A method of cooling a gas turbine engine and gas turbine engine

摘要

A gas turbine engine (10) includes a compressor rotor assembly (14) which directs air at a sufficient pressure and temperature to a downstream turbine (20) for cooling. The compressor assembly includes a compressor including an impeller (50) and a cooling circuit (40). The impeller includes an exit (52), an inlet (60), and a body (56) extending therebetween. The impeller body includes a first opening (64) positioned a distance (74) from the impeller exit. The cooling circuit extends between the compressor and the turbine and is in flow communication with the impeller opening.