公开(公告)号：US20240026827A1

公开(公告)日：2024-01-25

申请号：US18091860

申请日：2022-12-30

Applicant: Raytheon Technologies Corporation

Inventor： Steven W. Burd ,  Christopher A. Eckett

IPC: F02C7/32 ,  F02C3/073 ,  F02C3/113 ,  F02C3/14 ,  F02C6/18

CPC classification number: F02C7/32 ,  F02C3/073 ,  F02C3/113 ,  F02C3/14 ,  F02C6/18 ,  F05D2220/323 ,  F05D2220/50

Abstract: An aircraft system is provided that includes a gas turbine engine, a gearbox and at least one compressor. The gas turbine engine includes a compressor section, a turbine section, a combustor section and a rotating structure. The combustor section is fluidly coupled with and between the compressor section and the turbine section. The rotating structure includes a compressor section rotor within the compressor section and a turbine section rotor within the turbine section. The at least one compressor includes a compressor rotor rotatably driven by the rotating structure through the gearbox. The gas turbine engine may be dedicated to powering the at least one compressor.