TURBINE COOLING SYSTEM OF TWO-CIRCUIT AIR-BREATHING ENGINE Russian patent published in 2024 - IPC F01D5/18 

FIELD: heat engines.

SUBSTANCE: double-circuit gas turbine engines and stationary gas turbine units. The system proposes to use a more optimal supply and distribution of cooling air in the cooling system and reduce the magnitude of axial forces acting on the high-pressure rotor bearing (HPR). The invention will make it possible to reduce the temperature at the inlet to the cooling cavities of the blades, reduce the cooling air flow rate, reduce the cooling air flow rate when cooling is partially switched off, prevent the flow of hot gas into the cavities of the air system and into the cooling cavities of the blades from the flow part at minimum engine cooling modes and reduce the magnitude of the axial forces acting on the HPR bearing.

EFFECT: increase in efficiency, specific thrust and engine economy at cruising operating modes while maintaining the values of these parameters at maximum modes, as well as an increase in engine life.

3 cl, 5 dwg