公开(公告)号：US20230313711A1

公开(公告)日：2023-10-05

申请号：US18109448

申请日：2023-02-14

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Malcolm P. MacDonald ,  Stephen H. Taylor ,  Ram Ranjan

IPC: F01K23/10 ,  F01K25/10

CPC classification number: F01K23/10 ,  F01K25/103 ,  F05D2260/211 ,  F05D2220/76 ,  F05D2260/213

Abstract: A gas turbine engine includes a core engine that includes a core flow path that connects a compressor section, combustor section and a turbine section. The gas turbine engine further includes a bottoming cycle system that includes a supercritical CO2 (sCO2) working fluid flow. A first recuperator is disposed in the core flow path downstream of the turbine section, the first recuperator is configured to transfer thermal energy from a core flow aft of the turbine section to the sCO2 working fluid flow. A second recuperator is disposed in the compressor section, the second recuperator is configured to transfer thermal energy from the sCO2 working fluid flow to a location forward of the combustor section.

公开(公告)号：US12140050B2

公开(公告)日：2024-11-12

申请号：US18109448

申请日：2023-02-14

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Malcolm P. MacDonald ,  Stephen H. Taylor ,  Ram Ranjan

IPC: F01K23/10 ,  F01K25/10

Abstract: A gas turbine engine includes a core engine that includes a core flow path that connects a compressor section, combustor section and a turbine section. The gas turbine engine further includes a bottoming cycle system that includes a supercritical CO2 (sCO2) working fluid flow. A first recuperator is disposed in the core flow path downstream of the turbine section, the first recuperator is configured to transfer thermal energy from a core flow aft of the turbine section to the sCO2 working fluid flow. A second recuperator is disposed in the compressor section, the second recuperator is configured to transfer thermal energy from the sCO2 working fluid flow to a location forward of the combustor section.