RU2367808C2 - Gas turbine engine thrust control system - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: invention relates to aircraft engineering, particularly to aircraft gas turbine thrust control systems. In compliance with this invention, thrust measurement unit comprises two laser anemometres, one designed to measure exhaust gas velocity while the other one measures flight speed. Microprocessor with memory unit computes thrust value from the formula R=f(G_B, c_C, V_P). Proposed thrust control system incorporates also thrust measurement unit, fuel metering unit, adder, anemometre to measure exhaust gas velocity, anemometre to measure flight speed and microprocessor with memory unit.

EFFECT: higher accuracy of control.

1 dwg

Description

The invention relates to aircraft, and in particular to thrust control systems for gas turbine engines (GTE) of aircraft (LA).

A device is known that implements a method for regulating an aircraft turboprop engine (RU 2023897 dated 10.11.1994), comprising a fuel consumption regulator, a rotational speed regulator, two actuators, a rotor speed value sensor, a thrust value sensor, comparison elements, an adder, a current flow value sensor fuel and optimization block.

A disadvantage of the described device is that thrust control in the described system is carried out indirectly by maintaining other engine parameters set, which does not provide the required thrust control accuracy over a wide range of flight conditions and engine operating conditions.

The technical task of the claimed device is to increase the accuracy of engine control by traction.

The solution to the technical problem of the invention lies in the fact that in the traction control system of a gas turbine engine comprising a thrust measurement unit, a fuel metering unit and an adder, the thrust measurement unit contains two laser anemometers and a microprocessor with a memory unit, while one anemometer measures the flow rate (jet) gases from the engine nozzle, and using the second anemometer, the flight speed is measured, the microprocessor calculates the thrust value according to the formula R = f (G _B , s _s , V _p ), where G _B is the air flow through the engine, and _{s c} is the gas outflow rate in from the nozzle of the engine, V _p - the speed of the aircraft.

The measurement of the velocity of a gas stream is described, see Klochkov V.P., Kozlov L.F., Potikevich I.V., Soskin M.S. Laser anemometry, remote spectroscopy and interferometry. Kiev. Naukova Dumka, 1985.S. 21-22, 415, 419.

The technical result of the invention is to increase the accuracy of regulation, while increasing the accuracy of maintaining thrust by measuring it has become possible due to the use of a thrust measurement unit in the gas turbine engine control system containing two laser anemometers that measure the gas flow velocity by the non-contact method.

The drawing shows a structural diagram of a traction control system for a gas turbine engine.

The traction control system of a gas turbine engine contains a thrust measuring unit 1, a fuel metering unit 2 and an adder 3, while the thrust measuring unit 1 contains two laser anemometers (4 and 5) and a microprocessor 6 with a memory unit, while one anemometer 4 measures the gas flow rate from the engine nozzle, and using the second anemometer 5, the flight speed is measured, the microprocessor calculates the thrust value according to the formula R = f (G _B , s _s , V _p ), where G _c is the air flow through the engine, and _{s c} is the rate of gas outflow from engine nozzles, V _p - airplane flight speed that one.

The system operates as follows.

Depending on the specified flight mode of the aircraft (altitude and speed) at the first input of the adder 3 the required value of the engine thrust R _ass . At the same time, in unit 1 of the thrust measurement, the actual value of the current thrust value R _{tech of the} engine is determined by the formula R = G _B ( _s -V _p ), where G _in is the air flow through the engine, with _c is the rate of gas outflow from the engine nozzle, V _p - aircraft flight speed, see. Theory and calculation of jet engines / Ed. A.V.Shlyakhtenko. - M.: Mechanical Engineering, 1987, p. 48. Velocities c _c and V _{p are} determined using laser anemometers, see Klochkov V.P., Kozlov L.F., Potikevich I.V., Soskin M.S. Laser anemometry, remote spectroscopy and interferometry. Kiev. Naukova Dumka, 1985, pp.21-22, 415, 419. The value of G _in is determined through the frequency of rotation of the turbine, see Theory and calculation of jet engines / Ed. A.V.Shlyakhtenko. - M.: Mechanical Engineering, 1987, p.219 and B. Cherkasov. Automation and Regulation of Aircraft Engines: A Textbook in the Specialty “Aircraft Engines”, 3rd ed. reslave. and add. - M.: Mechanical Engineering, 1988. S. 9.

If the set value of the thrust R _ass does not correspond to the current value of the thrust R _tech , then in the adder 3 a signal ΔR = R _ass -R _tech is generated that is not equal to zero. In accordance with the received control signal ΔR, the fuel metering unit 2 changes the fuel consumption in the gas turbine engine.

A change in fuel consumption causes a change in engine parameters. This process continues until the equality R _ass = R _tech .

The proposed system for controlling a gas turbine engine by traction can be easily implemented using an on-board digital computer (BCM).

Claims (1)

A gas turbine engine thrust control system comprising a thrust measuring unit, a fuel metering unit and an adder, characterized in that the thrust measuring unit contains two laser anemometers and a microprocessor with a memory unit, while one anemometer measures the gas flow rate from the engine nozzle, and using the second anemometers measure flight speed, the microprocessor calculates thrust according to the formula R = f (G _in , s _s , V _p ), where G _in is the air flow through the engine, with _c is the velocity of the outflow of gases from the engine nozzle, V _p is the aircraft flight speed.

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