Abstract: For a fuel control for a turbine type of power plant a throttle valve servo piston combination including a servo control valve operated off of a multiplication lever system wherein said throttle valve servo piston combination is rotated resulting in a smaller unit and achieving a reduction in its size and that of the control valve and lever system. A gear secured to the rotatably supported mechanism is located in a judiciously selected position within the drain portion of the control and the maximum fuel flow limit changes the feedback system from a force balance one to a position one during maximum limiting.

Abstract: Apparatus and method for governing speed and acceleration of a gas turbine system which includes a trimming unit responsive to the speed of a common shaft connecting a combustion air compressor and a gas turbine, which trimming unit varies the fuel flow to the combustion chamber. The setting of the fuel flow to a new speed is by way of a pressure reducer and actuator piston movable in response to changes in the compressor outlet pressure. A blocking mechanism is provided for blocking out the trimming means during acceleration and deceleration conditions. The actuator piston movable with the compressor end pressure is attached at one end of a pivotal bar which has the other end pivotally connected to a control valve sleeve on a fuel supply valve, while the trimming unit operates to control the position of a pivot intermediate the ends of the control bar in response to a speed governor which acts on a control valve piston slidable within the control sleeve.

Abstract: A control system for a gas-coupled gas turbine engine particularly directed to control of the setting angle of the power turbine nozzle of the engine and to correlation of the power turbine nozzle setting with fuel supply and with operating parameters of the engine. The control provides for operation of the engine from closed to full open throttle, with closed throttle calling for idle speed of the engine. The initial stage of opening the throttle develops an increasing nozzle reference temperature signal which is matched with a turbine temperature signal to control a servo which varies the setting, and therefore area, of the turbine nozzle. After the initial stage of throttle opening, the reference temperature signal increases with engine speed, which increases in response to an increasing throttle signal. The actual level of the nozzle reference temperature is also a function of engine inlet temperature up to a given level of this temperature.

Abstract: A continuous combustion device of the type having a combustion chamber and an outer casing forming with it an annular air delivery passage for distributing a continuous supply of compressed air into the combustion chamber, and a fuel injector at one end of the combustion chamber. The combustion chamber has a pattern of holes connecting the air passage with primary and secondary combustion zones within it. The invention provides adjustable means for controlling the flow of delivery air in the annular passage to proportion the relative air distribution to the primary and secondary zones so as to reduce polluting emissions under varying load conditions. Preferably, the hole pattern is designed to provide a lean primary zone fuel-air ratio at full power conditions and early quenching of the flame in the primary zone. The regulating device may take the form of adjustable baffle means and for proportioning the distribution of the flow of air in the annular passage.

Abstract: This engine or energy converter has a casing comprising coaxial spaced sections each having a cavity bounded by opposed parallel flat inner side surfaces merging with semi-cylindrical top and bottom inner surfaces and a rotor coaxial with said sections, having rotor portions in said sections. Said rotor portions carry outwardly spring pressed opposed aligned radial pistons. The pistons of one rotor portion are disposed at right angles to the pistons of the other rotor portion. In each section there is formed a top chamber on one side of the rotor portion for said sections and a bottom chamber on opposite side of the rotor portion for said section.

Abstract: The engine exhaust flow diverter is formed as a duct, extending from the exhaust section of a gas turbine powerplant, having a closed end which is contoured externally as a nozzle plug. First exit means for the flow from the powerplant extends around the duct just forwardly of the contoured plug and second exit means for the flow extends around the duct midway between the first exit means and the end of the exhaust section of the powerplant. An annular door is axially movable around the duct between an open and closed position to control the flow through the second exit opening and an annular shroud is axially movable around the duct between an open and closed position to control the flow through the second exit means. The annular shroud cooperates with the contoured nozzle plug to form a conventional nozzle. An actuating system is connected to both the annular door and annular shroud to actuate them so that when one is open the other is closed.

Abstract: A combined cycle power plant includes gas and steam turbines, gas turbine afterburners, steam generators, and a digital/analog control system. A megawatt load control system varies a fuel control signal to govern a detected power output according to a reference value, the fuel control signal determining the flow rate of fuel to a gas turbine. An afterburner is connected to heat the exhaust gas from the gas turbine. Both the gas turbine and the afterburner are adapted to use gas and liquid fuels. During gas turbine fuel transfer, the gas and liquid fuel flows are controlled in response to the fuel control signal to compensate power output disturbances that typically result from various nonlinearities of fuel system elements. Afterburner fuel transfer is initiated upon completion of gas turbine transfer.

Abstract: An integrated nozzle is designed to deflect the jet from a waterjet pump in a watercraft before it leaves the nozzle for watercraft steering. The nozzle may be so configured to be steerable in both the horizontal and vertical planes. The integrated nozzle and steering mechanism with thrust reversal mechanism attached thereto allows a full thrust capability without appreciable friction losses inherent in conventional waterjet steering buckets.

Abstract: This invention relates to an electromechanical pumping and fuel metering means interfacing an electronic fuel control adapted for small engines. A centrifugal engine driven pump and electrically driven pump are combined such that the electrically driven pump pressurizes the fuel at low crank up speeds and continuously meters fuel to the burner section and the centrifugal pump pressurizes the fuel at all other times, so as to utilize the centrifugal pump during its high efficiency regime and the electrically driven pump when the centrifugal pump is not at its high efficiency regime.

Abstract: A marine jet drive unit includes a continuously running pump. A reversing gate is positioned partially or wholly within the forward jet to establish a corresponding reverse jet. For neutral drive, the gate is positioned such that the reverse jet just balances the forward jet. A remote shift control unit includes a detent means for locating and holding a rotatable shift lever in neutral. The detent means includes a pair of detent pins carried by a plate which is connected to a support wall by a slot and bolt lost motion connection. The pins are located to opposite sides of the lever and the connection permits angular adjustment about the pivot axis of the lever. The plate supports the detent pin in alignment with a circular outer periphery of the lever plate having oppositely located radial detent grooves. The lever is connected by a push-pull cable to the gate. The precise neutral position of the lever may vary for different drive units.

Abstract: A rotary diesel engine comprising a casing which forms a working space composed of intersecting cylindrical chambers. A rotor is rotatably positioned in at least one of the chambers and a rotary sealing member is positioned at least in one of the other of the chambers, the rotor having a plurality of radially extending lobes and the rotary sealing member having a plurality of radially extending grooves intermeshing with the lobes. A fuel injection assembly is cooperatively carried by the rotary sealing member and is made up of a manifold, a fuel entry port, fuel injection chambers, and pressure building and metering components for each of the fuel injection chambers. An appropriate actuating device, stationarily located external to the rotary sealing member, provides control for the complete fuel injection assembly.

Abstract: A seven-phase rotary internal combustion engine for carrying out intake, compression-ignition, power or primary expansion, transfer, scavenging, afterburning or secondary expansion, and exhaust phases, has an intake port, a second intake or scavenging air intake port, an exhaust port and a transfer passage.

Abstract: A load on the flyweight transmitted through the pilot valve to preload the thrust bearings of a speed sensor serves to prevent the fuel control for a turbine type of power plant from shifting to its emergency schedule from the starting or normal schedule or vice versa at an indeterminant speed. Thus, the preload assures that the transition from one schedule to the other always occurs at a predetermined compressor rotational speed.

Abstract: A mathematical expression is converted and approximations applied to simplify same and thus circuitry which modifies an electrical signal representing a gas temperature into another one.

Abstract: A hydromechanical fuel control for a turboshaft engine includes a gas producer control and an independent power turbine governor in series flow relationship. The basic gas producer control includes an acceleration system, a deceleration system and all speed governor to regulate the fuel flow output of the gas producer control. The acceleration system includes a main metering valve which is positioned by a compressor discharge pressure responsive device and the all speed governor. A speed responsive computer mechanism controls the head across the metering valve. The computer mechanism includes an enrichment valve and a start valve and is connected to the shut-off valve lever for the fuel control in such a manner that the mechanism may be controlled by actuation of this lever. The power turbine governor includes a fuel flow reset governor and a deceleration system to prevent flameouts.

Abstract: The present invention relates to a device comprising an expansion engine, having at least one cylinder and a piston moving therein and a separate apparatus for feeding said expansion engine with combustion gases under pressure.

Abstract: A method of and apparatus for detecting air distortion at the inlet of a turbine engine and adjusting fuel flow to anticipate and prevent compressor stall. A plurality of pressure taps are arranged in a spaced relation around the periphery of the engine inlet. A distortion detector senses the differential pressure between the instantaneous pressure at each pressure tap and the ambient pressure of a reference pressure chamber which communicates with the plurality of pressure taps. At a predetermined pressure differential the distortion detector activates a solenoid-operated fuel bypass valve which reduces fuel flow to the fuel nozzles of the gas turbine engine.

Abstract: In order to automatically adapt the control of an ultrasonic fuel-injection system or other system in which fuel delivery from nozzles is normally controlled by varying the mark/space ratio of energising current supplied to the nozzles, to variation of ambient pressure, a pressure-regulating unit is provided in a line leading from a source of fuel under pressure to the nozzles through a manually adjustable throttle valve and is arranged to maintain the pressure difference between the inlet and outlet of this series arrangement constant for any given ambient pressure P1. An altitude compensator comprising a spring-expanded vacuum capsule and a mechanical transmission is provided for varying this pressure difference in proportion to the ambient absolute pressure P1.

Abstract: A control system for a gas-coupled gas turbine engine particularly directed to control of the setting angle of the power turbine nozzle of the engine and to correlation of the power turbine nozzle setting with fuel supply and with operating parameters of the engine. The control provides for operation of the engine from closed to full open throttle, with closed throttle calling for idle speed of the engine. The initial stage of opening the throttle develops an increasing nozzle reference temperature signal which is matched with a turbine temperature signal to control a servo which varies the setting, and therefore area, of the turbine nozzle. After the initial stage of throttle opening, the reference temperature signal increases with engine speed, which increases in response to an increasing throttle signal. The actual level of the nozzle reference temperature is also a function of engine inlet temperature up to a given level of this temperature.

Abstract: A reciprocating piston device has its pistons and cylinders arranged in a circle, each piston and each cylinder being rotatable about a common shaft to which power is directed or, alternatively, to which power is supplied depending on the use to which the device is put. For example, the device may be a fluid pump, a fluid motor, a diesel engine, a two cycle engine, a four cycle engine, or the like. In a preferred embodiment, two pistons and two cylinders form a part of a first rotor and two other pistons and two other cylinders form a part of a second rotor. Each piston forming a part of one rotor is mounted for reciprocal movement within a cylinder of the other rotor.