公开(公告)号：US20230349321A1

公开(公告)日：2023-11-02

申请号：US17730849

申请日：2022-04-27

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Stephen H. Taylor ,  Malcolm P. MacDonald ,  Dmytro M. Voytovych ,  Brian M. Holley

IPC: F02C3/10 ,  F02C6/18 ,  F01D15/10

CPC classification number: F02C3/10 ,  F02C6/18 ,  F01D15/10 ,  F05D2260/213 ,  F05D2210/12 ,  F05D2220/323 ,  F05D2260/10

Abstract: A propulsion system for an aircraft includes a core engine that includes a core flow path that is in communication with a compressor section, combustor section and a turbine section, the core engine is configured to generate a high energy gas flow, a first cycle turbine that is configured to drive a first cycle compressor at a cycle speed in response to expansion of a heated working fluid flow between a first inlet and a first outlet of the first cycle turbine, and a first power turbine that is configured to drive a first output shaft at a power speed that is different than the cycle speed in response to expansion of a working fluid flow received from the first outlet of the first cycle turbine.