Abstract: An internal combustion four cycle engine is provided with a plurality of stationarily mounted cylinders radially arranged in equal spaced apart relationship within the inner circumference of a rotatably mounted drive drum and in parallel relationship with the axis of rotation thereof, a movable track anchorably supported by a pair of oppositely disposed raised lobes fixed to the interior webbed surface of the drum and comprised of two pairs of declining slope track quadrants serving to receive the driving thrust of each piston during its power stroke and to activate each piston during its intake, compression and exhaust strokes, and a cam ring fixed to the inner circumference of the drive drum serving to activate an intake-exhaust slide of each cylinder commensurate with the requirements of its intake, compression, power and exhaust strokes.
Abstract: A two-cycle reciprocal, rotary, internal combustion engine having a plurality of piston cylinders mounted symmetrically around a cylindrical central supply core; each piston cylinder contains two oppositely reciprocating pistons having a common central combustion chamber, the cylinders and pistons are encased in a rotor housing which rotates as a unit around the stationary central core; the central supply core projects from each end of the rotor housing and has stationary elliptical drive plates mounted at an inclination on the ends of the supply core, the inclined drive plates interface cooperatively inclined end faces of the pistons which project through the barrel housing and slide against the drive plates as the barrel housing rotates; rotation results from selective combustion during the reciprocal cycle of the pistons, an angular force being developed by the inclination of the end plates.
Abstract: A gas turbine engine fuel delivery and control system is provided with means to recirculate all fuel in excess of fuel control requirements back to the aircraft fuel tank, thereby increasing the fuel pump heat sink and decreasing the pump temperature rise without the addition of valving other than that normally employed. A fuel/oil heat exchanger and associated circuitry is provided to maintain the hot engine oil in heat exchange relationship with the cool engine fuel. Where anti-icing of the fuel filter is required, means are provided to maintain the fuel temperature entering the filter at or above a minimum level to prevent freezing thereof. In one embodiment, a divider valve is provided to take all excess fuel from either upstream or downstream of the fuel filter and route it back to the tanks, the ratio of upstream to downstream extraction being a function of fuel pump discharge pressure.
February 4, 1976
Date of Patent:
May 3, 1977
The United States of America as represented by the United States National Aeronautics and Space Administration Office of General Counsel-Code GP
Abstract: A fluid flow control valve has two inlets and two outlets. A control element is movable to simultaneously vary flow from the first and second inlet to the first outlet, and from the second inlet to the second outlet. The control element is responsive to the pressure at the first inlet and to a pressure intermediate the second inlet and first outlet. The arrangement is such that the flow from the second inlet to the first outlet is a predetermined multiple of the flow through the first inlet, and that excess fluid entering the second inlet is spilled through the second outlet.
Abstract: A fluid flow control valve includes a body having an inlet and two outlets. A metering control element is slidable in the body to regulate flow through one of the outlets. A combined spill and throttle control element is slidable within the metering element so as simultaneously to control metered flow between the inlet and the one outlet, and spill flow between the inlet and the other outlet. Both of the control elements are responsive to respective servo pressure signals.
Abstract: A gas turbine power plant is provided with an industrial gas turbine which drives a generator coupled to a power system through a breaker. The turbine-generator plant is operated by a hybrid control system having digital function capability during sequenced startup, synchronizing, load buildup and steady state load, and shutdown operations. The control system also contains monitoring and protective subsystems which function through all stages of operation, with redundancy and permissive features which maximize turbine availability.
Abstract: A regulating system for a prime mover, especially a single-spool gas turbine for use in propelling a motor vehicle or aircraft, in which system there is provided a first speed governor for controlling the fuel flow or input power and a second speed governor for controlling the power output. The two speed governors act concurrently in response to the speed of the prime mover and regulate the power input and power output independently of one another.
November 14, 1974
Date of Patent:
April 19, 1977
Motoren- und Turbinen-Union Munchen GmbH
Christian Greune, Bruno Herrmann, Siegfried Steuer
Abstract: A gas turbine engine is described in which a compressor, combustor and turbine are arranged in series flow relationship. Pressurized air enters the combustion chamber with approximately the same swirl as imparted to it by the compressor rotor, through an annular inlet tangentially of and at the outer bounds of the combustion chamber which has a toroidal configuration. This creates a vortex which swirls annularly and in which combustion of fuel is maintained. Mixing action in this vortex is enhanced through the introduction of additional air through chutes formed in the combustion chamber liner. The hot gas stream is discharged from the combustion chamber through an exit also at the outer bounds and tangentially thereof. In one embodiment fuel is introduced by means of nozzles aligned with the discharge ends of the chutes. In another embodiment the combustion chamber inlet is in the form of a venturi passageway and fuel is introduced into the inlet air by ports at the venturi throat.
Abstract: A rotary internal combustion engine that includes a housing that defines an elliptical cavity in which a rotor is disposed. The rotor slidably supports a number of circumferentially spaced, radially disposed blades, with each pair of blades defining a chamber therebetween. The rotor is so rotatably supported in the cavity that the ratio of the intake chamber volume may be adjusted so that there is a minimum residual pressure on exhaust gases and the efficiency of the engine is increased as a result thereof.
Abstract: In a primary or backup control system for operating a gas turbine, a blade path temperature limit signal is generated which acts as a check on a fuel scheduling signal to the turbine which might otherwise cause excursion of the blade path temperature beyond prescribed limits. The means for generating the blade path temperature limit signal is adapted however so that a preliminary error signal is conditioned to behave in one manner in response to a condition of increasing temperature and in another manner to a condition of decreasing temperature.This two-way response is achieved by utilizing a plurality of proportional signal limiters, each one of which is matched to or tuned in accordance with the characteristics of the gas turbine. Further, the response duality is automatic and subject to the particular condition of temperature change which obtains.In addition, means are provided for generating a temperature limit signal which is clamped to a fixed, predetermined percentage of the fuel scheduling signal.
Abstract: A valve actuated in response to a drop in fuel pressure across a fuel supply valve that will drain the fuel from a fuel line but not leak when exposed to high fuel pressures during normal operation. The dump valve is particularly applicable to the draining of fuel from a gas turbine engine fuel nozzle line after shutoff of the engine fuel supply valve.
April 20, 1970
Date of Patent:
April 12, 1977
Caterpillar Tractor Co.
Duane E. Evans, Thomas M. Tabor, David A. Tyler
Abstract: A calculator is interposed between a sequence controller and a fuel regulator in order that the fuel regulator injects an optimum quantity of fuel into a combustion chamber in dependence on the temperature of the engine at start, resulting in a gradual warming-up of the engine under all temperature conditions.
Abstract: In a fuel control system of the type in which an electromagnetic valve responsive to timing pulse voltage is employed to intermittently effect the metering of the fuel, a control voltage generator generates a control voltage corresponding to a predetermined fuel metering characteristic of the engine, and a trigger signal generator triggers a timing pulse generator at a predetermined period to generate timing pulses whose time width is controllable in accordance with the control voltage to actuate an electromagnetic valve.
Abstract: A servo-operated shut-off valve for a gas turbine engine fuel system has a main valve control element and an electrically-operated pilot valve control member for controlling a servo-operating pressure for the main valve. The pilot valve control member and main valve control element are resiliently interconnected so that movement of the main valve control element urges the pilot valve control member in a direction to cause the servo pressure to maintain that movement of the main valve control element.
Abstract: A control system for a gas turbine, which control system comprises a fuel pressurizing pump and two fuel flow restrictors supplied with fuel at different pressures from the pump, said restrictors being in communication with a common fuel pipe line, and there being electrically actuated means, e.g. a rotenoid, for varying the fuel pressure in the common fuel pipe line whereby said varying fuel pressure can be used for controlling the output of the gas turbine.
November 22, 1974
Date of Patent:
March 15, 1977
Plessey Handel und Investments A.G.
Horace George Turner, Robert Spurgeon Wood
Abstract: The invention pertains to a rotary machine embodying as major elements a dual rotor consisting of two rotor halves rotating in a circular housing and an oscillator comprised of a cascade of elliptical gears. The periphery of the housing is adapted, with respect to intake, outlet and other necessary means, to suit the purpose for which the machine is intended. The dual rotor has an even number of vanes shaped to best suit the purpose of the machine. Half of the vanes are located on each rotor half in such a manner as to be able to rotate with the rotor halves in the circular housing and to oscillate with respect to each other creating working chambers of varying volume while rotating in the same direction. The oscillations are imposed by the oscillator which includes an input-output shaft integrated with a pair of elliptical gears in the center of the cascade. The space between the dual rotor and the housing and between the respective rotor parts is sealed by a suitable sealing system.
Abstract: An improved automatic fuel shutoff system is provided for a turbine type power plant which incorporates (1) sensing means responsive to a preselected abnormal engine operating condition for initially cutting off fuel flow to the engine and (2) latching means for maintaining the cutoff until engine conditions favorable for a normal restart are obtained.
Abstract: One or more of the aft stages of the fan section of a gas turbine engine are rotated by the high pressure turbine of a gas generator and the remainder of the fan stages are rotated by a low pressure turbine downstream of the gas generator. This arrangement divides the fan work between the low and high pressure turbines to permit more efficient utilization of the total available turbine capacity, reduction in low pressure turbine workload, increased aft fan stage pressure ratio capability and greater flow and pressure ratio modulation potential for a split fan engine. The invention has a wide range of application for various turbofan configurations including separated and/or mixed flow turbofan engines with separated or close coupled fan sections.
Abstract: A combined cycle electric power plant includes gas and steam turbines and steam generators and a digital/analog control system. An automatic digital portion of the control system includes a speed control which generates a speed error from the actual turbine speed and a turbine speed reference, and a proportional plus integral controller acts on the speed error to generate a fuel reference for the gas turbine fuel valve position controls after ignition and during wide range speed control. A speed reference generator includes a stored representation of speed as a function of time with zero time made equal to the point in time at which the flame goes on. The speed versus time characterization is made up of three linear parts having different slopes.
Abstract: A rotary combustion engine is provided with an exhaust gas recirculation system that is responsive to both exhaust gas pressure and inlet vacuum and is operable to connect the working chambers adjacent their trailing end to the intake port through a variable size opening only when the chambers are nearing the end of the exhaust phase so that the differential between the pressure of the exhaust gases and the inlet mixture causes exhaust gases rich in unburned hydrocarbons in the trailing region of the chambers during the exhaust phase to flow at a rate increasing with decreasing inlet vacuum to the inlet port and thereafter be recirculated through the intake, compression and expansion phases.