GAS-TURBINE ENGINE Russian patent published in 2008 - IPC F02C7/12 

FIELD: mechanical engineering; aircraft industry; gas-turbine engines.

SUBSTANCE: proposed gas-turbine engine contains high-pressure compressor whose output is connected with inner space of first working blade of high-pressure turbine. Connection is effected by two air main lines first of which includes air space of combustion chamber connected at input with output of high-pressure compressor, and at output, with channels in support of first nozzle assembly and cooling air nozzle swirler. Second air main line includes cooling air flow rate control gate communicating at input with output of high-pressure compressor, and at output, with radial pipes at input of combustion chamber and cooling air nozzle swirler. Ratio of passage area of channels in support of first nozzle assembly to passage area of cooling air nozzle swirler at input of inner space of first working blade of high-pressure turbine is 0.4-1.4. Ratio of maximum passage area of cooling air flow rate control gate to passage area of cooling air nozzle swirler at input of inner space of first working blade of high-pressure turbine is equal to 0.8-2.2.

EFFECT: improved reliability at takeoff, of economy of gas turbine engine at cruising owing to partial cutting off of cooling air getting into inner space of first working blade of high-pressure turbine.

3 dwg