Abstract: Dual fuel/air injectors are provided, including a conventional central diffusion flame fuel nozzle 12. A fuel injector 14 for pre-mixing fuel and air for low emissions combustion and coaxial to the central nozzle includes a plenum 30 about the central injector having an air inlet 32, an annular pre-mix chamber 34, a fuel injection region 36 between the pre-mix chamber and air inlet 32 and an outlet 40 defined in part by swirler vanes 38. Radially projecting fuel spokes 46 extend into the plenum 30 and are supplied fuel from a manifold 44. Apertures 52 in the spokes supply fuel in a circumferential direction to the incoming air. The spokes in the plenum define throat areas T which, in the aggregate, define a minimum cross-sectional area of the plenum 30. Differential air flows through the throats provide inverse differential fuel distribution in the throats whereby a uniform fuel/air mixture strength distribution occurs at the throats.

Abstract: A turbine frame includes first and second coaxially disposed rings having a plurality of circumferentially spaced apart struts extending therebetween. A plurality of clevises join respective first ends of the struts to the first ring for removably joining the struts thereto. Each of the clevises includes a base removably fixedly joined to the first ring, and a pair of legs extending away from the base and spaced apart to define a U-shaped clevis slot receiving the strut first end. The first strut end is removably fixedly joined to the clevis legs by a pair of expansion bolts. The clevis base includes a central aperture aligned with a first port in the first ring for providing access therethrough. And, the strut first end abuts the first ring for carrying compressive loads therebetween and providing a seal therewith.

Abstract: A process is disclosed, for pumping a multi-phase gas-liquid mixture by using a pump as the thrusting machine, and at least two pumping vessels alternatively performing functions of intake and functions of compression/delivery.

Abstract: A satellite power plant with a gas turbine, electric current generator and liquid metal circulation heat recovery unit is constructed so that, when a future planned major power plant is erected, the excess fuel gas from its coal gasifier can supply its combustion chamber with the heat recovery unit fuel effective gas turbine unit and the current generator can cover the peak power demand. A device for recovery of low-temperature heat for local heating purposes has its optimum low-temperature thermal energy extraction when the heat recovery unit is shut down.

Abstract: A seal centering and restraining device for positioning the seals between the divergent flaps of a vectoring convergent/divergent nozzle. The device includes a restraint bar that spans between two adjacent divergent flaps and is pivotally attached to the air side of a seal and slidably secured by sliders to tracks on the adjacent divergent flaps, thereby sandwiching the adjacent divergent flaps between the seal and sliders. A positioning linkage connecting the two adjacent divergent flaps centers the seal at all nozzle operating conditions.

Abstract: A gas and steam turbine plant includes a coal gasification plant, a gas turbine connected downstream of the coal gasification plant, a steam turbine having a water-steam loop and a steam generator connected downstream of the gas turbine. The steam generator includes a preheater connected to the water-steam loop, a heater of a high-pressure stage connected downstream of the preheater, and a heater of a low-pressure stage connected upstream of the preheater. An outflow line leads into the coal gasification plant and is connected to the water-steam loop downstream of the preheater, as seen in water flow direction. A heat exchanger has a primary side integrated with the water-steam loop between the low-pressure stage and the high-pressure stage and a secondary side connected parallel to the outflow line.

Abstract: A system and method to maximize fuel efficiency for a plurality of simultaneously operating engines is disclosed. The system includes means to determine the fuel consumption of the engine, measure the thrust of each engine and means to substantially equalize the ratio of the fuel consumption to the thrust between each of the engines. A pressure transducer is included to provide thrust data supply to each of the engines to a microprocessor, and a microprocessor is run to substantially equalize the ratio of the fuel consumption to the thrust to provide an increased fuel efficient system.

Abstract: A fuel injection pump for internal combustion engines, having a pump piston that is guided axially and rotationally movably in a cylinder bore of a cylinder liner and that with a face end defines a pump work chamber. The fuel injection pump pumps a quantity of fuel that is divided into a preinjection quantity and a main injection quantity. On a jacket face, this pump piston has known oblique grooves for the high-pressure pumping diversion process, and also a recess, which cooperates with an annular groove in the cylinder bore and with a control opening which discharges into a low-pressure chamber, and on its end face the piston has a cutout formed by two different, deep shoulders; the cutout is recessed within the annular groove continuously and cooperates with a first control opening that discharges into the low-pressure chamber.

Abstract: A power plant having a fluidized bed steam boiler for supplying steam for powering a turbine generator comprises low pressure and high pressure feed water heaters, and combustion air heater is provided with a gas turbine for burning sulfur containing fuels, with heat recovery economizers for reducing the exhaust temperature of the gas turbine and directing the exhaust gas from the gas turbine into the fluidized bed for reducing the emissions therein.

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: This gas turbine arrangement has an at least two-stage gas turbine (1) with a main combustion chamber (10) and a compressor (5). An energy exchanger (8) which interacts with the separate combustion chamber (14) is installed upstream of the gas turbine (1). The efficiency of the gas turbine arrangement is to be increased by simple means. In order to achieve this, the separate combustion chamber (14) is designed as an afterburner chamber for a part of the gases generated in the main combustion chamber (10). In addition, means for the additional injection of a liquid or vapor medium are provided in the region of the combustion chamber (14). The volume flow in the energy exchanger (8) and hence the efficiency of the gas turbine arrangement are increased by this injection.

Abstract: This gas turbine arrangement has a gas turbine which can be divided into a high-pressure part and a basic part and has a compressor (1) and at least one energy exchanger (7). In addition, it has a combustion-chamber arrangement and a separate combustion chamber (18) connected upstream of the energy exchanger (7). The intention is to provide a gas turbine arrangement in which an increased efficiency is achieved by simple means and which can be regulated more simply. This is achieved by providing at least two combustion chambers (9, 10) for the combustion-chamber arrangement. The first (9) of the combustion chambers cooperates with the high-pressure part of the gas turbine arrangement. The second (10) of the combustion chambers cooperates, via the interposed energy exchanger (7) having the upstream combustion chamber (18), with the basic part.

Abstract: A dual inner central drive shaft in a gas turbine engine includes rearward and forward shaft portions which overlap and interengage with one another. The rearward shaft portion includes an elongated cylindrical inner middle portion and a rear conical end portion, whereas the forward shaft portion includes an elongated cylindrical outer middle portion and a front conical end portion. The respective opposite ends of the inner and outer middle portions of the rearward and forward shaft portions have intermeshing rear and front sets of radially projecting and circumferentially spaced splines which extend parallel to the shaft axis so as to rigidly secure the outer and inner middle portions of the rearward and forward shaft portions together for concurrent rotary motion of the rearward and forward shaft portions in both clockwise and counterclockwise directions.

Abstract: A variable displacement radial ball pump (11) is disclosed of the type in which the balls (59) are restrained by a cam ring (25), which is pivotable about a cam pivot pin (27) to vary the displacement of the pump. In accordance with the invention, in order to return the pump to absolute zero displacement, the pump is provided with a detent mechanism (65;83). The cam ring 25 has a neutral region (73) and a ramp surface (77), and a detent member (69;89) is biased into engagement with the neutral region when the cam ring is in neutral (FIGS. 2 and 3). When the cam ring is displaced from neutral, the detent member engages the ramp surface, against the bias force of a spring (71;91), which exerts a force tending to return the cam ring to neutral in the absence of an input to the control assembly (33).

Abstract: A drive system for rotating a disk includes a housing having a planar element with a working surface which includes a spindle which facilitates rotational movement of the disk relative to the drive assembly. A plurality of orifices extend through planar element at an acute angle relative to the working surface and are arranged in a circular array. A conduit assembly delivers fluid to the housing. The fluid exits through the orifices outlets to provide a motive force for rotating the disk around the spindle, while also providing a pressure differential to support the medium.

Abstract: A fuel injector system for a combustor of a gas turbine engine includes first and second fuel injectors rendered operative to discharge fuel to the combustor during a high power regime of engine operation and rendered non-operative during a lower power regime of engine operation. The first and second fuel injectors include respective first and second fuel discharge passages in fuel flow communication to one another and to the combustor via associated fuel discharge lips to sustain a flame region. The first and second fuel injectors are operatively associated with respective first and second air discharge means having air discharge lips for discharging air to the combustor for sustaining the flame region therein. When the fuel injectors are rendered non-operative, different pneumatic pressures are established at the fuel discharge lips to purge fuel from the fuel injectors to the combustor.

Abstract: In a disk player/recorder apparatus, a radial access mechanism is disclosed in which a first guide rod is positioned on a mounting plate accurately with respect to the information storage medium. A head assembly engages the first guide rod through bushings which provide stringent tolerance requirements. The position of the head assembly is accurately controlled by the position of the first guide rod and the tolerances on the bushings. A second guide rod coupled to the mounting plate and a single bushing also supports and guides the head assembly, however, the tolerances on the components associated with the second guide rod are less stringent. Coupled to each of the guide rods is a bracket with a permanent magnet coupled thereto. The permanent magnets interact with the coils of linear motors coupled to the head assembly. The linear motors are arranged to minimize torque on the head assembly. The brackets and the guide rods form magnetic circuits for the associated permanent magnets and linear motors.

Abstract: A control system for hydraulically controlling variable engine structures is disclosed in which the control system utilizes hydraulic fluid identical to that used by the aircraft hydraulic control circuit. A high pressure hydraulic pump, driven by the aircraft engine, may be interconnected with the aircraft hydraulic control circuit, or may be associated with a separate fluid reservoir, to supply pressurized hydraulic fluid to the actuators for controlling the variable engine structures. The engine control circuit also includes a hydraulic pressure modulator to modulate the pressure of the fluid supplied to the actuator and a selector connected between the high pressure pump and, the modulator and the aircraft control circuit to selectively supply the high pressure hydraulic fluid from the pump to either the engine control circuit, or to the aircraft control circuit.

Abstract: The invention relates to secondary power system apparatus and method for use aboard aircraft in place of conventional auxiliary power units (APU's) and emergency power units (EPU's). The invention integrated power unit (IPU) performs the function of both an APU and an EPU, while avoiding the use of hazardous monofuels. The IPU includes a turbine engine operable on pressurized ambient air, or on pressurized stored air, along with jet engine fuel. The structure of a combustion chamber for the engine which is able to use pressurized air from two separate sources; of a control able to selectively operate the engine as an EPU, as an APU, and to effect operating transition from EPU to APU; and of a complete secondary power system with the IPU are all disclosed.

Abstract: A cooling arrangement for the cooling air of hypersonic jet engines comprises a heat exchanger in which the temperature of the cooling air is reduced by means of the fuel to be burnt in the engine. In order to keep the operating temperatures of the heat exchanger within controllable limits, a partial flow of the cooling air is branched off downstream of the heat exchanger and is admixed to the cooling air upstream of the heat exchanger for reducing the temperature.