FIELD: machine building.
SUBSTANCE: gas turbine engine comprises a fan, a compressor, a combustion chamber, a high-pressure turbine and a low-pressure turbine, arranged serially and communicating along the flow. The compressor comprises rows of compressor fins designed for serial compression of air in appropriate stages. The high-pressure turbine comprises a row of hollow nozzle blades having front and rear inner cooling channels, downstream which there is a row of hollow rotor fins, having front and rear inner cooling channels. The gas turbine engine also comprises the first, second, third and fourth circuits of air supply connected so that they communicate along the flow with different stages of the compressor for bleeding of air under pressure from them with different values of pressure to supply the first, second, third and fourth coolers into the front and rear channels of the blade and front and rear channels of the fin accordingly.
EFFECT: higher efficiency factor of the engine by reduction of air supply under pressure arriving from the compressor.
10 cl, 6 dwg
