Abstract: A gas turbine engine thermal backbone deflection control apparatus to counter the effects of backbone bending due to nacelle aerodynamic, thrust, and maneuver loads by introducing a controlled backbone counter-bending moment by applying an uneven temperature or thermal field around the backbone to induce controlled compression and/or tensioning forces in the backbone or casing between axially spaced apart frames connected by the backbone. One embodiment of the invention provides for flowing thermal control air along an axially and circumferentially sector of the engine casing. The thermal backbone deflection control apparatus is controlled by the engines digital electronic control system using input signals generated by engine thrust load, inlet moment load sensors and/or blade tip clearance sensors.

Abstract: A combined combustion and steam turbine power plant which includes a steam turbine unit, a boiler unit for supplying steam to the steam turbine unit, and a combustion turbine unit with an exhaust gas duct structure for supplying the turbine exhaust gases to the boiler unit, has at least one heat recovery steam generator arranged in the exhaust gas flow downstream of the boiler unit and connected to the steam-turbine unit so as to supply any steam generated in the heat recovery steam generator to the steam turbine unit.

Abstract: A refrigerant gas suction valve mechanism for a reciprocating piston type compressor is disclosed. The mechanism has a drive shaft rotatably disposed in a gas receiving chamber where uncompressed gas is introduced, Double- headed pistons provided in cylinder bores compress the gas when the pistons move from the bottom dead center to the top dead center. A suction port selectively permits and blocks communication between the suction passage and the compression chambers. A resilient member holds a rotary valve in contact with an inner wall of a recessed chamber with predetermined force. The suction port is maintained at a predetermined distance from a point where the pistons reach the top dead center so that the suction port is closed by the pistons before the pistons reach the top dead center.

Abstract: The radial jets of a fuel nozzle for the combustor of a gas turbine engine are non-axisymmetrically disposed around the tip of the fuel nozzle to distribute the fuel into the swirler unevenly around the circumference to reduce pattern factor.

Abstract: Thrust modules are provided at the distal ends of a low aerodynamic drag rotor. The rotor is affixed at a central hub to a shaft, and rotates about an axis defined by the shaft. In the preferred embodiment the thrust modules are ramjet engines, and the ramjet inlet captures and compresses an impinging inlet air stream. The compressed air stream thus provides oxygen for mixing with a fuel which is supplied to the ramjet thrust modules from a convenient fuel source such as natural gas. The fuel is oxidized in the thrust modules to produce combustion gases. The gases expand, and the exhaust flow creates thrust which is substantially tangential to the circumference defined by the distal end of the rotor. The gases expand to motivate the ramjet engine to rotate about the shaft at supersonic thrust module velocities, producing shaft energy.

Abstract: A turbofan engine bypass and exhaust system has a double-hoop configuration in which a fan exhaust passageway comprises shells of a constant circular contour to resolve air pressure induced stresses and increase in bypass passageway area asymmetrically in the horizontal direction without substantially increasing the overall engine height.

Abstract: In a fuel injection pump including a plunger barrel provided with a fuel pressure chamber, a plunger which reciprocates within this plunger barrel to take in fuel from a fuel reservoir chamber and deliver this fuel from the fuel pressure chamber under pressure, and a timing sleeve which is positioned between the plunger and the plunger barrel such that it slidably mates with the outside of this plunger, and on which a spill port is formed; a fuel injection pump is characterized by an impingement-cushioning cavity being formed on the surface of the inside wall of the plunger barrel in a position opposite the spill port of the timing sleeve along with the peripheral surface of the timing sleeve being formed in a certain shape corresponding to this impingement-cushioning cavity.

Abstract: A rotary pump (10) is disclosed of the type including a rotating cylinder block (25) defining a plurality of cylinders (27), each defining an imaginary axis (a), which are uniformly spaced about an axis of rotation (A) of the cylinder block. A piston (29) is disposed for reciprocation within each cylinder (27) as the cylinder block rotates. The housing defines a fluid inlet (43) and a fluid outlet (45). In open communication with each cylinder (27) is a cylinder port (47), disposed for serial communication with the fluid inlet and fluid outlet as the cylinder block (25) rotates. Each cylinder port (47) defines a leading edge (L) which are disposed randomly relative to their respective imaginary axis (a).

Abstract: An apparatus for regulating the fluid throughput of a rotary screw compressor from a full capacity operating condition to a desired predetermined capacity operating condition includes a turn valve or spiral valve which is disposed in fluid communication with a low pressure fluid. A stepping motor positions the turn valve in a predetermined orientation. A position sensing means is operably connected to the turn valve. The position sensing means detects the angular orientation of the turn valve. A pressure sensing means detects a compressor service pressure. An electronic control means directs the stepping motor in a predetermined orientation. The electronic control means is independently operable to regulate the fluid throughput of the rotary screw compressor from a full capacity operating condition to a predetermined capacity operating condition in response to the first pressure sensing means.

Abstract: A gas turbine combustion system includes a plurality of combustors within a pressure vessel, each combustor including a combustion liner defining a combustion chamber having a reaction zone and a dilution zone, the liner in the dilution zone provided with a plurality of circumferentially spaced dilution air feed holes. A flow shield surrounds each combustion liner in radially spaced relation thereto for feeding compressor discharge air to the combustion chamber. Air staging apparatus directly controls the amount of compressor discharge air fed into each combustion chamber dilution zone via the dilution air feed holes.

Abstract: An apparatus and method for minimizing compressor casing distortion due to bleed air extraction wherein the compressor casing includes an annular outer casing having at least one outlet duct, an annular inner casing disposed co-axially with the outer casing and spaced radially inwardly therefrom to define a plenum, two radial discs extending inwardly from the outer casing defining a plenum, a plurality of small area bleed openings located in the inner casing for imparting a radial velocity to the bleed air greater than the circumferential velocity entering the plenum, an air tube located over each bleed opening, and a baffle plate located on top of the air tubes and communicating with the radial discs for supporting the casings, whereby the bleed air impinges on the outer casing and controls distortion by sufficiently reducing the circumferential temperature gradient forming at the outer casing.

Abstract: A gas turbine engine includes a fan, fan bypass duct, compressor, core duct, and turbine including a clearance control system. The core duct includes a bleed valve, the fan bypass duct includes a bleed vent, and a bleed pipe is disposed in flow communication therebetween. A feed pipe is disposed in flow communication between the bleed pipe and the clearance control system. The apparatus is effective for practicing a method of bleeding a portion of compressed air from the core duct to the fan bypass duct during a first mode of operation, and diverting a portion of the bleed air from the bleed pipe into the feed pipe for flow to the clearance control system at a low flowrate during the first mode. During a second mode of operation, the method includes bleeding a portion of the fan air from the fan bypass duct and through the feed pipe to the clearance control system while discontinuing bleeding of the compressed air from the core duct.

Abstract: A nacelle cooling and ventilation system for an aircraft gas turbine engine which includes a chin scoop and duct assembly for directing air through the engine bay where it is exhausted into the engine exhaust through an exhaust shroud eductor. The nacelle is enclosed so that effectively all of the cooling air entering the bay leaves the bay through the engine exhaust and is not dumped overboard, thereby adding to the effective thrust of the engine. An engine oil and generator oil heat exchanger is positioned in the cooling air duct into the bay so that the same air which cools the bay also cools engine and generator oil. The oil heat exchanger includes directional louvers which regulate and keep to a minimum the amount of cooling air and direct cooling air forwardly in the bay so that the entire bay area is cooled, and which can be shut as a fire control measure.

Abstract: A flight vehicle scramjet combustor. The combustor, in its "2-D" and annular embodiments, has two spaced-apart, generally opposing, and longitudinally extending walls. One wall includes a generally aft-facing step having a first section and an interconnected second section, a forward wall portion attached to the first section, and an aft wall portion attached to the second section. The second section includes a fuel injector discharge orifice having a fuel discharge axis which is aligned generally perpendicular to the second section and which projects both generally towards the other wall and longitudinally aft. The combustor has a cylindrical embodiment which includes a cylindrical wall having a step and fuel injector discharge orifice similar those of the "2-D" and annular combustor embodiments.

Abstract: An apparatus for loading a compressor includes a microprocessor based electronic controller, a pneumatically driven, spring loaded open first valve, and a normally open, electrically driven second valve flow connected in series with the first valve. The first valve and the second valve are fluidly disposed intermediate a receiver tank and the compressor. The second valve is disposed in signal receiving relation to the controller. An orifice and muffler combination is flow connected intermediate the first valve and the second valve. The orifice has a predetermined inside diameter dimension suitably sized to establish a pressure signal to close the first valve to thereby load the compressor.

Abstract: A fluid-flow regulating device is comprised of (a) a plurality of driving mechanisms each of which has a chamber, a diaphragm disposed at an opening of the chamber, a light-heat conversion substance accommodated in the chamber, and an operating fluid stored in the chamber, (b) a fluid-flow passage along which the plurality of driving mechanisms are arranged in such a manner that each of the diaphragm is opposed to the fluid-flow passage, (c) a plurality of optical fibers corresponding to the plurality of the chambers, and (d) a controller having a plurality of optical sources corresponding to the plurality of optical fibers which are set to be turned on and turned off in order to move an amount of fluid through the fluid-flow passage in any one of the normal and the reverse directions.

Abstract: An internal combustion and internally cooled steam engine and powering method to be used to more efficiently and effectively power steam turbines and like drive sources. The steam engine includes an insulated pressure chamber having a boiler concentrically located therein, and a combustion chamber concentrically positioned within the boiler, into which fuel and air pass, through inlet conduits, and are ignited to form hot gasses, thereby heating water within the boiler such that steam emerges from the boiler through a plurality of apertures in the boiler and mixes with the hot gasses. The gasses emerge into the pressure chamber through at least one flue gas line connected to the combustion chamber, and extending into the pressure chamber.

Abstract: A gas turbine nozzle includes a plurality of nozzle segments having a pair of nozzle vanes supported by inner and outer shroud segments. Each inner shroud segment includes a circumferential retention slot and a radial retention slot in generally circumferential alignment and an interlocking tab and slot arrangement at the respective ends to provide engagement between adjacent flange segments. A 360 degree retention ring includes a plurality of circumferential retention tabs and radial retention tabs to engage respective ones of the plurality of flange segments to secure the nozzle segments in a circumferential ring about the outlet of a gas turbine combustor.

Abstract: A composite structure for rocket motors includes a longitudinal element of the composite structure, which is an assembly of segments of clamshell or barrel stave form. The element is held in place by a circumferential element, which is a composite overwrap of reinforcing fibers in a resin matrix. The matrix may be thermoplastic or thermosetting. The reinforcing fiber being high strength polyolefin thereby providing the rocket motor with insensitive munitions capability.

Abstract: A liquid fuel power plant (100) including an open-ended combustion chamber (102) and a first mechanism (112) for delivering a combustible liquid fuel to the open-ended combustion chamber (102). A second mechanism (136) is included for igniting the fuel in the open-ended combustion chamber (102). A coiled tube-shaped mechanism (140) located external to the combustion chamber (102) is provided for extending the length of the combustion chamber (102) to decompose the ignited fuel and to provide an exhaust gas comprised of fundamental elements. Finally, a third mechanism (160) is provided for using the exhaust gas to perform useful work. The air input line (120) delivers compressed air, which can be preheated, in an air passageway (130) and thereafter is mixed with the combustible fuel in the open-ended combustion chamber (102).