RU2578780C1 - Aircraft turbojet engine control method - Google Patents

Abstract

FIELD: electricity.

SUBSTANCE: invention relates to methods for regulating aircraft turbojet engines (TJE) with variable geometry of the output device. A method for controlling aircraft turbojet engine with variable geometry of the output device includes maintaining a predetermined pressure drop across the turbine according to the temperature of the inlet air to the engine and on engine operation. In the method previously for this type of engine is additionally formed with at least two control programs pressure differential across the turbine, at each management program created at the inlet into the engine and engine-out condition corresponding to different flight conditions height and speed, measured values of thrust and fuel consumption, and then build according to the fuel consumption of the thrust on them define management program that provides minimum fuel consumption in a given range of thrust and is administered for a further engine controller, and a signal from the aircraft when flying at maximum length and range in the regulator engine make switching control program differential pressure turbines for the program, which provides minimum fuel consumption.

EFFECT: implementation of the method can significantly increase the range and duration of flight of the aircraft.

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Description

The invention relates to methods for regulating an aircraft turbojet engine (turbojet engine), depending on the objectives of the flight of the aircraft, in particular to ensure maximum duration and range.

A known method of regulating an aircraft turbojet engine to a variable area of the output device, including maintaining a given law of changing the pressure drop across the turbines depending on the reduced speed of one of the engine rotors or on the air temperature at the engine inlet (see Yu.N. Nechaev, "Control laws and characteristics of aircraft power plants ", Moscow, Engineering, 1995, p. 265).

This method is not optimal in the entire area of operation of the turbojet engine due to the fact that it provides traction and speed characteristics, but it does not provide the longest flight range at cruising flight modes of the aircraft (haul modes).

The objective of the invention is to increase the efficiency of the engine at cruising flight modes of the aircraft.

The expected technical result is achieved by the fact that in the method for regulating an aircraft turbojet engine with a variable output device area, which includes maintaining a predetermined pressure drop across the turbines depending on the air temperature at the engine inlet and on the engine operating mode, according to the invention, preliminary for this type of engine is formed at least two pressure differential control programs on turbines, with each control program create at the engine inlet and outlet conditions from the engine that correspond to different flight conditions in altitude and speed, measure the thrust and fuel consumption values, build the fuel consumption dependencies for the thrust, determine the regulation program that ensures the minimum fuel consumption in the given thrust range, and enter it additionally into the engine regulator, and on a signal from the aircraft during the flight to the maximum duration and range in the engine controller, the turbine differential pressure control program is switched to a program, providing minimum fuel consumption.

The invention consists in the following. When conducting bench tests, it was noted that by shifting the control program up, the specific fuel consumption significantly improves. In view of the foregoing, it was decided to use two programs in the engine controller to maintain a given pressure drop across the turbines, providing both traction characteristics and optimal economic performance of the engine, which are necessary for driving the aircraft.

In FIG. 1 shows programs for maintaining a given pressure drop across turbines;

in FIG. 2 - graphs of the dependence of fuel consumption G _R thrust R.

For each control program under the required flight conditions, thrust (R) and fuel consumption (G _T ) are measured and the specific fuel consumption C _R = G _t / R is determined. Then build the dependence With _R = f (R) (Fig. 2).

For a given thrust value R = 4500 kgf corresponding to the cruising mode — the maximum range and flight duration mode, the smallest specific fuel consumption C _R and the program for maintaining the given pressure drop across the turbines are determined (see table).

The transition from program No. 1 - regular to program No. 3 gives a decrease in specific fuel consumption C _R by 3% and, consequently, an increase in the range and duration of the flight by the same amount - 3%.

The program with the lowest specific fuel consumption is introduced into the engine controller as an addition to the standard one to ensure the flight range.

Using this method can significantly increase the range and duration of the flight of the aircraft.

Claims (1)

A method for controlling an aircraft turbojet engine with a variable geometry of the output device, including maintaining a predetermined pressure drop across the turbines depending on the air temperature at the engine inlet and the engine operating mode, characterized in that at least two control programs are additionally generated for this type of engine the pressure drop across the turbines, with each control program create conditions corresponding to p for different flight conditions in altitude and speed, the values of thrust and fuel consumption are measured, then the dependences of fuel consumption on thrust are built, the control program is determined from them, which ensures the minimum fuel consumption in a given range of thrust and is additionally introduced into the engine regulator, and by a signal from the board when flying to the maximum duration and flight range in the engine controller, the turbine differential pressure control program is switched to a program that ensures minimum flow fuel.

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