METHOD FOR PROVIDING STRENGTH OF TURBINE OF GAS TURBINE ENGINE Russian patent published in 2021 - IPC G01M15/02 G01M15/14 

FIELD: testing.

SUBSTANCE: invention relates to aircraft gas turbine engines, namely to methods for testing during creation thereof, experimental development of characteristics of a prototype and an industrial model, and operation. Proposed is a method including a normalised change in the temperature field in front of and behind the combustion chamber while changing the operating mode of the engine and a long operating time. The fuel consumption of the power unit, the heating chamber and the combustion chamber, the air flow rate through the blower of the power unit and into the combustion chamber, the static and total pressure behind the combustion chamber, the pressure and the temperature of the gas in the measuring sections of the inner and the outer channels, the speed of the low and high pressure compressor of the power unit engine and the speed of the blower, the air temperature at the inlet to the power unit engine and the blower, the temperature of the medium in the combustion chamber are measured; additionally, using a rotary turret, the gas temperature at the outlet from the combustion chamber is measured. The measured values of the parameters are used to determine the specific air velocity at the inlet to the combustion chamber and the air temperature at the inlet to the diffuser, wherein the average mass gas temperature is determined in real time using grid methods for imaging the results of multipoint boundary value problems, excluding by regulation the values of the gas temperature not corresponding to the basic values, from the combined gas temperature calculation based on the measured values of the air and fuel consumption set in the measurement section. The change in the average radial regulated irregularity of gas temperature field distribution from the condition of providing the strength of the turbine is executed by maintaining the set pressures, temperatures and the specific air velocity at the inlet to the combustion chamber and considering the relative flow rates of the air taken for cooling the turbine.

EFFECT: invention makes it possible to reduce the costs of creation and experimental development of combustion chambers, to achieve the required averaged characteristics of the combustion chamber by the completeness of fuel combustion and the content of substances in the exhaust gases, stalling and starting characteristics, acceptable losses of total pressure and temperature of the elements of the combustion chamber.

1 cl, 6 dwg, 1 tbl