Abstract: A predetermined time delay of speed setpoint ramping of a gas turbine is imposed at ignition in its primary control system or local maintenance controller in order to compensate for the fixed energy input at ignition which might otherwise greatly increase the possibility of flameout. The imposed time delay results in the increase of an initial turbine speed tracking mode time period for the duration of the time delay.During the time delay period, fuel flow is maintained at a fixed fuel valve setting and pressure. At the termination of the time delay period, ramping of a speed setpoint at a selected rate is begun and the turbine speed is thereby increased towards synchronization speed whereat synchronization is effected.

Abstract: A torque control system designed to economize on consumed fuel includes a source of motive power, a load and a transmission coupling the motive power to the load. A torque measuring device is attached to the output of the transmission and senses a torque applied to the load. The output of the torque sensor is compared with electrical analogs of optimized torque situations. The comparison results in the development of a control voltage which is applied to the source of motive power and the transmission to effect optimization of torque control.

Abstract: A control circuit for controlling output speed of a gas turbine engine through comparison between a signal representative of an actually detected output speed of the engine and a signal representative of a desired engine output speed, wherein the rate of increase of the latter signal is limited in accordance with a predetermined schedule depending upon a detected temperature of the engine and a predetermined engine temperature which varies with a preselected operating condition such as the detected output speed of the engine. The control circuit is characterized in that the same is at all times maintained as a closed-loop system although switching means is provided in the circuit.

Abstract: A valve arrangement for controlling the flow of fluid from an inlet passage to the cylinder of a reciprocating piston compressor wherein the valve is actuated to the open position by the pressure of the fluid compressed in the cylinder by planned early closing of the discharge valve as the piston approaches its top dead center position; actuation of the inlet valve to the closed position being effected at the desired time by operation of a cam and valve closing spring.

Abstract: A gas turbine engine which comprises a rotary air compressor and a gas turbine, each with a rotor mounted on opposite ends of a rotor shaft, which is journalled in a housing positioned between the compressor and the turbine. The housing includes reduction gears. A combustion chamber is connected between the outlet air duct of the compressor and the hot gas inlet duct of the turbine. The power output is controlled by varying the air inlet to the compressor by means of an axially moving throttle control which limits the air passage into the compressor, either alone or in conjunction with variable angle compressor inlet pre-whirl vanes. It is also controlled by a shroud which surrounds the nozzle blades of the turbine. The shroud can be moved axially to limit the cross-section of flow of hot gas to the turbine blades.

Abstract: A fuel control system has a positive displacement gear pump for supplying a metered fuel flow to a gas turbine engine. A variable speed drive mechanism, as constituted by a hysteresis type of electro-magnetic clutch driven by the engine, is operatively connected to the pump for varying the speed of the pump in accordance with a commanded pump speed signal. A scheduling device, which senses various engine parameters, generates a signal indicative of a scheduled fuel flow. The fuel flow signal is, in turn, applied to a function generator which supplies the commanded pump speed signal in accordance with a predetermined relationship between pump speed and fuel flow for the engine sought to be controlled. The relationship between pump speed and fuel flow may be calculated for a wide range of flight conditions since the pressure rise or head across the pump is basically a function of fuel flow. This arrangement obviates the use of a head regulator for highly accurate fuel metering.

Abstract: Method and apparatus for metering fuel flow to a gas turbine engine includes a first bifurcated movable metering element straddling a pair of opposed metering openings and shiftable to adjust the area of the openings to vary fuel flow from a pump to the combustion chamber of the engine. A second bifurcated movable metering element straddles a second pair of opposed metering openings to adjust fuel flow back to the inlet of the pump in bypassing relationship to the combustor. The movement of the second metering element is responsive to the pressure differential across the first metering openings to maintain this pressure differential substantially constant to allow precise fuel metering by movement of the first metering element.

Abstract: The 3-D cam utilized for acceleration scheduling of a fuel control for a turbine type of power plant is also utilized to schedule the position of the stator vanes of the power plant and to provide speed and temperature schedules for idle and maximum speed. A single follower responding to the same profile on the cam controls both stator vane position and idle speed. The stator vane and idle speed contour on the 3-D cam controls idle speed through a single linkage and readjusts the W.sub.f /P.sub.3 ratio lever to adjust fuel flow.

Abstract: A method and apparatus for preventing overspeed in a gas turbine in response to the rapid loss of applied load is disclosed. The method involves diverting gas from the inlet of the turbine, bypassing the same around the turbine and thereafter injecting the diverted gas at the turbine exit in a direction toward or opposing the flow of gas through the turbine. The injected gas is mixed with the gas exiting the turbine to thereby minimize the thermal shock upon equipment downstream of the turbine exit.

Abstract: Control apparatus for programmed control of a plurality of gas turbine engine compressor air bleed valves in response to a plurality of control input signals representing engine operating conditions including variable conditions related to engine power output. The control inputs are sensed and/or computed and scheduled to provide accurate and reliable control over a plurality of compressor air bleed valves by means including a hydraulic programmer with a three dimensional compressor rise scheduling cam and adjustable hydraulic timers.

Abstract: A housing defining a flow passage therethrough including inlet and outlet ends as well as a central portion intermediate the inlet and outlet ends is provided. Positive displacement gas pump structure in the form of a roots-type compressor is operatively associated with the inlet end of the passage for pumping air under pressure therethrough and into the central portion between the inlet and outlet ends which defines a combustion chamber. The roots-type compressor or pump also defines an obstruction to the reverse flow of gas under pressure from the combustion chamber outwardly of the inlet end of the passage. A positive displacement gas motor in the form of a roots-type fluid motor is operatively associated with the outlet end of the passage for developing rotary torque in response to elevated gas pressures within the combustion chamber and the passage of gas under elevated pressures from the combustion chamber, through the roots-type motor and out the outlet of the passage.

Abstract: A multi-apex rotor for an internal combustion rotary engine is provided on its radially outwardly facing flanks with hot plates which each form a portion of a combustion chamber and have a shape and coefficient of expansion in relation to the rotor body so that they are normally separated within their periphery from the adjacent flank by a sealed air space so as to be insulated therefrom and thereby retain a substantial portion of the heat of combustion and on hot plate temperature rise with engine speed and load to a level below that which would cause pre-ignition expanding radially inwardly to establish a substantial heat conducting relationship with the flank to thereby limit hot plate temperature to below the pre-ignition temperature.

Abstract: A rotary combustion engine having a planetary rotor and a side intake port is provided with an internal exhaust gas recirculation system that is operable to connect the trailing region of the working chambers and the space below the trailing apex seal to the annular space between the side seals and oil seals on one rotor side only when the chambers near the end of the exhaust phase whereby the differential between the pressure of the exhaust gases and the vacuum of the inlet mixture causes the exhaust gases rich in unburned hydrocarbon that are in the trailing regions of the chamber during the exhaust phase to flow through the annular space to the intake port and thereafter be recirculated through the compression and expansion phase.

Abstract: A rotary internal combustion engine including a single shaft supporting two rotors recessed to form working chambers in adjacent sections of a housing with a cylindrical interior, one rotor performing the intake and compression functions and the other, the combustion and exhaust functions.

Abstract: Control apparatus for programmed control of a plurality of gas turbine engine compressor air bleed valves in response to a plurality of control input signals representing engine operating conditions including variable conditions related to engine power output. The control inputs are sensed and/or computed and scheduled to provide accurate and reliable control over a plurality of compressor air bleed valves by means including a hydraulic programmer with a three dimensional compressor rise scheduling cam and adjustable hydraulic timers.

Abstract: A rotary engine wherein a side port is formed in one side housing, and a main peripheral port, communicating with the side port, and a bypass peripheral port, communicating with a bypass passage formed in another side housing, are formed in a rotor housing, the side port being maintained in communication with the carburetor through a passage formed in the rotor, while the bypass peripheral port communicates with the carburetor by bypassing the passage in the rotor. Respective valves are mounted in the main peripheral port and the bypass peripheral port, and the two valves are closed or throttled at low engine speeds. The bypass peripheral port opens at higher engine speeds than the main peripheral port.

Abstract: A fuel control system for a gas turbine engine has a pump, a variable metering device and a servo-operated throttle valve connected in series. A spill valve at the pump outlet is responsive to a servo pressure which is dependent on engine speed and on the total pressure drop across the metering device and the throttle valve. A selector valve is effective in one of its positions to shut the throttle valve and simultaneously to modify the servo pressure to the spill valve so as to increase spill flow to a maximum.

Abstract: In a plant of a composite cycle which includes a steam turbine having a high pressure portion and a low pressure portion, a gas turbine, and a waste heat boiler having heat exchangers producing high pressure steam and low pressure steam to be fed to the steam turbine, by the use of exhaust gas from the gas turbine as a heat source; there are provided steam valves on steam passages through which steam is fed from the heat exchangers of waste heat boiler to the steam turbine; a detecting device for detecting the condition of steam flowing into the steam valve; and another detecting device for detecting the r.p.m. of the steam turbine; whereby the opening and closing of the steam valves are controlled by means of a selecting device which preferentially selects either of signals from the aforesaid detecting devices to adjust the quantity of steam to be fed to the steam turbine for controlling the steam turbine.

Abstract: An orbital rotary piston-type internal combustion engine in which a series of pistons are mounted for co-operation on a pair of rotors which are carried on a drive shaft and travel in an annular combustion chamber, with associated pre-combustion chambers which are charged with rich fuel-air mixture while the annular combustion chamber is charged with a relatively lean fuel-air mixture, the mixture in the pre-combustion chambers being ignited by primary spark plugs and the expanding gas being forced through ports into the annular combustion chamber where secondary spark plugs adjacent the ports assist in more complete combustion and help force the pistons past exhaust ports, and with a variable ratio, overriding clutch-bearing for transmitting power from the rotors to the drive shaft, a solid state ignition system, a pressurized fuel injection system, a drive shaft mounted timing system and an electromagnetic controlled starting device, the disengagement of the latter being effected by means of an engine veloc

Abstract: The casing of a rotary engine has a combustion chamber in which a rotor having a precisely circular section is supported by a center shaft. Part of the peripheral wall of the combustion chamber has the same size as the circumference of the rotor and the rest of the wall is larger than the circumference of the rotor. Accordingly, a requisite length of the circumferential surface of the rotor is kept in sliding contact with the peripheral wall all the time, while the rest of the circumferential surface of the rotor is always out of sliding contact with the peripheral wall to provide a space in the combustion chamber. The circumferential surface of the rotor is partially recessed to provide a cavity for accommodating a fuel-air mixture.