A gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the 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. The buffer system includes a first circuit configured to selectively mix 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.
申请公布号
EP2809911(A4)
申请公布日期
2015.09.16
申请号
EP20130787586
申请日期
2013.01.16
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
GLAHN, JORN, A.;CRAWLEY, CLIFTON, J.;STRIPINIS, PHILIP, S.;ACKERMANN, WILLIAM, K.