamshell elements. In use the thrust produced by the nozzle can be vectored by rotating the two clamshells about their respective axes.

Abstract: A two dimensional gas turbine engine exhaust nozzle includes transversely spaced apart upper and lower convergent and divergent flaps and extending longitudinally in a downstream direction and between two widthwise spaced apart sidewalls. The divergent flaps have inwardly facing upper and lower flap surfaces defining together with the sidewalls at least a part of an exhaust stream flowpath therebetween. The upper and lower flap surfaces have respective upper and lower apexes wherein the upper apex is axially spaced apart and aft of the lower apex. The upper divergent flap has an expansion ramp diverging away from the nozzle axis. The ramp extends aftwardly from the upper apex and aftwardly of a trailing edge of the lower divergent flap. The upper and lower divergent flaps are operably movable to block a line of sight along the nozzle axis through an exit of the nozzle during engine operation.

Abstract: A nacelle comprised of a rigid shroud and a support truss. The shroud encloses the truss and a rocket engine. The shroud is comprised of three sections, including a top section and two side sections. The top section has openings to permit the communication of lines for liquid propellant, electrical current, and hydraulic fluid between the engine and an attached flight vehicle. The two side sections are connected to each other by longitudinal field joints, and to the top section by a circumferential field joint. The rocket engine is attached to the flight vehicle by a gimbal allowing the engine to rotate relative to the flight vehicle about orthogonal pitch and yaw axes. A pair of actuators is located in the flight vehicle, one to control the rotation of the rocket engine about the pitch axis, and the other to control its rotation about the yaw axis. The truss is attached to the body of the rocket engine.

Abstract: A valve assembly for supplying cooling air to a nozzle of a gas turbine engine. The nozzle can move between a first configuration and a second configuration. The valve assembly includes a first member having openings that receive cooling air. The valve assembly also includes a second member having openings. The second member resides adjacent the first member to receive the cooling air from the first member. Finally, the valve assembly includes actuator for moving the first member from a first position, which allows a first flow rate of cooling air to pass through the openings, to a second position, which allows a second flow rate of cooling air to pass through the openings. The second flow rate is less than the first flow rate.

Abstract: An outlet device for a jet engine (2) includes an outlet channel (3), which has an upstream end (3′) for being connected to the jet engine and a downstream end (3″) and which defines a main flow direction (a) for a jet from the jet engine. The outlet channel has in the proximity of the downstream end an elongated shape, seen in a section across the flow direction, and includes at least two outlet portions (4, 5, 6), which are separated from each other, for a respective outlet flow of said jet. A first outlet portion (5, 6) includes means for controlling the outlet direction of the outlet flow in a first plane and a second outlet portion (4) includes means for controlling the outlet direction of the outlet flow in a second plane, which forms an angle to the first plane. An aircraft may include such an outlet device.

Abstract: A variable area exhaust nozzle with a variable thrust vector angle for a turbo-fan engine and mounted on the aft portion of the nacelle which wraps said engine. The nozzle may include a fixed structure having at least two lateral arms separating two radial cutouts. The cutouts are positioned one above the other, one being located above the engine axis, the other one below the engine axis. At least two shells close the fixed structure cutouts and are pivotally mounted on the fixed structure to form a portion of the exhaust nozzle of the engine. A sealing means ensures fluid tightness between the shells and the fixed structure for any angular position of said shells. Actuator means are provided for pivoting the shells either to a symmetrical configuration for changing of the value of the exhaust area of the nozzle or to an unsymmetrical configuration for changing the angle of the thrust vector of the exhaust nozzle.

Abstract: A flow-through thrust takeout apparatus comprises an injection manifold (coupler) mounted to an engine and having a manifold passage. A ball line is attached to the injection manifold, and has a ball line passage fluidicly coupled with the manifold passage. A ball clamp is movably connected with the exterior surface of the ball line. A tank interface is attached to the ball clamp. The tank interface and ball clamp form a socket around the ball line to be movable relative to the injection manifold and the ball line. The tank interface is attached to a fuel tank. The interface member has an interface passage fluidicly coupled with the ball line passage to permit fuel flow from the fuel tank to the engine. A valve is mounted between the engine and the interface passage, and is adjustable to control fluid flow between the tank and the engine. The apparatus transfers the engine thrust from the rocket engine to the fuel tank, and the flow-through passages permit fuel transfer from the fuel tank to the engine.

Abstract: An engine nozzle arrangement for an aircraft comprises a nozzle (18) for hot exhaust gases, and a shroud (20) for the stream of hot exhaust gases emerging from the exhaust nozzle. The shroud includes an intake for a boundary layer of air for cooling the stream of exhaust gases.