Abstract: A thrust vectoring exhaust nozzle structure for an engine, such as a ramjet, rocket or turbojet, which generates thrust by expulsion of gaseous fuel combustion products along a thrust axis is described which comprises a generally axisymmetric housing defined along a central thrust axis including a wall structure defining an exhaust duct, and an axially spaced radially inwardly convergent portion, throat and radically outwardly divergent portion, and at least one airfoil disposed on the wall structure of the divergent portion and mounted for rotation about an axis substantially perpendicular to the thrust axis.

Abstract: A pivot door type aircraft turbine engine thrust reverser which includes a pair of pivoting panels on the inner side of the door. The panels are positioned alongside the door actuation mechanism. The panels form a flush surface along the fan duct flow path when stowed during normal engine operation in flight. When the door is deployed in thrust reversing mode, one end of the door moves to at least partially block airflow through the duct and divert it out along the door through an opening uncovered by door deployment. During door deployment, a linkage moves the panels toward the outer surface of the door, exposing a door deflector plate to the airflow. Air flows along the door, then along the panel, out through the opening, then impacts the deflector plate which deflects the airflow in the reverse direction.

Abstract: An adjustable converging-diverging nozzle (10) includes a body (11) having a flow passageway (14) therethrough. The passageway is configured to define an entrance section (18), a narrowed throat section (19), and an exit section (20). Two opposing vane members (12,13) are pivotally mounted on the body. Each vane member has a first surface (33,33') facing into the passageway to form a movable wall portion of the throat section. Each first surface is eccentric to the pivotal axis (38,38') of the associated vane member. A pair of actuators (42,43) are mounted on the body for selectively varying the angular positions of the associated vane members. The vane members may be moved to a closed position to reduce the orifice area of the throat section to zero, or may be moved to other angular positions to vary the magnitude and/or direction of the thrust vector of hot gas discharged through the nozzle. The invention also provides an improved method of operating the nozzle by selectively moving the vane member(s).

Abstract: A thrust reverser in a two dimensional jet engine exhaust nozzle employs a plurality of reverser apparati that maintain a constant flow throat area, for example, in the reverse throat mode. A single reverser apparatus includes an actuator that operates through a lever upon linkage and a coupler to drive a set of parallel vanes and at least one independent vane. The parallel vanes are connected by a parallelogram of links to the coupler. The independent vanes move in a manner as defined by a cam having a preselected path therein that causes the independent vanes to move in a desired manner to provide the constant throat area.

Abstract: A propelling nozzle for a hypersonic jet plane having movable upper and lower primary and secondary flaps assigned to the gas turbojet engine as well as to the ramjet engine, both engines being arranged axially above one another, their outlet ducts being separated by means of a partition extending in the downstream direction to the narrowest cross-section of the propelling nozzle. The nozzle flaps can place themselves against the end edge of the partition on both sides in a manner advantageous with respect to the flow in the transition area from the primary flaps to the secondary flaps. As a result, each of the two outlet ducts can advantageously, either alternatively or simultaneously, be closed or opened, while, at the same time, a narrow cross-section and a divergence of the propelling nozzle can be adjusted which are optimal for the respective flying Mach number.

Abstract: A convergent/divergent gas turbine engine exhaust nozzle having reverse thrust capability includes a door which blocks a reverse flow outlet port when the nozzle convergent flap is in any forward thrust operating mode. The door is coupled to the convergent nozzle flap such that it opens as the convergent nozzle flap moves to a reverse thrust position and the flap directs the exhaust gases through the reverser outlet. Coupling is accomplished by a cam track connected to the blocker door and a cam track connected to the convergent flap, with a cam follower interconnecting the two cam tracks. As the convergent flap is rotated, the cams and cam follower cause appropriate movement of the blocker door.

Abstract: Tapered disc rotatably mounted in the exhaust duct of a propulsion system. The disc can be rotated about an axis normal to the yaw plane. A disc bump projects from both the upper and lower surfaces of the disc, and extends diametrically across it. When fluid is flowing through the exhaust duct, the bump, together with the opposing surfaces of the exhaust duct, chokes the flow and causes a sonic plane to be formed at the bump. The supersonic flow downstream of the disc bump remains approximately normal to the bump for angles of rotation of up to 20.degree. from normality between the bump and the upstream flow. Rotation of the disc thus causes deflection or turning of the fluid flow. The resultant thrust vectoring enables the yaw of the propulsion system and, therefore, a vehicle containing the propulsion system, to be controlled.

Abstract: Gas turbine engine power plants of the ducted fan type. During reversed thrust operation of the power plant, air is induced into the bypass duct through two inlets in one type of power plant is concerned. One of these, a secondary inlet, is located between a stationary front section of the bypass duct and a translated rear section. A gas or fluid such as air is injected at high velocity into the bypass duct to turn air induced through the secondary inlet into paths paralleling the longitudinal centerline of the duct or to accomplish this goal and also promote the attachment of induced air to the inner surface of the bypass duct. In both cases, the efficiency of the power plant in the reversed thrust mode of operation is increased. A second type of power plant of interest does not have a translatable rear section.

Abstract: A gas jet engine nozzle such as a turbine engine nozzle is provided for directing an axial flow in a downstream direction of exhaust gases to obtain thrust vectoring. The gas jet engine nozzle comprises an exhaust nozzle member for channeling the axial flow of the exhaust gases into a flow field, and a plug movably positioned substantially within the exhaust nozzle member and in the flow field for interacting with the gases to control the direction of flow of the gases. The plug has a substantially continuous surface including a diverging forebody portion and a monotonically converging afterbody portion. The afterbody portion is in the downstream direction relative to the forebody portion. A support structure is coupled to the plug for movably supporting the plug within the exhaust nozzle member and in the flow field. A hydraulic actuating system is operatively coupled to the plug for selectively controlling the position of the plug.

Abstract: An axisymmetric thrust vectoring exhaust nozzle includes a plurality of divergent flaps (30) each supported at the upstream end by a universal joint (32) and at the downstream end by a load link (34) connected to a unison ring (36) positioned by actuators (45).

Abstract: Disclosed is a two-dimensional nozzle for a gas turbine engine which, through the use of divergent flaps mounted on pivot shafts eccentric to the side disks in which they are received, provides thrust vectoring and low observability flight operation.

Abstract: Disclosed is an apparatus and a method for cooling a rotatable convergent side disk in a two-dimensional nozzle for a gas turbine engine, in which coolant is supplied and exhausted through concentric conduits, the cooling requirements of a liner assembly are reduced by use of a thermal barrier coating, and exhaust gas from the nozzle is prevented from aspirating into the side disk by use of a liner which is impervious to the exhaust gas.

Abstract: A simplified and cost-effective missile is disclosed which features a generally cylindrical casing, an aerodynamic warhead, and a plug nozzle. The casing of the missile contains a combustible propellant. The plug nozzle comprises a generally radially symmetric plug fitting within an open rear end of the casing such that an annular passageway is formed therebetween, through which exhaust gases from combustion of the propellant pass. The shape of the plug is chosen such that the cross-sectional area of the annular passageway varies in a predetermined fashion, to cause a desired thrust to be generated by combustion of the propellant. A number of vanes are spaced radially around the annular passageway and are inclined with respect to the centerline of the missile, so that the reaction of the exhaust gases on them provides a twisting force on the missile, whereby it spins and is stabilized in flight.

Abstract: A simplified actuation system for positioning the divergent flaps of a vectorable two-dimensional exhaust nozzle is disclosed. The system includes lever arms having cam surfaces pivotably attached to diverent flap crank shafts. An actuator is pinned to the nozzle sidewall and operably connected to a slider bar which has two cam followers at either end which are fixed with respect to each other and enage the cam surfaces of the lever arms. The slider bar is slideably engaged to the nozzle sidewall so as to permit radial movement with respect to the nozzle centerline. As the convergent flaps are moved the lever arms are translated axially and the cam followers in cooperation with the cam surfaces on the lever arms schedule the relative angle between the divergent flaps and thereby the exit area of the nozzle. Vectoring is provided operating the actuators which translate the cam followers in the radial direction, up or down, thereby rotating the divergent flaps so that they are pitched up or down in unison.

Abstract: A thrust reverser including a bypass duct and a plurality of light weight, circumferentially displaced blocker doors each movable between a normal position and a thrust reversal position. The blocker doors include pits on the inner portion which faces the bypass duct during normal operation of the engine. Provision is made for automatically covering the pits during normal operation to provide smooth, non-turbulent flow of air through the bypass duct. In one embodiment of this invention a pit cover is pivotally mounted on the blocker door and is biased to engage the edge of a ramp fairing when the blocker door is in the position it occupies during normal operation of the engine. During thrust reversal, the pit cover moves outwardly along with the blocker door and away from the ramp fairing so as not to impede in any way flow of thrust reversal air through an opening in the outer wall.

Abstract: A two-dimensional nozzle is disclosed wherein outward deflection of the sidewalls is controlled by using the load force of the divergent actuators to produce a bending moment within each sidewall which opposes such outward deflection.

Abstract: A thrust reverser door for a turbofan-type turobjet engine thrust reversing system is disclosed defining a gas flow passage between inner and outer panels of the door. The passae has an inlet formed through the inner panel of the thrust reverser door and an outlet, directs a portion of the gas flowing through a cold flow air duct in a forward direction. The gas flowing in the forward direction inpinges upon gases flowing through a laterally facing opening in the housing in order to provide a forward component to this gas flow. A moveable flap may be attached to the thrust reverser door in order to cover the inlet to the passageway when the device is operated in the forward thrust mode.

Abstract: A thrust reverser having a multi-panel construction is disclosed. The thrust reverser has a main door operatively associated with a deflector panel. The door and the deflector panel are pivotally attached to the housing so as to pivot about axially displaced pivot axes. The deflector panel and a downstream inner door panel surface extend along an ideal for flow line between the stationary upstream housing portion and the downstream housing portion when the thrust reverser is in the forward thrust mode. A cavity is defined between an upstream stationary housing portion, an upstream inner door panel surface and the deflector panel communicates with the ambient atmosphere such that the pressure acting on the upstream inner door panel surface is substantially equivalent to the ambient air pressure.

Abstract: The invention relates to a stepping mechanism for rotary motions with a driven switching wheel (9) which comprises at least one wheel-side stop (10), with an escapement mechanism having at least one pawl (12) which cooperates with said wheel-side stop, and with an actuating device (3, 17) for the pawl. Pursuant to the invention, a miniaturizable stepping mechanism is provided which is of a simple design and which permits reliable positioning of the switching wheel into preselected individual rotational positions. According to the invention, this is achieved in that the escapement mechanism of the stepping mechanism comprises a brake (20) displaceable under the action of force, with a run-up edge (21) lying in the region of each pawl (12) on to which the wheel-side stop (10) runs up before striking the pawl (12) to thereby displace the brake.

Abstract: A guided missile with a hot-gas generator, whose gas penetrates a plurality of blow-out nozzles, which are arranged at regular intervals along the circumference and extend essentially perpendicularly to the longitudinal missile axis, whereby the flow rate of the gas through the individual blow-out nozzles can be regulated by a control device. The control device has a star coupling, which contains a number of arms corresponding to the number of blow-out nozzles, whereby each arm has a positioning element assigned to it, the corresponding blow-out nozzle can close completely or partially, and each arm has a control element assigned to it.

Abstract: Thrust reverser for a jet engine of the type with doors equipped with auxiliary flaps. The invention relates to thrust reversers with doors 13 having a front deflector 15. The door is equipped, on its inner face, with one or two auxiliary flaps 16 articulated about axles 17 and controlled by a lever 21 articulated on the door at 22 and stressed into a retracted flap position by means of a spring 24. At the end of closure of the door, the end 31 of the lever interacts with a stop 33 which ensures that the lever tilts and that the flap 16 moves away from the door 13.

Abstract: A thrust ring assembly for use in a thrust reverser system for a gas turbine engine. The ring assembly is useful in a turbine engine having a core engine surrounded by an engine casing and nacelle, with a fan at the inlet directing air flow into the bypass duct between core engine and nacelle. The thrust reverser basically comprises at least one opening through the engine casing and nacelle, a turning vane cascade in the opening, a cover movable by an actuator between positions covering and uncovering the opening and at least one blocker door movable between a position allowing flow through the bypass duct and a position diverting flow to the turning vane cascade. The actuator and cascade are severely aerodynamically loaded during thrust reversal. The improved thrust ring assembly carriers those loads and transfers them to the engine casing. The forward ends of the cascade and actuator are secured to a bulkhead ring which is secured to the base of a frustoconical ring.

Abstract: A thrust vectoring axisymmetric convergent divergent variable exhaust nozzle is provided with a universally pivoting joint between the divergent and convergent flaps and actuating the linkage mechanisms for changing the divergent nozzle section from axisymmetrical to asymmetrical by pivoting the divergent flaps in the radial and tangential directions with respect to the axisymmetric nozzle centerline in a controlled manner.

Abstract: An exhaust nozzle assembly for vectoring the thrust of the exhaust gases from a turbojet engine is disclosed wherein the exhaust gases are vectored by an assembly that is separate from the flaps that are utilized to adjust the cross-sectional area of the exhaust nozzle. The thrust vectoring exhaust nozzle assembly has a moveable thrust vectoring assembly comprised of inner and outer vectoring members, each of which have a generally annular configuration. The vectoring members are pivotally attached to the exhaust nozzle so as to pivot about an axis extending generally perpendicularly to the longitudinal axis of the exhaust duct.

Abstract: A thrust vector control for a jet engine is accomplished by controllable flaps which have an inner, jet flow facing contour with a double curvature. One curvature section is convex and extends between the leading edge of the flap and a transition point. The other curvature section is concave and extends between the transition point and the trailing edge of the flap. The flap or flaps are arranged downstream of the propulsion jet nozzle and are tilted into the jet stream as required for the vector control. A pressure sensor is arranged so as to measure or pick-up a pressure value, preferably near the trailing edge of the flap, which pressure value depends on the dynamic pressure head in that area. The respective pressure value is used in a closed loop control circuit for operating the tilting drive of the respective flap.

Abstract: A thrust reverser including a bypass duct and a plurality of light weight, circumferentially displaced blocker doors each movable between a normal position and a thrust reversal portion. The blocker doors include pits on the inner portion which faces the bypass duct during normal operation of the engine. Provision is made for automatically covering the pits during normal operation to provide smooth, non-turbulent flow of air through the bypass duct. In one embodiment of this invention a pit cover is pivotally mounted on the blocker door and is biased to engage the edge of a ramp fairing when the blocker door is in the position it occupies during normal operation of the engine. During thrust reversal, the pit cover moves outwardly along with the blocker door and away from the ramp fairing so as not to impede in any way flow of thrust reversal air through an opening in the outer wall.

Abstract: In the preferred configuration, the assembly is characterized in that the lateral and longitudinal thrust reserving loads exerted on the thrust reversing subassembly are transmitted into the fan duct structure which is arranged to in turn transmit these thrust reversing loads into outer structure to which the jet engine and thrust reversing assembly is mounted.In the preferred from, there are vane means which, with the thrust diverting structure in the thrust reversing position, is positioned in the thrust reversing opening to properly direct flow through the thrust reversing opening. Also in the preferred form, the thrust diverting structure is pivotally mounted to the fan duct structure at a lower location so that the thrust diverting structure rotates with a downward component of motion to the thrust reversing position, so that the thrust diverting opening is directed upwardly.

Abstract: A thrust reverser includes a thrust reversing door having maximum efficiency in both the closed, forward thrust position and the open, reverse thrust positions. An inner panel is pivotally attached to the thrust reverser door by a linkage mechanism such that, in the closed position, an interior surface of the inner panel is substantially flush with the interior surfaces of the housing defining the cold flow duct so as to minimize or eliminate any perturbations in the air flowing through the cold flow duct. When the door is moved to the opened position, the linkage mechanism interconnecting it to the inner panel causes the inner panel to pivot a greater amount so as to bring an upstream portion of the inner panel closer to an upstream portion of the door to expose the deflector and thereby increase the thurst reversing efficiency.

Abstract: The present invention provides a movable air deflector which, in a first position, deflects air passing through the cold flow air duct of a turbofan engine in a direction such that it approximates the theoretical air flow line and does not enter a cavity defined by the interior of the thrust reverser door when the door is in its closed position. A linkage mechanism connects the air deflector to the door actuator, such that, when the door is moved to its opened or thrust reversing position, the deflector is moved to a second position so as to minimize its interference with the thrust reversing air flow.

Abstract: To quickly change rocket flight direction immediately after a rocket has been launched without increasing the wing area, the rocket flight direction control system comprises four steering wings for controlling rocket flight directions; four deflectable nozzles for jetting combustion gas backward to generate rocket thrust; a controller for generating steering control signals; and at least one actuator for actuating the deflectable nozzles in response to the steering control signals in synchronism with steering motion of the steering wings. Further, when the deflectable nozzle is divided into two, fixed and movable, nozzles, the diameter of the outlet end of the fixed divergent nozzle of the overexpansion type nozzle in matched with that of the movable nozzle for prevention of gas leakage through a gap between the two nozzles.

Abstract: An actuation system for pivoting a blocker door and blocking and redirecting airflow through cascades during thrust reversal of an aircraft. The system is operated when an engine nacelle thrust reverser sleeve assembly is opened and then closed.

Abstract: An external fairing flap (26) is provided with an hydraulic spring (42, 44) for causing the external flap (26) to follow the motion of an exhaust nozzle control flap (18). The external flap (26) is hinged (32) at the leading edge thereof, and contacts the control flap (18) via corresponding rubstrips (40, 36) at the flap trailing edges (28, 38).

Abstract: The present invention relates to an improved thrust reverseer door structure having a deflector that will reduce the aerodynamic losses and thereby increase the operating efficiency of a turbofan engine. The deflector has a first portion that extends generally radially inwardly when the door is in its retracted position and a second portion extending in a downstream direction from the distal edge of the first portion. The downstream facing second portion is located adjacent the inner surface of a secondary-duct wall and serves to deflect the air passing through this annular space away from an inner, concave portion of the thrust reverser door. The deflector may also include aperatures in the first portion to allow passage of the thrust reversing gases when the door is in its extended position. A baffle may also be attached to the first portion so as to extend at an angle over the aperatures.

Abstract: A seal assembly (28) is provided for sealing between a static sidewall (12), a rotating first member having a flat and annular surface (22) disposed therein, and a concentric rim (34) disposed between the sidewall (12) and first member (22). The rim (34) is supportably secured to an arcuate hood (18) which extends axially from the rim (34).

Abstract: A sensor (20) is mounted on a fixed torque box (8) carried by a fixed portion of an engine nacelle (6). A target plate (40) is resiliently mounted on a thrust reverser translating cowl (10). A cylindrical sleeve (32) is attached to the sensor (20) and surrounds its outer sensing end (22). The outer radial surface (34) of the sleeve (32) is spaced beyond the sensing end (22) a predetermined distance (100). The surface (34) contacts the target plate (40) when the cowl (10) is in its closed position. The resilient mounting of the plate (40) compensates for inaccuracies in the installation of the plate (40) and allows relative movement between the cowl (10) and the plate (40) when the cowl (10) is in its closed position to maintain a fixed gap (100) between the plate (40) and the sensor (20).

Abstract: Gas turbine engines, usually of the kind which include ducted fans, have cowl structures which generate drag inter alia by virtue of their frontal area. Where the cowl is of very large diameter i.e. in the order of 3 to 4 meters, if known devices such as thrust reverser cascades are installed in them, the frontal area and weight of the structure would be unacceptable. The invention provides a cowl structure of the magnitude mentioned hereinbefore, in which an improved cascade is installed. The or each cascade comprises a pair of rectangular frames which are joined by vanes. The vanes are pivotably connected to the frames in the manner of parallel rules as used in navigation. When non operative, the frames are stowed in superimposed relationship and thus enable a thinner cowl to be utilized than is possible in known cascade storage arrangements.

Abstract: A nozzle 16 for a turbojet is provided with a thrust deflector mechanism, downstream of the nozzle in the form of one or more target-type thrust reverser plates 18. The plate or plates 18 are movable from a stowed position into the efflux of gases issuing from the nozzle to deflect the exhaust gases and hence redirect the thrust produced by the nozzle obliquely relative to the central axis of the nozzle 16. The plate or plates 18 are mounted in a bearing for rotation about the longitudinal axis of the jet pipe. When rotated the redirected thrust is effectively rotated relative to the central axis of the nozzle. In one embodiment a pair of plates 18 is used and they can also be employed as a conventional thrust reverser.

Abstract: A thrust vectoring exhaust nozzle (6) is provided with a vent bypass (38) and flow control valve (44) to vent a portion (43) of the exhaust gas (2) only during diversion of the exhaust gas (2) into an alternative gas flow path (18).

Abstract: An exhaust nozzle for a gas turbine engine comprises a substantially tubular duct structure to which is mounted flow directing flaps for varying the throat area of the nozzle. The duct structure is progressively shaped and deformed as it extends in a downstream direction to provide straight upper and lower lips to which respective upper and lower flaps are pivotally attached for selectively vectoring the exhaust flow. The opposing sidewalls extend vertically within the duct structure and protrude therefrom between which the flaps and exhaust orifice is thereby defined within an essentially tubular duct.

Abstract: A common mechanism enables both throat area change in either a fan duct or an exhaust gas duct and flow deflection at the nozzle of the duct.

Abstract: A convergent-divergent jet exhaust nozzle has an aft end with an exit area thereat and a throat area spaced from the exit area and forward thereof. The ratio of the exit to throat diameter is from 1.00 to 1.05. Each of two symmetrical blocker doors has an axis coincident with the axis of the nozzle. Each of the blocker doors has opposite forward and rear edges and a surface extending between the edges. Each of the blocker doors is pivotally mounted to pivot about a pivot axis transverse to the axis of the nozzle and disposed downstream of the engine in the nozzle. The pivot axes are in a plane intersected by the axis of the nozzle.

Abstract: An adjustable two-dimensional nozzle is disclosed in which simplified control means are located away from the flow of gasses through the nozzle. The nozzle includes a movable frame located outside of fixed sidewalls and has pivotally attached thereto a pair of upstream or converging nozzle flaps. Upstream edges of the upstream flaps are attached to the movable frame such that the flaps pivot about axes extending substantially perpendicular to the longitudinal axis of the nozzle. Downstream or diverging flaps are attached to the downstream edges of the upstream flaps such that these flaps also pivot about axes extending substantially perpendicular to the longitudinal axis of the nozzle. A cam member extends between each of the movable frames and each downstream flap to control the angular variations of the flaps during movement of the frame.

Abstract: A linkage for area controlled thrust vectoring comprising of vane cascade (26) having a plurality of vanes (28, 29, 30) pivotable in unison and a flow regulating vane (36) oriented to provide a constant collection gas flow area is provided with a mechanical linkage for orienting the vanes (28, 29, 30) and the flow regulating vane (36) responsive to a single linear actuator (59).

Abstract: A two dimensional exhaust nozzle for a gas turbine engine having reverse thrust capability includes a pair of spaced apart converging flaps which are able to rotate about their respective axes until their downstream edges meet along the engine centerline to block the flow of gases through the engine and to redirect the flow through fixed area reverser outlet ports. The axes about which each convergent flap rotates are spaced inwardly from their respective convergent flap surfaces. The flaps themselves cover the outlet ports when the flaps are in forward thrust operating positions. The flaps move away from and unblock the outlets as they rotate to their reverse thrust position. The distance between the flap axis and its convergent surface is critical to being able to use short flaps while obtaining large reverser outlet areas.

Abstract: A propulsion nozzle of a gas turbine engine comprising two mutually confronting spaced fixed side walls 14, 16 and two upper and lower mutually confronting spaced movable walls 20, 22 which locate and move in trackways 18 in the side walls. The movable walls 20, 22 each comprise a plurality of pivotally interconnected members which extend transverse to the fixed walls to define a convergent part and throat of the nozzle.A flap 28 is pivotally connected at its upstream end to a downstream end of one of the movable walls 20(b) and is operable, in at least one mode of operation, to cooperate with the fixed walls to define a divergent expansion ramp downstream of the throat of nozzle. In a first mode of operation, the movable walls 20, 22 can be moved along the trackway 18 to cause the members to define a con-di nozzle facing rearwards to produce forward thrust.

Abstract: A convergent/divergent gas turbine engine exhaust nozzle having reverse thrust capability includes a door which blocks a reverse flow outlet port when the nozzle convergent flap is in any forward thrust operating mode. The door is coupled to the convergent nozzle flap such that it opens as the convergent nozzle flap moves to a reverse thrust position and the flap directs the exhaust gases through the reverser outlet.

Abstract: The invention concerns a gas generator with a fuel gas filter for the pyrotechanical production of gases from a propellant charge. A separator chamber is disclosed that is designed with annular slots for the purpose of cleaning gas contaminated with solid residue from combustion. The gases produced in the combustion chamber enter the separator chamber through tangentially arranged gas ducts. After flowing through the annular formed separator chamber, the gases flow around the frontal area of the central axially arranged center block before they reach the guidance components, which are sensitive to soiling. Subsequently, the hot gases exit by way of a jet. Through the effect of centrifugal forces, the contaminating particles are slung against the outer wall of the annularly slotted separator chamber and are held fast in its special profile.

Abstract: A thrust reverser for a gas turbine engine of the type to power an aircraft, the thrust reverser comprising a first pair of half round doors nesting in a second pair of half round doors and both being pivoted on an axis extending diametrically of a jet pipe for the gas turbine engine. Each of the first pair of half round doors having a downstream edge which has a scarfed portion thereon and each of said second pair of half round doors having a downstream edge which is fully scarfed, the scarfed portion of said first pair of half round doors and the scarfed edges of said second pair of half round doors abutting when said doors are in a thrust reversing position with said second pair of half round doors preventing axial spillage of efflux. When said first pair and said second pair of half round doors are in non-thrust reversing position, said first pair of half round doors forming a greater portion of a nozzle throat and said scarfed portions of the downstream edges thereof reducing side spillage of efflux.

Abstract: A thrust vector control apparatus for selective deployment of a vane within n exhaust stream has the vane mounted on the periphery of an exhaust nozzle for pivotable movement between a retracted position without the stream and an inserted position within the stream. A pivotally mounted link assembly is used with an actuator to urge the vane into the stream. The link assembly becomes locked in place upon the full insertion of the vane. This locked position precludes unintended pivotal motion of the vane; however, rotational motion of the vane is still possible due to the pivotal connection of the link. A second actuator rotates the vane in the stream, thereby controlling the direction of the stream.

Abstract: A thrust vectoring and reversing exhaust nozzle structure for a gas turbine engine is described which comprises a rotatable flap mounted within the exhaust duct of the engine, and being rotatable about an axis of rotation extending transverse of the exhaust duct and substantially central of the flap, control means for rotating the flap between an open position allowing substantially unrestricted exhaust flow through the nozzle and a closed position substantially closing the exhaust duct, and a cascade of rotatable vanes in the engine housing structure operatively interconnected with the flap for rotation to an open position in response to rotation of the flap to the closed position.