公开(公告)号：US11692493B1

公开(公告)日：2023-07-04

申请号：US17662199

申请日：2022-05-05

Applicant: Raytheon Technologies Corporation

Inventor： Paul R. Hanrahan ,  Stephen K. Kramer ,  Daniel B. Kupratis

IPC: F02C7/36 ,  F02C9/18 ,  F02K3/06 ,  F02C7/18 ,  F02C3/04

CPC classification number: F02C7/36 ,  F02C9/18 ,  F02C3/04 ,  F02C7/18 ,  F02K3/06 ,  F05D2240/35

Abstract: A gas turbine engine includes a first spool associated with a diffuser and a primary combustor and a second spool associated with a secondary combustor. The first spool includes a first compressor and a first turbine mounted to a first shaft, and the second spool includes a second compressor and a second turbine mounted to a second shaft. An inlet duct fluidly connects the diffuser to the second compressor. An outlet duct assembly fluidly connects the second turbine to the diffuser and the primary combustor.