Centrifugal compressor impeller downstream face cooling system for aircraft turbomachine e.g. turbojet and jet prop engines, has cylindrical passage and sheet guiding drawn ventilating air till neighborhood of downstream face of impeller

摘要

The system has a labyrinth seal (76) for intake of a fraction of a ventilating air flow of a turbine on an air injecting unit (36) of the turbine. An annular cylindrical passage (75) and a cylindrical sheet (94) guide the drawn ventilating air till neighborhood of a downstream face (40) of an impeller (18) of a centrifugal compressor (14). The cylindrical passage is formed around a shaft (20) of the compressor between the injecting unit and the downstream face.