Patent ID: 9027353
Filing Date: 2015-05-12
Classification: F01D,F02C,F05D,Y02T,Y10T

Abstract:
1. A gas turbine engine, comprising: a compressor section; a combustor in fluid communication with said compressor section; a turbine section in fluid communication with said combustor; a fan section configured to be driven by the turbine section via a geared architecture; and a buffer system that communicates buffer air to a portion of the gas turbine engine, wherein the buffer system includes a first circuit including a valve configured to selectively mix, based on a power condition of the gas turbine engine, a first bleed air supply having a first pressure and a second bleed air supply having a second pressure that is greater than the first pressure to provide a first buffer supply air having an intermediate pressure compared to the first pressure and the second pressure, and wherein the valve is in communication with the first bleed air supply and the second bleed air supply.