Fuel

A control system for a helicopter power plant with three power units driving the lifting rotor system through a main gearbox. Each power unit comprises a gas turbine engine of the gas-coupled type, a hydromechanical fuel control receiving electrical inputs to set a gas generator governor in the fuel...     

A pair of pressure transducers are connected to pressure probes positioned in a flow passage of a turbofan engine downstream of the fan and respond to pressure fluctuations which occur in the airstream. One transducer has a high response capability, and its output is passed through a band-pass filter...     

A speed-responsive governor arrangement has a lever which is movable by a governor device. A spring-loaded transmission device is engaged between an arm of the lever and an opposed face of a cam element, so that a torque applied to the lever, opposing that applied by the governor device, is dependent...     

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...     

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...     

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,...     

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...     

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...     

A device conceived with the purpose of charging air with hydrogen to give it explosive power as a novel means for generating energy by utilizing the heat obtained from the combustion of these gases. Another purpose of the invention is that of utilizing the heat produced by such combustion for the expansion...     

A pure fluidic fuel control system for a gas turbine engine in which engine speed and compressor discharge pressure are sensed and utilized to control the flow of fuel to the engine. In the system an analog fluid signal proportional to engine speed is applied to two separate fluidic circuits, one circuit...     

A control system for a helicopter power plant with three power units driving the lifting rotor system. Each power unit comprises a gas-coupled gas turbine engine, a hydromechanical fuel control receiving electrical inputs to set a gas generator governor, an engine electronic control, and engine accessories....     

A control system for a helicopter power plant with three power units driving the lifting rotor system through a main gearbox. Each power unit comprises a gas turbine engine of the gas-coupled type, a hydromechanical fuel control receiving electrical inputs to set a gas generator governor in the fuel...     

A fuel control system for a gas turbine engine providing single lever thrust control and closed loop fuel flow surge valve positioning system.

This invention relates to fuel controls for turbine types of power plants and to the means for resetting the idle speed and stator vanes from a single point contact. In one embodiment, fuel flow is reset by changing the hydraulic forces on the throttle valve and its control system which serves to provide...     

A fuel and burner variable geometry (BVG) control for a gas turbine engine. Fuel is controlled in response to the product of desired overall fuel-air ratio and a value of air flow derived from gas generator turbine speed. The desired fuel-air ratio is controlled by a speed governor, and by acceleration...     

A gas turbine power plant, particularly adapted for powering motor vehicles. The engine includes a gas generator made up of a compressor, combustion apparatus, and a turbine driving the compressor. It also includes a power turbine energized by the flow from the gas generator rotatable independently of...     

A gas turbine power plant, particularly adapted for powering motor vehicles. The engine includes a gas generator made up of a compressor, combustion apparatus, and a turbine driving the compressor. It also includes a power turbine energized by the flow from the gas generator rotatable independently of...     

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...     

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...     

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...     

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...     

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,...     

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...     

A lead-lag compensated gas-filled temperature sensor having an output which essentially matches, without error, the temperature of a flowing airstream in a gas turbine engine during both transient and steady state conditions comprises a pair of gas-filled temperature probes disposed in the airstream...     

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...     

This invention relates to fuel controls for turbine types of power plants and to the means for resetting the idle speed and stator vanes from a single point contact. In one embodiment, fuel flow is reset by changing the hydraulic forces on the throttle valve and its control system which serves to provide...     

This invention relates to a fuel distribution valve for a turbine type power plane capable of supplying fuel to a set of primary nozzles and proportioning the flow to a set or sets of secondary nozzles upon initiation of a command signal which may be manifested by the fuel control.

Control apparatus for controlling an aircraft gas-turbine engine, having two control lanes operated in parallel with one another and each of which is capable of performing the function of the control apparatus individually, includes a computer and a monitor unit associated with each lane for performing...     

Fuel distribution apparatus comprising a jet and two valves arranged in parallel in a passage connecting the fuel delivery line to the main manifold. The first valve maintains a predetermined pilot manifold pressure required for steady combustion of the fuel delivered through the pilot manifold. The...     

This disclosure deals with a variable fluid pressure regulator wherein the level at which the fluid pressure is regulated is adjustable. A member has a flow passage formed therein, and the fluid flows through the passage and out of the member, and a closure is positioned over the opening. The closure...     

A fluid flow control valve has a bore within which a control member is slidable in response to variations in a servo pressure signal. The control member is also rotatable and includes a relieved portion which co-operates with a control orifice to regulate said servo pressure signal. It is arranged that...     

In order to maintain local flame temperatures in a gas turbine engine combustor lower than 3200.degree. F. to prevent excessive formation of nitrogen oxides and above 2500.degree. F. to prevent excessive carbon monoxide formation and flameout, it is desirable to measure the flame temperature at a number...     

An electronic circuit is used to control a gas turbine engine primarily as a function of turbine inlet temperature and compressor speed and in particular includes a speed governing loop to control compressor speed according to throttle position and modified by a temperature limiting compensation loop...     

A control system for gas turbines with a gas generator which comprises a compressor, a combustion chamber, and a compressor turbine, with a power take-off device and a thrust device arranged past said gas generator and adjustable as to through-put preferably in the form of an efficiency turbine provided...     

A fluid flow control valve, particularly for use in a gas turbine engine fuel control system has an orifice with a closure member which is urged open by a pressure signal and which is urged shut by a biasing spring. The bias applied by the spring is variable by an input control lever and the response...     

There is disclosed herein a fuel control useful for automotive-type gas turbines and particularly advanced gas turbines utilizing variable geometry components to improve mileage and reduce pollution emission. The fuel control described compensates for fuel density variations, inlet temperature variations,...     

By employing in-line gas turbine power plants in the nose and tail of a low profile highly streamlined aircraft, twin engine reliability is obtained with only a single engine frontal area combined with the employment of strakes rather than pipes for the nose engine exhaust, excellent fuel economy is...     

An engine speed governor which utilizes the fuel mass itself as a control element, combined with fuel pressure regulation and orifice pressure drop. The fuel is fed through an orifice and then inwardly through radial slots in a shaft rotating at a speed proportional to engine speed, the rotating columns...     

An apparatus for monitoring whether the combustion system of a gas turbine is working properly includes an annular array of temperature sensors disposed in the gas turbine to monitor the temperature of the hot gas stream at a plurality of spaced positions and a temperature sensor disposed in the gas...     

This invention relates to a stall detector for a gas turbine engine that has as its feature, means for restarting the engine upon engine shutdown. In this mode, the automatic restart switch normally provided in an engine ignition system is made responsive to compressor discharge pressure so that it becomes...     

A fuel control system for controlling the supply of fuel to a gas turbine engine in all the engine operating ranges including the acceleration, deceleration and part-load operations. The fuel control system comprises load control signal generating means and idling control signal generating means for...     

For improved thrust responsiveness and smooth transition of the various zones of an augmentor of an augmented jet engine powered aircraft, the time to prefill the fuel manifolds of the zones are calculated from preselected parameters so as to be on line upon light-off. The throttle lever signal is rate...     

An energy producing device is driven by a motor vehicle equipped with a gas turbine engine to produce an energy stored and concurrently to give an engine braking effect to the engine to provide a braking force to decelerate the vehicle and the supply of fuel to a combustion chamber of the engine is stopped...     

An aircraft having two turbine engines is provided with both torque and temperature sensitive electronic circuitry to control the fuel supplied to the turbine engines. Pushbutton switches are provided for the selection of the desired torque level by the pilot. The fuel to either engine is reduced, regardless...     

A fuel system particularly for a gas turbine engine in which a tubular shaft rotatable during operation of the engine at engine speed or at a speed proportional thereto has a fuel inlet through which liquid fuel is introduced into the interior of the shaft, the peripheral wall of the shaft having at...     

A control circuit is described for sensing and correcting deviations in speed of a turbine-generator. The control circuit compares actual turbine speed with a speed reference signal and provides a non-linear speed control signal to the turbine. The non-linear speed control signal is characterized by...     

A new and improved low emission combustor comprises a plurality of concentric cylindrical shells spaced radially to provide air supply and cooling passages and a primary fuel supply means disposed at the inlet end and a secondary fuel supply means disposed at the outlet end and arranged so that fuel...     

A fuel control system has a boost pump for pumping liquid fuel to a positive displacement pump, which in turn meters the fuel to a fuel nozzle of a combustion engine. The positive displacement pump is variably driven independently of the boost pump, and includes a pressure regulator for minimizing pressure...     

A governor is adjusted as to speed by having a fluid diaphragm directly connected to a speeder spring which acts against a thrust bearing which bears against the flyweight toes. The fluid diaphragm is resisted by a set of low speed springs at all times. A lost motion arrangement brings a set of normal...     

An overspeed protection system is provided which utilizes simplified construction for detecting overspeed conditions of a rotating device. In the preferred embodiment, a single up/down counter is employed in an overall sequence which includes a first time period during which the counter is counted up...     

An engine auto throttle control system is disclosed wherein the stability of the high gain control loop is provided by means of complemented EPR feedback. Furthermore, the multi-engine auto throttle control system of this invention generates a stable engine thrust trim command by means of a voter mechanism...     

A servo-operated shut-off valve arrangement has a main valve responsive to a servo pressure and fluid pressure operated pilot valve for controlling the servo pressure. The pilot valve has two stable operating positions in which the main valve servo pressure is respectively vented and maintained. The...     

An output control system for a gas turbine, comprising a fuel flow control valve provided in the fuel supply circuit of the gas turbine for continuously regulating the flow rate of the fuel to be supplied to the combustor of the turbine, and a control circuit for operating the valve to enable the gas...     

A fuel flow distribution system having a hydraulically actuated flow sensing valve, a hydraulically operated switch assembly and at least one hydraulically operated on-off valve assembly. These elements are operably connected to a metered flow manifold and a plurality of distributor lines. The flow sensing...     

A control system for a gas turbine engine includes provisions for adjusting fuel flow in relation to gas generator speed, and for adjusting guide vane position in relation to power turbine speed.

A recuperated gas turbine engine fuel governor which controls fuel flow in response to both mechanical and electronic input signals.

A gas turbine fuel control system for controlling the acceleration of an engine during start-up which permits the engine to accelerate substantially along its required-to-run line. Fuel flow to the engine is controlled by a speed governor, and means are included to gradually increase the speed set point...     

A gas turbine fuel control system for controlling the acceleration of an engine during start-up which permits the engine to accelerate substantially along its required-to-run line. Fuel flow to the engine is controlled by a speed governor, and means are included to gradually increase the speed set point...     

A fuel control system having a fuel control valve provided in a main fuel path for controlling the amount of fuel for an injection valve, an ON-OFF valve provided in a sub-fuel path and bypassing the main fuel path for controlling the passage of the fuel from the fuel tank, and holding means for maintaining...     

A power boost mechanism for converting pilot linear throttle input commands to rotary motion and providing amplification of output torque to an engine fuel control and having an output shaft adapted for connection to an engine power lever assembly. An input member is movable in response to a throttle...     

A method of controlling fuel flow to a gas turbine engine includes computing the compressor discharge pressure from signals indicative of engine inlet temperature, engine speed and the computed scheduled fuel flow. The method permits accurate scheduling of fuel flow without employing a compressor discharge...     

A turbine engine over-temperature shut-off control circuit includes a series of separate timing circuits and output control signal generation gates. A corresponding set of temperature set-point triggering comparator circuits apply energization signals to their associated timing circuits and gates, to...     

Fuel flow to a gas turbine engine is controlled in response to power lever position and CDP. Fuel is supplied to the engine through three fuel flow regulating circuits which are in parallel. In one of these circuits there is a valve which establishes a minimum fuel flow which decreases with increasing...     

A compensated temperature sensing device having a sensing element capable of surviving extreme operating environments while still being able to substantially instantaneously sense temperature changes. This is accomplished by incorporating within the device an auxilliary heat source which artificially...     

An electronic fuel control system for varying the fuel flow to a gas turbine engine during the engine's acceleration. The reference speed set point of the engine's fuel controlling governor is increased as a function of the elapsed time from engine start-up and the engine characteristics so that the...     

A fuel delivery system for supplying high pressure fuel flow to a gas turbine engine which includes a first stage ejector pump driven by a second stage compressor which is driven by a hydraulically operated turbine supplied with fuel flow from a third stage gear pump.

A control system for an aircraft gas-turbine engine has positive and negative acceleration control units. Each control unit has a memory storing values of the maximum or minimum desired rate of change of fuel flow at different speeds beyond which surge or extinction will occur. The control units produce...     

A method of starting a gas turbine engine, particularly one having a high inertia rotor, in which the engine is cranked until sufficient air flow is available for lightoff, at which time fuel is injected at a fixed rate until ignition occurs, and fuel flow is then increased at a rate that is a function...     

A mechanical variable authority trim mixer for controlling the flow of fuel to an engine receives a main input from the throttle lever and a second input from a trim actuator motor. The trim mixer combines the inputs to produce a single output operably connected to the fuel metering control of the engine....     

A control system 54 for a doser type hydraulic actuator 56 is disclosed. The doser actuator includes a pair of unequal area pistons 18, 20 on a common shaft 16 which are moved incrementally by injecting into or removing from a control pressure chamber metered quantities or doses of fluid. The doses are...     

A fuel control for a gas turbine engine has a positive displacement pump (10) which directs fuel to a constant flow regulator (14) which generates a constant or fixed rate flow of fuel. A flow diverter (16) includes a dividing device which divides the constant flow of fuel between a discharge conduit...     

Gas turbine engine powerplant has an engine 10 including a fuel pump 14 driven by the engine to supply fuel to the combustor 12 thereof. The pump flow rate varies in accordance with the requirements of the engine as determined by an electric control system 17. Power supply for the control system is derived...     

A fuel control system for a spark ignition internal combustion engine of the type having a source of fuel and a pump for supplying the fuel from the fuel source and to the engine at variable flow rates. The fuel control system of the present invention is particularly suited for a reciprocating piston...     

The fuel flow for a turboprop or turboshaft engine is provided by a plurality of parallel circuits each of which supplies a portion of the fuel to the engine with different valves controlling the flow through each of the separate circuits. In the turboprop engine there is imposed on the parallel flow...     

A control system for regulating a controlled device or process, such as a turbofan engine, produces independent multiple estimates of one or more controlled variables of the device or process by combining the signals from a plurality of feedback sensors, which provide information related to the controlled...     

An emergency fuel control system for an aircraft engine, which emergency fuel control system comprises means for supplying emergency fuel to the engine such that the fuel supplied to the engine is proportional to engine speed and pressure, first fluidic means which is controlled by a pilot's throttle...     

An acceleration limit reset circuit (38, 40, 42, 44) is disclosed for a closed loop fuel control (11) of a gas turbine engine (10). The closed loop control includes a comparator circuit (28) which compares an acceleration term Ngs-Nd to a limit value Al and if the scheduled acceleration (Ngs-Nd) is in...     

A low cost, integrated, aircraft fuel management system. A system control unit receives engine variable signals and provides a signal to a motor control unit which thereby controls a variable speed motor. The motor drives a positive displacement pump which delivers and meters fuel to a slinger type turbine...     

An acceleration limit reset circuit (38, 40, 42, 44) is disclosed for a closed loop fuel control (11) of a gas turbine engine (10). The closed loop control includes a comparator circuit (28) which compares an acceleration term Ngs-Nd to a limit value Al and if the scheduled acceleration (Ngs-Nd) is in...     

This invention relates to the fuel system of a gas turbine power plant and modifies a conventional fuel control to automatically vent trapped air contained in the fuel control and fuel distribution system into the engine's burners by bypassing the conventional minimum pressure and shut off valve. This...     

Damping of a helicopter rotor drive train, the drive train including the free turbines of a gas turbine engine propulsion system, the aircraft main and tail rotors, and associated shafts and gears, is accomplished through active modulation of the fuel flow to the engine gas generator. The fuel flow is...     

The maximum speed of a turbofan engine varies in accordance with moderately complex relationships involving the temperature, the pressure or altitude, and whether or not the subordinate systems such as the anti-ice systems are operative. The maximum allowable rotational speed for the fan section of a...     

The ability of a gas turbine engine to recover from surge is enhanced by implementing a closed loop control mode wherein fuel flow is varied as a function of the ratio of the rate of change of engine gas generator speed to compressor discharge pressure.

An acceleration limiter is disclosed which includes a hydraulic accumulator (10) with a piston (10a), a spring, (10d) and a chamber 10b) for receiving the pressure Pi residing in the fuel supply circuit (3) from a point P1 in the supply circuit (3) located upstream from the injectors (2). Another chamber...     

An acceleration schedule, from which data is derived for use in calculating fuel flow during acceleration of a gas turbine engine, is modified each time the engine surges so as to avoid future surges.

Fuel flow to the burner (10) of a gas turbine engine (15) is turned on and off by a minimum pressure valve (60) controlled by a fluid pressure operated sequence valve (110). The sequence valve includes a valve element (125) set by the pressurization thereof with fuel discharged from a pump (35). The...     

A digital processor implemented electronic governor for engine-generator units including a first control loop for producing a speed error and controlling fuel delivery setting as a function thereof and a second control loop for detecting rack error and producing a field excitation current control signal...     

A controller [20] for scheduling the flow of a liquid fuel to a gas turbine engine [16]. The controller includes a fuel valve assembly [246], a compressor discharge pressure responsive (P.sub.CD) actuator [150], a differential linkage assembly [152] which is connected to the P.sub.CD actuator and a fuel...     

Damping of a helicopter rotor drive train, the drive train including the free turbines of a gas turbine engine propulsion system, the aircraft main and tail rotors, and associated shafts and gears, is accomplished through active modulation of the fuel flow to the engine gas generator. The fuel flow is...     

An invention is disclosed in which a signal indicating a rate of fuel flow desired for a gas turbine engine is bounded between limits imposed by maximal- and minimal-fuel rates allowed under the current operating conditions of the engine and between limits imposed by maximal- and minimal-accelerations...     

An apparatus for controlling a gas turbine engine. A control device is provided for controlling the energy conversion function of the engine. Adjustments of the control device are obtained by comparing an actual value of a condition of the engine with a demand value of the engine condition to produce...     

A limited authority system for controlling engine performance in accordance with energy or thrust requirements in response to engine parameters which is capable of operating in a number of control modes.

A modular thrust control lever assembly for manual pilot control of the forward/idle/reverse thrust operational modes of multiple engine aircraft and including manually manipulable pilot control levers (24L, 24R) each having a fixed lever portion (69L, 69R) and an integral crank (42L, 42R) mounted about...     

Controls for a dual element pump having first and second pumps with separate outputs wherein a modulating valve is positionable to control the amount of fuel delivered by a first pump to a fuel control and additionally to selectively control the utilization of flow delivered by the second pump. The flow...     

In the present invention, fuel flow in an aircraft is modulated automatically in order to maintain a preselected altitude.

A reduced fuel flow to a gas turbine engine experiencing impending overspeed operating conditions is provided through a line (250) which bypasses the main shutoff valve (70) of the engine's fuel control (20). A transfer valve (260) disposed in the bypass line actuates the shutoff valve in response to...     

The present invention concerns a fuel control for a gas turbine aircraft engine. The control de-riches fuel-air mixture during ground start-ups in order to reduce a temperature within the engine.

A mechanical multiplier (25) in a fuel control for a gas turbine engine has a first track member (26) mounted for lateral movement and a first axially movable displacement member (34) connected to the first track member. A second track member (42) is mounted adjacent the first track member for pivoting...     

A metering valve (20) for supplying a turbine engine with a fuel at a substantially constant flow rate in response to operational conditions evaluated by a computer (28). A signal from the computer (28) in the form of voltage pulses is supplied to a solenoid (30). The solenoid (30) regulates the flow...     

A fuel control system is provided for a turbine engine for delivering fuel from a fuel source and to the turbine engine combustion chamber to maximize fuel economy engine efficiency. The fuel control system comprises a fuel pump having its outlet connected to the inlet of a fuel control assembly while...