TURBINE AIR COOLING CIRCUIT HEAT EXCHANGER Russian patent published in 2008 - IPC F02C7/12 

FIELD: engines and pumps.

SUBSTANCE: method of feeding cooling air into hot sections of turbojet engine consisting of a compressor, a diffuser, a combustion chamber, a guide nozzle assembly and a turbine driving the said compressor consists in bleeding air from air flow forced by the compressor and cooled in a heat exchanger arranged radially outside the combustion chamber. Further on, this air is forced radially inside through the guide nozzle assembly to air the turbine wheel. Cooling air is bled in the lower section of the chamber enclosing the diffuser. The guide nozzle assembly fixed blades are blown by another air portion bled in the said lower section.

EFFECT: lower pollution of the heat exchanger, higher guide nozzle assembly cooling efficiency.

4 cl, 2 dwg