GAS TURBINE ENGINE Russian patent published in 2015 - IPC F02C7/06 F02C7/14 

FIELD: engines and pumps.

SUBSTANCE: in gas-turbine engine air cavities of shaft and bearing supports are connected with the high and low air pressure ring manifolds designed with a possibility of switching of air selection from the high air pressure manifold to the low air pressure manifold. The low air pressure manifold at the inlet is connected with the flow-through part of the gas-turbine engine downstream the third stage of the low pressure compressor. The high air pressure manifold at the inlet is connected with the flow-through part of the gas-turbine engine downstream the third stage of the high pressure compressor. Between the high air pressure manifold and air cavities of bearing support and the shaft the air-air heat exchanger placed in the channel of external circuit of the gas-turbine engine is installed.

EFFECT: invention improves reliability of the gas-turbine engine by decrease of air temperature passing from the high pressure manifold for cooling of shafts of the gas-turbine engine and for pressurisation of air cavities of bearing supports.

4 dwg