COMPUTATION OF AIRCRAFT GAS TURBINE ENGINE COOLING AIR TEMPERATURE IN TRANSITIONAL OPERATION MODES

N.N. Salov, А.А. Kharchenko, V.M. Bubentsov

A method of computation of cooling air temperature during the transitional regime of aircraft turbine engines is proposed. It is marked that the temperature of cooling air substantially influences on the temperature state and descriptions of details of rotor, and character of its change at changing of the modes of operations of engine for aviation GTD and GTD of industrial application differs on principle. The change of temperature of cooling air, transported through the rotor of compressor is considered, on the modes of warming up of engine, flight, set of height and cruiser flight of airplane.

Key words: aviation gas turbine engine, the temperature of the cooling air, transitional operation modes.