RU2480601C2 - Gas turbine engine start-up control method - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: in addition, in order to increase the power of an air starter, the air supplied to the air starter turbine is heated due to combustion of fuel in it, the dosing of which is performed depending on pressure and temperature of air at the air starter inlet and gas temperature in the heating zone.

EFFECT: increase of available power of the air starter and improvement of the gas turbine engine start-up reliability.

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Description

The invention relates to the field of gas turbine engine manufacturing and can be used in electronic systems (ACS) for automatic control of gas turbine engines (GTE).

A known method of controlling the launch of a gas turbine engine with hydromechanical self-propelled guns, I. Keba "Flight operation of helicopter gas turbine engines." - M .: Transport, 1976, p. 178, which consists in the fact that in the process of starting the engine, the flight engineer, according to the indications of the device in the helicopter cockpit, controls the gas temperature behind the turbine and, if the temperature rises above a predetermined limit, turns off the engine.

The disadvantage of this method is its low efficiency.

Closest to this invention, in technical essence, is a method for controlling the start of a gas turbine engine, which consists in turning on the air starter and starting the engine rotor, measuring the rotor speed of the engine, pressure and air temperature at the engine inlet, depending on the temperature and air pressure at the engine inlet, the fuel consumption necessary to ignite the combustion chamber (KS) of the engine is determined, and when the frequency reaches the predetermined value determined for each type of engine p countable and experimentally confirmed in the course of engine PSI is supplied to the ignition rate of the COP.

The disadvantage of this method is the following.

The available power of the air starter (AC) turbine depends on the pressure and temperature of the air supplied to it and decreases (due to a drop in efficiency) as the aircraft develops a resource.

The required power required for the rotation of the engine rotor to a rotational speed at which the ignition of the compressor is possible, as the engine resource is exhausted increases (due to wear of the mechanical parts of the rotor).

Thus, a situation may arise when, due to a combination of external (temperature and air pressure) and internal (life of the mechanical part of the engine rotor) factors, starting the engine may not be possible due to a lack of aircraft power.

This reduces the reliability of the gas turbine engine and is unacceptable for aircraft not only combat aircraft, but also the civil air fleet.

The aim of the invention is to improve the quality of work of self-propelled guns of gas turbine engines and, as a result, increase the reliability of launching gas turbines.

This goal is achieved by the fact that in the method of controlling the start of a gas turbine engine, which consists in turning on the air starter and starting the engine rotor, measuring the rotor speed of the engine, pressure and air temperature at the engine inlet, depending on the temperature and air pressure at the inlet the fuel consumption necessary for ignition of the combustion chamber (CS) of the engine is determined in the engine, and when the frequency reaches a predetermined value determined for each engine type by the calculated-experimental way and the engine specified in the PSI process, the ignition flow is supplied to the compressor station, in addition to increase the power of the air starter, the air supplied to the air starter turbine is heated by burning fuel in it, dosing is carried out depending on the pressure and temperature of the air entering the air starter and gas temperatures in the heating chamber.

The figure shows a diagram of a device that implements the inventive method.

The device contains serially connected block 1 of sensors (DB), electronic controller 2 (ER), block 3 of executive elements (IE), the outputs of which are connected to the metering unit 4 of the fuel consumption in the main compressor, input 5 and output 6 of the aircraft shutters (not shown ), the dispenser 7 of the fuel consumption in the chamber for heating the air (not shown in the figure).

The device operates as follows.

On command from the cockpit “Start”, ER 2 issues commands to block 3, by which the input 5 and output 6 of the aircraft damper are opened - the aircraft is turned on and the engine rotor spins up.

Using DB 1 in ER 2, the rotor speed of the engine, the pressure and temperature of the air at the engine inlet are measured, depending on the temperature and air pressure at the engine inlet, the fuel consumption necessary for igniting the combustion chamber (KS) of the engine is determined.

So, for example, for the PS-90A2 engine developed by Aviadvigatel OJSC, this is done as follows:

where GT roses. - fuel consumption required for ignition of the compressor;

k is the coefficient of correction of the ignition flow according to the thermal state of the engine (it depends on the air temperature behind the compressor, it can vary from 0.8 to 1.2, the nominal value is 1.0);

Pin - air pressure at the engine inlet;

Tvh. - air temperature at the engine inlet.

When the engine rotor speed reaches a predetermined value determined for each engine type by calculation and experimentation and specified in the engine PSI process (for the PS-90A2 engine, this value is 1200 rpm), by command ER 2 using block 3 and dispenser 4 serves the ignition flow to the nozzles of the COP (not shown in the figure).

In addition, to increase the power of the aircraft, the air supplied through the valve 5 to the aircraft turbine (not shown in the figure) is heated by burning fuel in it, dosing of which is carried out according to the ER 2 commands using block 3 and dispenser 7, depending on the received from DB 1 values of pressure and air temperature at the inlet of the aircraft and the temperature of the gases in the heating chamber (not shown in the figure).

For example, for the 117C engine developed by JSC NPO Saturn, Rybinsk, the fuel consumption necessary for heating the air is determined as follows.

where GT pv - fuel consumption necessary for heating the air;

Pstvg is the air pressure at the inlet of the aircraft;

Tvh. - air temperature at the inlet of the aircraft;

f (Tin.) - calculated in accordance with table 1;

Out.in - gas temperature in the heating chamber;

f (Tout.ext) - calculated in accordance with table 2.

Table 1 Tvh. ° C -60 -40 -fifteen +15 +25 +40 +60 f2 0.7 0.8 one one one 0.8 0.7

table 2 Tout.hc ° C 180 220 240 280 f1 13 10 10 8

Thus, due to the heating of the air, an increase in the available power of the aircraft is ensured and, as a result, an increase in the reliability of the launch of the gas turbine engine.

Claims (1)

A method for controlling the starting of a gas turbine engine, which consists in turning on the air starter and starting the engine rotor, measuring the engine rotor speed, pressure and air temperature at the engine inlet, depending on the temperature and air pressure at the engine inlet, determining fuel consumption, necessary for ignition of the combustion chamber (CS) of the engine, and when the frequency reaches a predetermined value determined for each type of engine by calculation and experimental means and specified in pr engine PSI process, supply the ignition flow to the compressor, characterized in that, in addition to increasing the power of the air starter, the air supplied to the air starter turbine is heated by burning fuel in it, which is dosed depending on the pressure and temperature of the air entering the air starter and gas temperature in the heating zone.

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