Abstract: A rotary piston engine comprises a housing having a trochoidal peripheral wall and side walls on both sides thereof, a rotor adapted to perform a planetary rotary motion along the inner surface of the peripheral wall, and intake and exhaust ports formed in the housing. The engine performs intake, compression, combustion and exhaust strokes of a working fluid in accordance with the planetary rotary motion of the rotor. An air injection port is formed in the peripheral wall of the housing between the exhaust port and a portion of the minor axis of the trochoidal curve, being adapted to communicate with the intake chamber formed between the peripheral wall and the rotor.
Abstract: A cable controlled apparatus comprises a housing having a control member movably mounted therein and adapted to actuate a directional control valve or the like. The cable is threadably mounted in a bracket, mounted on the housing, to selectively move and adjust the position of the valve control member upon rotation of the bracket. A clamping member is mounted on the housing and has an annular groove defined thereon for retaining a flanged base of the bracket therein whereby axial movement of the bracket is prevented upon rotation thereof.
Abstract: A fuel feed control comprising a device for a metered fuel supply to the combustion chamber of a gas-turbine engine, a valve to maintain a preset fuel pressure differential across the actuator element of the metering device, and a corrector of the rate of fuel feed to the combustion chamber depending upon the ambient air temperature. The actuator element, corrector and valve are mounted in respective parallel passageways which connect the fuel pump with the combustion chamber of the gas-turbine engine.
December 2, 1975
Date of Patent:
July 12, 1977
Vasily Petrovich Dmitriev, Andrei Alexandrovich Luzhin, Anatoly Mikhailovich Polyakov, Alexandr Grigorievich Tomilin, Stanislav Mikhailovich Shushpan
Abstract: Fuel control apparatus including a fuel conduit connected to receive pressurized fuel from a fuel pump and provided with fuel servo actuated metering valve means therein for controlling the rate of fuel flow therethrough to an engine. The fuel servo actuated metering valve is actuated by a fuel servo piston pressurized by a servo valve controlled fuel pressure differential derived from a predetermined fuel pressure differential maintained by a pressurizing valve downstream from and in series flow relationship with the metering valve. The metered fuel flow for actuating the servo piston is extracted from the fuel conduit upstream from the pressurizing valve and returned to the fuel conduit downstream from the pressurizing valve.
Abstract: A rotary internal combustion engine comprising a generally cylindrical stator member having two pairs of sockets located in the periphery thereof, and a rotor member mounted to rotate about the stator member. Two pairs of opposing wedges are pivotally mounted at their vertices on the periphery of the stator member to pivot in and out of respective ones of the sockets as the rotor member is caused to rotate about the stator member. The rotor member has side walls and an interior peripheral wall which, in cooperation with the periphery of the stator member and the two pairs of pivotal wedges, define a combustion cavity and a compression cavity there between. The combustion cavity and compression cavity are disposed on opposite sides of the stator member adjacent the periphery thereof.
Abstract: Fuel distribution apparatus comprising a jet and two valves arranged in parallel in a passage connecting the fuel delivery line to the main manifold. The first valve maintains a predetermined pilot manifold pressure required for steady combustion of the fuel delivered through the pilot manifold. The second valve has a flow area greater than that of the jet and the first valve. When engine speed is reached at which the combustion of the fuel delivered through the main manifold becomes steady, the second valve opens and allows fuel to flow therethrough, effectively bypassing the jet and the first valve.
September 23, 1975
Date of Patent:
July 5, 1977
Vasily Petrovich Dmitriev, Anatoly Mikhailovich Polyakov, Alexandr Grigorievich Tomilin, Stanislav Mikhailovich Shushpan
Abstract: An emergency hydraulic power system for aircraft which becomes operable upon aircraft engine failure includes a hot gas turbine for driving a hydraulic pump, a decomposition chamber to provide hot gas for driving the turbine, a normally unpressurized fuel storage tank, and a fuel pump for delivering fuel from the tank to the decomposition chamber. A start system includes a start fuel bottle having a cell filled with fuel and provided with a movable wall, and a cylinder of gas under high pressure which is regulated to put intermediate pressure on the movable wall and expel fuel from the cell, and also to put low pressure on the fuel tank, after a start valve is opened. Both the fuel tank and the start fuel cell communicate with an inlet conduit which goes to the fuel pump inlet, and a valve is provided to prevent start fuel from going into the fuel tank; and there is also means normally blocking communication from the start bottle and the tank to the pump inlet.
Abstract: A multiple fuel supply or an internal combustion engine wherein phase separation of components is deliberately induced. The resulting separation permits the use of a single fuel tank to supply components of either or both phases to the engine. Specifically, phase separation of a gasoline/methanol blend is induced by the addition of a minor amount of water sufficient to guarantee separation into an upper gasoline phase and a lower methanol/water phase. A single fuel tank holds the two-phase liquid with separate fuel pickups and separate level indicators for each phase. Either gasoline or methanol, or both, can be supplied to the engine as required by predetermined parameters. A fuel supply system for a phase-separated multiple fuel supply contained in a single fuel tank is described.
March 9, 1976
Date of Patent:
June 28, 1977
The United States of America as represented by the United States Energy Research and Development Administration
Abstract: A device for actuating a sheathed control cable comprises a push button wh is movable to apply a tension to the cable. An inclined surface rigid with the push button engages, via a ball, a traction member anchored to the cable. When the button is depressed the inclined surface displaces the traction member via the ball whereby the cable is tensioned. The ball rolls along the inclined surface during this movement whereby such movement occurs substantially without friction.
July 14, 1976
Date of Patent:
June 28, 1977
SICMA - Societe Industrielle et Commerciale de Materiel Aeronautique
Abstract: Air-cooled two stroke internal combustion engine having a cooling air blower driven by the engine and a lubricating oil pump for supplying lubricating oil to the engine, said lubricating oil pump being housed in the hub portion of the blower.
Abstract: A rear view mirror having a pair of mirror panels with different reflective surfaces angularly disposed with respect to each other, one of which is used during the day, the other at night when driving, and means from within the vehicle to shift the mirror for use of either mirror panel.
Abstract: A thrust reverser suitable for reversing the flow direction of the fan air of a fan jet engine is disclosed. The thrust reverser comprises a cascade section and a fan duct blocker section. The cascade section includes a series of cascade elements mounted in a side-by-side manner about a portion of the engine nacelle for rotation through an arc of 90.degree. about longitudinal axes lying generally parallel to the direction of fan air flow. Each cascade element includes an inner panel, an outer panel, and a series of vanes located between the inner and outer panels. Rotation is between a closed position whereat the inner panel forms a portion of the fan air duct and the outer panel forms a portion of the outer surface of the nacelle, and an open position whereat the vanes define passageways adapted to reverse fan air flow i.e., direct fan air flow back toward the front of the engine.
Abstract: A rotating piston engine for use as a combustion engine, air or gas compressor, water or hydraulic pump or motor, and the like. A stator supports a rotor which is bored to receive a double acting piston journalled on the crank of an eccentric mounted crankshaft. The crankshaft penetrates the rotor and cylinder wall in a manner to reduce the overall dimensions of the engine. Inlet and outlet ports are provided with a slide valving arrangement adapted for operation in four-stroke cycle combustion engines.
Abstract: This invention relates to a fuel distribution valve for a turbine type power plane capable of supplying fuel to a set of primary nozzles and proportioning the flow to a set or sets of secondary nozzles upon initiation of a command signal which may be manifested by the fuel control.
Abstract: This invention relates to fuel controls for turbine types of power plants and to the means for resetting the idle speed and stator vanes from a single point contact. In one embodiment, fuel flow is reset by changing the hydraulic forces on the throttle valve and its control system which serves to provide a W.sub.f /P.sub.3 .times. P.sub.3 control function, where W.sub.f = fuel flow in pounds per hour and P.sub.3 = compressor discharge pressure in pounds per square inch absolute. The profile of the 3-D cam utilized to control the stator vanes is also utilized to set the droop schedule of the idle speed setting controlled by the fuel control.
Abstract: A fuel distributor valve for splitting and proportioning fuel feeding more than one set of fuel nozzles of a turbine type power plant is improved upon by adding thereto means to prefill the secondary nozzle and its attendant manifold and fuel passages immediately preceding actuation.
Abstract: A thrust reverser cascade section comprising a plurality of cascade windows mounted in an engine nacelle rearwardly of the fan air compressor, each cascade window including a plurality of cascade elements, is disclosed. The cascade elements are rotatable through an arc of 90.degree., more or less, between closed and open positions, along axes lying generally parallel to the longitudinal axis of the nacelle. The cascade elements include deflecting vanes and are generally S-shaped when viewed in cross-section. Adjacent cascade elements abut one another in both their open and closed positions. Seals are located in the regions of abutment. The vanes direct fan air flow from the fan air duct toward the front of the nacelle when the cascade elements are in their open position. Each cascade window also includes sealing end plates adapted to move into and out of sealing relationship with the cascade elements to seal the ends when the cascade elements are closed.
Abstract: The present invention provides a rotary internal combustion engine comprising a stator, and a rotor journalled for rotation in said stator, said stator considered in a plane normal to its axis of rotation having a cross-section which is approximately an equilateral triangle with curvilinear sides, each side of said rotor having its external peripheral surface defining with the internal periphery of said stator a respective combustion chamber, the external peripheral surface of each side of said rotor including considered in the direction of rotation of said rotor an upstream surface portion having a relatively great radial component so as to receive maximum rotary thrust from the expanding combustion gases, an intermediate surface portion which is curvilinear and which extends from said upstream surface portion so as with said upstream surface portion to define relative to the internal periphery of the stator a part of the combustion chamber and receive less thrust than said upstream portion, and a downstream
Abstract: Vane type rotary combustion engine in combination with a compressor apparatus for supplying a charge of air or an air-fuel mixture to the engine. The engine and compressor are drivingly connected to each other and include a conduit connecting the compressed charge outlet of the compressor to the intake port of the engine so that a compressed charge may be led into the engine. The engine includes a rotary-vane assembly wherein a series of rotatable chambers are provided therein, with a rotatablecombustion chamber of relatively low volume rotating past the intake port. A timed valve closes the intake port after which ignition of the charge in the combustion chamber takes place and effects a power stroke against a rotary-slide vane. A continuous succession of power strokes are effected by successive rotary combustion chambers formed by rotary-slide vanes.
Abstract: An internal combustion four cycle engine is provided with a plurality of stationarily mounted cylinders radially arranged in equal spaced apart relationship within the inner circumference of a rotatably mounted drive drum and in parallel relationship with the axis of rotation thereof, a movable track anchorably supported by a pair of oppositely disposed raised lobes fixed to the interior webbed surface of the drum and comprised of two pairs of declining slope track quadrants serving to receive the driving thrust of each piston during its power stroke and to activate each piston during its intake, compression and exhaust strokes, and a cam ring fixed to the inner circumference of the drive drum serving to activate an intake-exhaust slide of each cylinder commensurate with the requirements of its intake, compression, power and exhaust strokes.