FIELD: engines and pumps.
SUBSTANCE: anti-icing system of the gas turbine engine contains the heat exchanger installed in air-gas channel of the engine upstream the engine compressor. The air tapped downstream the last stage of the compressor is supplied through the heat exchanger into the turbine cooling system. The pressure ratio of the compressor is greater than 25, and flow rate of the air tapped from the compressor amounts δ = (0.05÷0.07)·(1+m), where δ - a share of the air tapped from the compressor; m - engine bypass ratio. Between the heat exchanger and the compressor the protection grid is installed.
EFFECT: anti-icing system protects the engine from penetration of ice and other foreign subjects, improves traction and input-output characteristics of the engine.
4 cl, 2 dwg
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