公开(公告)号：US11149641B2

公开(公告)日：2021-10-19

申请号：US16812807

申请日：2020-03-09

Applicant: Raytheon Technologies Corporation

Inventor： Joseph D. Evetts ,  William J. Riordan ,  Federico Papa

IPC: F02C7/12 ,  F02C7/18 ,  F02C6/08 ,  B64D29/00 ,  F01D25/24 ,  F02C3/04 ,  F02C9/18 ,  B64D13/08 ,  F01D11/24

Abstract: A method of cooling a gas turbine engine case assembly includes moving a fan air valve that is operatively connected to a pre-cooler having a bypass inlet that is configured to receive bypass air that bypasses a gas turbine engine core to facilitate a provision of bypass air through a fan air valve inlet to the bypass inlet to a first open position, in response to a core compartment temperature being greater than a target core compartment temperature. The method further includes bleeding the bypass air through a bypass outlet of the pre-cooler into a core compartment.