Abstract: The present invention relates to a gas turbine engine which is provided with a thrust reverser with unfoldable doors and which is of the double jet type, i.e. comprising a central generator emitting a jet of hot gas and surrounded by an annular by-pass conduit through which a jet of relatively cold gas passes, wherein said turbine engine comprises means for restricting the passage of the jet of relatively cold gas in said annular by-pass conduit when the doors of the thrust reverser are unfolded. The invention results in a simplification of the structure of the doors of the thrust reverser.

Abstract: A ducted fan propulsion plant has a reversible-pitch fan driven by a core gas turbine engine and housed in a duct which terminates at its downstream end in an outlet nozzle defined between two semi-cylindrical shells. The shells are mounted for movement hydraulically both axially and angularly to define an increased effective nozzle area for take-off. Upon further rearward axial displacement the shells adopt a reverse-thrust position to define air inlets to the fan when the fan blade pitch is reversed.

Abstract: A rocket motor equipped with a movable nozzle is provided with pneumatic pressure system for the operation of the mechanism for moving the nozzle with a gas for the pneumatic supplied from a gas generating propellant separate from the main propellant but located within the motor itself.

Abstract: A jet pipe arrangement is provided for the propulsion and control of an aircraft, which arrangement includes a first stationary pipe section which has a second pipe section fitted with a thrust nozzle attached thereto. To facilitate a simply constructed and operated control arrangement for rotatably moving the second pipe section with respect to the first pipe section, two pairs of angle levers are disposed about the circumference of the first pipe section. The first pair of angle levers are located opposite one another on the first pipe section and have pivot fulcrums located in the plane parallel to the vertical pivot axis of the second pipe section. The second pair of angle levers are likewise located at respective opposite sides on the circumference of the first pipe section and include pivot fulcrums located in a plane parallel to the horizontal pivot axis of the second pipe section.

Abstract: A slot seal closure apparatus for use in an aircraft engine mounting strut comprises at least one door which covers a slot formed in the strut to accommodate fore/aft movement of a portion of the engine cowl. When the engine is in a cruise mode, the movable portion of the cowl is in its forwardmost position disengaged from the slot and the door is in a first position covering the slot so as to prevent airflow through the slot. When the engine is placed in a reverse mode, the movable portion of the cowl moves aft and the door swings to a second position spaced from the slot in reaction to the aft movement of the cowl portion so as to expose the slot thereby enabling the movable portion of the cowl to engage the slot.

Abstract: A thrust reverser is provided for use with an asymmetric aircraft gas turbine engine exhaust nozzle. The thrust reverser includes a movable aerodynamic flap downstream of the asymmetric nozzle casing which is rotatable about one pivot in order to effect in-flight thrust vectoring through deflection of the exhaust stream, and which is also independently rotatable about another pivot to effect thrust reversing. In the reverse thrust mode, the leading edge of the flap is immersed into the exhaust stream, thereby splitting the stream into two portions, one of which is deflected upward and forward by a turning vane incorporated into the leading edge of the flap, and the other portion of which is deflected downward and forward by a hinged lip connected to the flap trailing edge. The thrust reverser thus permits the exhaust stream to be ejected in the vertical plane to produce reverse thrust without an accompanying pitch moment even though the exhaust nozzle is not symmetrical in the vertical plane.

Abstract: A suspension system for a pivotal nozzle of a jet propelled vehicle having a gas generator operable to effect propulsion of the vehicle, the system comprising a plurality of actuators connected to the exhaust nozzle and operable to effect pivotal movement thereof to steer the vehicle in a desired direction. Each actuator comprises a movable member connectible on one side to a source of fluid power to effect nozzle movement with the other side of the member being interconnected with said other side of each other actuator movable member to form a fluid suspension for the nozzle. In use, the suspension is pressurized to produce a force acting on the nozzle in a direction opposite to the load imposed on the nozzle by the gas from the gas generator acting thereon.

Abstract: A flight maneuverable gas turbine exhaust nozzle is provided with cooperating variable internal converging-diverging flaps to provide area control. A flap downstream of the converging-diverging flap provides flight maneuver vectoring as well as external exhaust expansion control. A vertical take-off and landing capability is provided by deployment of a rotating bonnet-type deflector which diverts the exhaust stream downward around one side of the exhaust nozzle. The nozzle throat rotates with the deflector to produce efficient turning of the exhaust stream.

Abstract: Compositions consisting essentially of about 1 weight percent carbon black, rom about 20 to about 35 weight percent polytetrafluoroethylene and from about 79 to about 64 weight percent of a material selected from the group consisting of isobutylene-isoprene copolymer and ethylene-propylene rubber are disclosed as being useful as protective fillers in situations where the protective filler is subjected to high temperatures and pressures.

Abstract: A jet deflecting device has a first rotatable pipe section connected to the nd of an engine jet pipe and a second pipe section rotatably connected to the end of the first pipe section. Nozzle flaps are provided at the end of the second pipe section, and coupled to be moved inwardly and outwardly in response to axial movement of a nozzle actuating skirt slidably mounted at the end of the second pipe section. A first drive motor on the stationary jet pipe directly rotates the first pipe section by way of driving gears. A second drive motor is coupled by gears to rotate the second pipe section independently of rotation of the first pipe section, and a third drive motor is provided for rotating an angular gear carrier on the second pipe section independently of the angular position of the two pipe sections. An angle drive mechanism is provided for converting rotational movement of the angular gear carrier to axial movement of the nozzle actuating skirt for control of the nozzle flaps.

Abstract: A streamline shroud surrounding a jet aircraft engine terminates forwardly of the aft end of the engine tail pipe, which comprises a secondary nozzle. Two or more deflector doors in stowed position combine to form a sleeve surrounding the aft portion of the tail pipe, and the trailing edges of these doors extend downstream and converge beyond the tail pipe to form a primary nozzle, which has an exit flow area smaller than that of the secondary nozzle, and of proper size and configuration to provide required mass flow, velocity and pressure for normal flight operation. The doors swing outwardly and rearwardly on linkage carried by the sponsons to a deployed position spaced aft of the tail pipe and disposed transversely to the tail pipe axis to deflect flow laterally and nullify thrust.

Abstract: The gimbal ring nozzle-trim comprises a substantially cylindrical forward control housing mounted to the discharge portion of a marine propulsion device, and having a frustra-orbicularly configured gasket-race flange at its rearwardmost terminal end; an annular gimbal ring mounted to the exterior cylindrical walls of the housing by pins disposed along the horizontal plane cutting the ring and housing distally forward of the gasket-race flange; and a nozzle having a hollow semi-orbicular portion which overrides the gasket-race flange and a substantially cylindrical portion issuing rearwardly from the orbicular portion of the nozzle, the nozzle being mounted by the forward interior surfaces of the orbicular portion to the exterior circumferential face of the gimbal ring by pins disposed through the nozzle into the gimbal ring along the vertical plane cutting the nozzle and gimbal ring.

Abstract: An integrated nozzle is designed to deflect the jet from a waterjet pump in a watercraft before it leaves the nozzle for watercraft steering. The nozzle may be so configured to be steerable in both the horizontal and vertical planes. The integrated nozzle and steering mechanism with thrust reversal mechanism attached thereto allows a full thrust capability without appreciable friction losses inherent in conventional waterjet steering buckets.

Abstract: A flexible duct assembly comprising axially first and second duct parts, a mounting system adjustably supporting the second duct part with respect to the first duct part, a primary seal between complementary relatively movable surfaces of the first and second parts, and a secondary seal between the first and second duct parts, the secondary seal being afforded protection from the interior of the duct assembly by the primary seal. The secondary seal may be an annular sliding seal or an annular strip of elastomeric material bonded on opposite sides to relatively movable facing surfaces of the first and second parts.

Abstract: A universal joint permitting relative angular deflection of two members, vided with transverse stiffness augmentation means which minimize rotational performance penalties. One member contemplates a receptacle adapted to receive in spaced-apart relation therefrom an annular plug formed on the other member. A rolling seal is positioned between the receptacle and plug. Tabs, segments or rings are placed on the annular plug and/or the confronting wall of said one member to increase the transverse stiffness under all load conditions, particularly at angle orientations of the aforesaid two members.