Patent ID: 6672072
Filing Date: 2004-01-06
Classification: F01D,F02C,F23C,Y02T

Abstract:
A gas turbine engine cooling system for providing cooling air to engine components, said system comprising:a core engine having, in downstream serial flow relationship, a high pressure compressor, a combustor, and high pressure turbine drivingly connected to said high pressure compressor and a core flowpath therethrough; said high pressure compressor being effective for providing pressurized air; a first flowing means for flowing a portion of the pressurized air to a heat exchanger to cool the portion of the pressurized air and form the cooling air; a second flowing means for flowing a first portion of the cooling air to a compressor impeller for boosting pressure of the first portion of the cooling air and operable for flowing a second portion of the cooling air to a turbine cooling means for cooling components of said high pressure turbine; and said compressor impeller operably connected to a compressor disk of said high pressure compressor.