公开(公告)号：US20220397062A1

公开(公告)日：2022-12-15

申请号：US17345205

申请日：2021-06-11

Applicant: Raytheon Technologies Corporation

Inventor： Neil Terwilliger ,  Lance L. Smith ,  Neal R. Herring ,  Christopher J. Hanlon

IPC: F02C7/32 ,  F02C7/141 ,  F02C7/18 ,  F01D15/10

Abstract: A gas turbine engine includes a turbine section located at an engine central longitudinal axis, a combustor configured to drive rotation of the turbine with combustion products, and a compressor section coupled to the turbine section at the engine central longitudinal axis and driven by the turbine section. An auxiliary compressor is located fluidly between the compressor section and the combustor such that an airflow exiting the compressor section is directed toward the auxiliary compressor. The auxiliary compressor is driven independently from the compressor section and is configured to output the airflow toward the combustor.