Abstract: The claimed engine is a gas turbine power plant having a conventional gas turbine system, a medium power plant system and a low power plant closed loop system. The turbines used in the medium and low power plant systems are designed to allow a heat exchange relationship between the aforementioned turbines and another part of the system. A heater, using an external energy source, provides heat energy to drive the conventional gas turbine system. The hot exhaust fluid of the gas turbine flows through a conduit where it gives up heat energy, through a heat exchange relationship, to the turbines of the medium power plant system, therefore providing the heat energy to drive those turbines. The exhaust fluid of the gas turbine having given up most of its heat energy, is released into the environment.

Abstract: A construction for the delivery of propellant constituents to the main combustion chamber of a hypergolic liquid bipropellant rocket engine having a staged combustion cycle incorporating at least one precombustor comprises: a mixer for mixing together prior to delivery to the main combustion chamber a first propellant constituent comprising oxidant together with exhaust gas from the precombustor injector means for injecting the mixture of the oxidant and exhaust gas provided by the mixer into the main combustion chamber in such a manner that the injected mixture forms a recirculation zone inside the main combustion chamber, an inlet into the main combustion chamber for a second propellant constituent comprising fuel, and a delivery channel to the said inlet, the said inlet and delivery channel being disposed laterally of the injector means relative to the main direction of flow through the injector means in such a position that fuel delivered into the main combustion chamber thereby is delivered into the said

Abstract: The present invention relates to a thrust reverser system for a turbofan-type turbojet engine having thrust reverser doors with movable deflectors. The deflectors are movably attached to an upstream edge of the thrust reversing doors and are movable between retracted and extended positions. When the thrust reversing door is closed and the turbojet engine operates in its normal thrust mode, the deflectors are retracted thereby enabling the difference between the inner surface of the thrust reversing door and the theoretical aerodynamic flow line to be reduced or eliminated. When the thrust reversing door is in the thrust reversing position, the deflector is extended so as to protrude beyond the inner surface of the door so as to direct the air flow in a more forward direction to increase the thrust reversing capabilities of the system. The deflectors are mounted on the thrust reversing door such that they are automatically extended when the thrust reversing door moves to the thrust reversing position.

Abstract: Method and apparatus for controlling the output emissions of a gas turbine engine provides an emissions combustor wherein the gas is burned locally and then thoroughly mixed with cooler unburned portions while propagating the resulting a very hot flame front is propagated over the whole gas stream flow. The emissions combustor serves to reduce the carbon monoxide content of the output. NOX can be eliminated by steam injection into the engine main combustor in combination with the emissions combustor. Combustion efficiency, which is reduced through the steam injection in the main combustor is recovered through the use of the emissions combustor. The emissions combustor can be placed at numerous locations, either as part of a main combustor staging, downstream of a high pressure turbine, or in a supplementary burner after a power turbine.

Abstract: A high speed electric motor drives an impeller to centrifugally induce air flow to an engine exhaust system. The motor is sealed within a noise attenuating cover, and the impeller induces a portion of the air flow to recirculate through the sealed motor chamber to cool the motor. A noise attenuating duct is mounted on the pump inlet. The duct includes an elongated neck of rectangular cross-section extending at an angle from a tubular body, the remote end of said neck being tapered, each side of the neck having a series of parallel inlet louvers, and the body having an internal foam liner.

Abstract: A technique for producing thrust by generating a hybrid plume plasma exhaust is disclosed. A plasma flow is generated and introduced into a nozzle which features one or more inlets positioned to direct a flow of neutral gas about the interior of the nozzle. When such a neutral gas flow is combined with the plasma flow within the nozzle, a hybrid plume is constructed including a flow of hot plasma along the center of the nozzle surrounded by a generally annular flow of neutral gas, with an annular transition region between the pure plasma and the neutral gas. The temperature of the outer gas layer is below that of the pure plasma and generally separates the pure plasma from the interior surfaces of the nozzle. The neutral gas flow both insulates the nozzle walls from the high temperatures of the plasma flow and adds to the mass flow rate of the hybrid exhaust. The rate of flow of neutral gas into the interior of the nozzle may be selectively adjusted to control the thrust and specific impulse of the device.

Abstract: An inlet air demoisturizing system utilizes a plurality of screens between the inlet of a cryogenic engine and a heat exchanger therefor. In a first embodiment, a curtain of liquid air flows on the forward side of the screen to pre-cool the gaseous intake air below the freezing point of water. In a second embodiment, a mist of liquid air is used to pre-cool the air prior to arrival at the screen. The screen traps ice crystals precipitated from the air. In each embodiment, a second sprayer washes the screen with a curtain of liquid water to remove the ice crystals therefrom. Collector troughs collect the liquid air and suspended ice crystals for removal from the engine inlet.

Abstract: The cost of fuel injection nozzles 50 and their tendency to clog in a gas turbine having an annular combustor 26 can be reduced by alternating the fuel injection nozzles 50 with bender jets 56 configured to introduce a combustion supporting gas into an annular combustion zone 40 at locations between the fuel injectors 50 to achieve uniform turbine inlet temperature distribution while requiring fewer of the nozzles 50 and allowing those nozzles 50 that are utilized to have larger fluid flow paths that are less prone to clogging.

Abstract: An oil system for a gas turbine engine including a supply circuit having a main pump supplied from a reservoir tank and discharging in bearing sumps of the engine, a scavenge circuit having a plurality of scavenge pumps supplied from the sumps of the engine and discharging back to the reservoir tank, and a distributing valve in the supply and the scavenge circuits operative when main pump discharge pressure is below a threshold pressure characteristic of main pump interruption to connect the scavenge pump discharge to the supply circuit so that residence oil in the supply circuit is recirculated to maintain bearing lubrication after main pump interruption.

Abstract: An air conditioning system includes an evaporator and a variable capacity compressor. The compressor has a lower pressure zone including a suction chamber connected to the outlet of the evaporator, a higher pressure zone, a bellows displaceable in response to pressure representative of a thermal load on the system, a control valve device responsive to displacement of the bellows for bringing the higher pressure zone into and out of communication with the lower pressure zone to thereby control the difference between pressure from the higher pressure zone and pressure from the lower pressure zone, and a control element responsive to change in the difference between pressure from the higher pressure zone and pressure from the lower pressure zone for varying the delivery quantity of the compressor.

Abstract: A secondary oil system for a flight propulsion gas turbine engine becomes operative only when engine fuel pressure is normal and engine primary oil pressure is abnormally low. The secondary oil system includes an air circuit having a mist circuit portion, a pilot operated air valve which normally blocks the air circuit, and a pilot valve responsive to fuel pressure and primary oil pressure to actuate the air valve. When the air circuit is unblocked, air flow in the mist circuit portion aspirates oil from a reservoir tank which oil is dispersed as a mist directed at a bearing in the sump.

Abstract: The present invention comprises a gas turbine engine augmentor including a new and improved fuel spraybar therein. The spraybar includes a base having a manifold for receiving fuel, and a plurality of fuel tubes extending from the base and in flow communication with the manifold. The invention further includes means for cooling the fuel tubes for allowing independent thermal movement between the cooling means and the fuel tubes. In one embodiment of the invention, the cooling means comprises an elongate shield disposed upstream of the fuel tubes to block direct impingement of combustion gases against the fuel tubes while channeling a cooling fluid such as air over the fuel tubes.In accordance with another embodiment, the invention includes means for securing the shield to the fuel tubes for allowing unrestrained longitudinal thermal movement while restraining lateral movement therebetween beyond a predetermined amount.

Abstract: An ejector adapter and guide rail assembly for coupling an opening of a discharge outlet of a submergible pump with an inlet opening of a discharge pipe through which waste water is discharged from a sump. The assembly includes a quick disconnect coupling device having a bifurcated guide member which engages a vertical guide rail to permit removal and reinstallation of the submergible pump without removal of a bracket that fixedly mounts the upper end of the guide rail to the sump.

Abstract: A compact instant steam generator is provided for on site use where various qualities of steam may be required. A water jacket cooled combustion chamber having a burner at one end and a water spray nozzle at the other end is used. In operation, a water spray is directed countercurrently to the burner exhaust gases whereby instant vaporization of the water occurs due to the extreme turbulence and thorough mixing of the opposing streams. The water spray is located remote from the burner flame so that flame quenching by the water does not occur. The device of the invention is capable of generating steam while coproducing a very low level of carbon monoxide.

Abstract: A combined cycle waste-to-energy plant is utilized to thermally convert municipal and industrial solid wastes into essentially complete products of combustion and use the combustion heat to produce steam and/or electrical power. The plant includes a building enclosure having a waste receiving area, a waste fuel separation and processing area, an incinerator area and a heat recovery and power generation area. Processed waste fuel is delivered to a series of incinerators by an automated conveyor and hopper system, and the waste fuel is burned in the incinerators by hot exhaust gas delivered thereto from one or more combustion turbines located outside the building and drivingly connected to electrical generators. Inlet air to the turbines is drawn from with the building to maintain its interior at a negative pressure, thereby preventing waste odors and pathogens from escaping from the building.

Abstract: An improved system provides cooling air to the turbine blades of a gas turbine engine. The improved system includes the combination of an inducer to receive pressurized cooling air from the compressor and then to direct this cooling air in a substantially tangential direction to a radial flow impeller which includes an air seal. Cooling air is directed to the turbine blades which are mounted on the rim of the rotating first turbine disk. In a preferred embodiment of the invention, a second portion of the cooling air from the inducer is conveyed through a deswirler to introduce the cooling air into a circumferential channel surrounding the rotor shaft. The cooling air is then directed to a second inducer means which is mounted on the higher pressure turbine disk. The cooling air is then directed to a second annular impeller mounted on the lower pressure turbine disk to convey this portion of cooling air to the lower pressure turbine rotor blades.

Abstract: The invention relates to turbopropeller gas turbine engines of the type which have a propeller positioned upstream of the gas generator. Intake openings supply air through intake ducts and annular intake duct to the gas generator. A separating duct removes foreign bodies from the air flowing through an outlet. The separating duct has a plurality of ejector nozzles equi-spaced in the wall of the duct. The ejector nozzles induce a flow through the separating duct to draw the foreign bodies through the separating duct. The separating duct allows the passage of large foreign bodies therethrough without damage to the ejector nozzles. The ejector nozzles are supplied with air from a compressor of the gas generator, and this allows control of the flow through the separating duct by a valve.

Abstract: The present invention is related to a liquid fuel rocket engine of the type that a liquid fuel is boosted in pressure by way of a booster means.

Abstract: An anti-rupture ring is slit axially at least at one location and is provided thereat with clamping devices which permit a rapid tightening and loosening of the anti-rupture ring. In one embodiment, the clamping of the anti-rupture ring can be varied hydraulically so as to minimize clearance losses in operation. The invention can be used in all types of turbo engines endangered by breakage of rotor blades, particularly in aircraft gas turbine construction, and it permits simple, damage-free mounting and a well-defined clamping of the anti-rupture ring.

Abstract: A centrifugal compressor for use in turbo-refrigerators, for example, has a motor casing frame section in which a drive motor is accomodated and a gear casing frame section in which a multiplying gear mechanism is accomodated. The multiplying gear mechanism is connected at its input side with the drive motor and at its output side with an impeller. The mechanism has a first shaft including a rotor shaft of the drive motor and a gear shaft carrying a multiplying gear and separably connected directly with the rotor shaft, a second shaft mounting the impeller and having a pinion meshing with the speed multiplying gear, and bearings mounted on bearing casing frame sections for supporting the first and second shafts at their opposed ends, respectively. The motor casing frame section, gear casing frame section and bearing casing frame section are integrally formed as a unitary body.