Abstract: An annular, radial flow gas turbine engine and airborne vehicle utilizing same for jet propulsion. The engine comprises counter-rotating rotors and a compressor section with counter-rotating annular rows of intermeshing compressor blades, an annular combustion section common to both rotors wherein the combustion zone is defined by oppositely rotating rotor walls, and a turbine section made up of annular rows of counter-rotating exhaust turbine blades. No stator blades are present in either the compressor or the turbine sections.The craft comprises a central hub on which the engine rotors rotate on thrust bearings, and air bearings maintain rotor tolerances with respect to each other and to nonrotating shell portions above and below the engine rotors. Air inlet guide vanes leading to the compressor section are also housed in the hub portion of the craft.

Abstract: An exhaust stub for a turbo-prop engine which exits from the aircraft nacelle at a location other than the aft end. A fairing is attached to the exhaust stub to minimize frontal area for a given exhaust stub exit area, but free of the nacelle, because of the requirement for the exhaust stub to move relative to the nacelle. An end plate is secured about the exhaust stub and fairing, substantially parallel to and at close proximity to the nacelle. The end plate effectively improves the performance of the fairing, by eliminating the effect of the gap in the nacelle around the stub and also the gap between the fairing and the nacelle. Improving the performance of the fairing reduces the magnitude of the exhaust duct wake which in turn reduces the momentum definiency in the wake flow; reduces exhaust duct drag; reduces mixing of the exhaust gases into the wake region; and reduces nacelle sooting by exhaust gases.

Abstract: A logic controlled take-off warning system having a circuit for enabling the logic controlled take-off warning system at engine thrust levels exceeding a predetermined value which is less than minimum take-off thrust of the aircraft and greater than trust required for normal ground operations, provided also that the aircraft is on the ground. When the logic controlled take-off warning system is enabled, a take-off warning horn is subsequently energized when any one of a plurality of undesired take-off configurations exists.

Abstract: This invention relates to a seal adapted to prevent leakage at the interface of a movable plug with articulated panels and the side wall of a two-dimensional nozzle for a gas turbine engine. The seal prevents the high pressure cooling air internal of the plug from escaping to the lower pressure exhaust gases and comprises judiciously located dam-like members installed in the vent slots in the side wall fabricated from Finwall.RTM. material which material achieves indirect heat exchange relation and film cooling.

Abstract: A hydraulically driving and controlling - unit comprises a power plant which drives a fluid flow producing device for the separate production and supply of pairs of flows of hydraulic fluid under pressure. The unit supplies at least one pair of flows to at least two fluid motors. Rates of flow in flows are proportionate to each other whereby motors of same pair of flow are actuated and maintained to act with to each other proportionate speed of motion. Unit may be transportable and adaptable to machines or vehicles. The drive unit may include a plurality of power plants and fluid flow producing devices. In such multiple unit one way valves are set into fluid lines which may combine partially after those one way valves for directing each one flow from a different power plant to the same motor. Thereby the unit can continue to operate, when one of the plurality of power plants fails.

Abstract: An exhaust nozzle for exhausting the effluent of a turbofan gas turbine engine across a portion of the upper surface of an aircraft wing wherein the exhaust nozzle is arranged to establish a temperature profile within the exhausted gases that prevents overheating the wing surface. The nozzle includes a contoured outer housing that longitudinally transists from a circular entrance opening, arranged for interconnection with the rear face of a gas turbine engine, to a semi-elliptical outlet opening located on the upper surface of the aircraft wing. A generally tubular mixer section, of the daisy type, is mounted within the outer housing and coaxially surrounds an engine tail plug.

Abstract: An aircraft jet propulsion power plant is fitted with a sliding ejector sleeve for the provision by selection, of an auxiliary flow of ambient air within the sleeve so as to quieten the noise of the gas efflux. The sleeve is mounted independently of the power plant and is supported from a side of the aircraft fuselage. The sleeve mounting structure has an arm which projects into the fuselage to provide a further mounting point, the reaction loads of which act downwardly so as to counteract the downwardly acting weight of the cowl on the side mounting.

Abstract: A logic controlled APR system including arming logic, engine failure detection circuits, and test circuit means for testing system operating condition without engine operation. The logic controlled APR system detects an engine failure in a multi-engine aircraft and provides solenoid controlled increased fuel flow to the remaining normally operating engines, and includes a disarm mode in the event of an RTO (rejected take-off).

Abstract: A jet thrust aircraft wing wherein the intake and exhaust are substantially coextensive with the leading and trailing edges, respectively; utilizing engine suction to induce intake of air and preventing build-up ahead of the wing by separating the same from the flow of air over and under the upper and lower wing surfaces; and utilizing engine exhaust thrust to induce controllable air flow through the wing and to induce longitudinal flow of air over and under the wing throughout its span.

Abstract: An aircraft body has a pair of hydraulic fluid operated motors mounted on it, a pair of stream-creating devices driven by the motors and symmetrically arranged on opposite sides of the axis of symmetry of the body. One or more hydraulic fluid-flow producing devices has at least a pair of separate fluid-handling chambers each connected to one of a pair of separate outlets, and including arrangements for fluid-tight separation of the chambers and outlets, so that fluid from each chamber passes through only one of the outlets. A pair of displacement units is associated with the fluid-handling chambers, respectively, and an equally acting actuator arrangement cooperates equally with both of the two displacement units for maintaining equal movements of the two displacement units so that fluid flows in the outlets at proportionate and equal flow rates. A pair of delivery passages connects each of the outlets with a different one of the motors, respectively.

Abstract: A logic controlled APR system including arming logic, engine failure detection circuits, and system fault detector circuit means for monitoring system integrity. The logic controlled APR system detects an engine failure in a multi-engine aircraft and provides increased fuel flow to the remaining normally operating engines, and includes a disarm mode in the event of an RTO (rejected take-off).

Abstract: A method of controlling flow attachment to the wing and flap surfaces of an upper surface blowing type aircraft by horizontally controlling the divergence of the jet exhaust of the aircraft engines to control the vertical thickness of the exhaust is disclosed. In addition to controlling the thickness of the exhaust, control of the divergent exhaust also provides control over the outward velocity component of the exhaust which further provides control over flow attachment by controlling the flow of ambient air under the jet exhaust. In one form, the apparatus of the invention comprises one or more side panels, located at the end of the engine exhaust nozzle, adjacent to the surface of the wing. When the panels are moved outwardly, openings are formed which allow the exhaust to horizontally diverge. When the panels are moved inwardly, the openings are closed and the exhaust is no longer diverted and thinned.

Abstract: A convertible auxiliary turbine capable of providing turbopropeller thrust interchangeably with pure jet propulsion, comprising a controllable fluid deflector element, and an inverted free-floating rotor having planular drive-vanes aligned with the normal flow direction of the engine's gas stream. Thus, no rotative force is imparted to the turbine until the flow direction is varied. At a given change, the turbine begins to spin, outboard swingable propeller blades are urged to open by action of centrifugal force, and propeller thrust is generated in ratio to the angle of deflection, with jet power in inverse ratio thereto.

Abstract: An airplane with an electric motor and rechargable battery pack are disclosed herein. The electric motor is of the high performance variety (i.e., it has a very high power rating for its size and weight). Means are provided for producing a high velocity blast of cooling air directly onto the rotating armeture for rapidly dissipating the waste heat generated inside of the motor. Means are also provided for obtaining a large power output from the battery pack and for very rapidly recharging the battery pack. A remote control system is included for controlling the operation of the airplane from a remote location.

Abstract: A gas turbine turbojet engine for a supersonic aircraft which fits into a nacelle having a substantially square cross-section. Air flow passing between the square section of the nacelle and the circular section of the engine is compressed by an auxiliary compressor driven by a compressor of the turbojet. The auxiliary compressor is housed within a diameter not greater than the maximum diameter of the turbojet, thus enhancing the engine performance particularly at take-off.

Abstract: The wings of an electromotorically drive aircraft have span wise extending central wing cases whose interior serves as battery cells. Load bearing transverse walls take up bending stresses reacted into such walls by tops and bottoms of such central wing case. These tops and bottoms may constitute the electrodes of the battery. Leading and trailing edge-profile completing wing cases are secured, possibly releasibly secured, to the transverse walls of the central wing case.