公开(公告)号：EP4253739A1

公开(公告)日：2023-10-04

申请号：EP23154075.8

申请日：2023-01-30

申请人： Raytheon Technologies Corporation

发明人： SMITH, Lance L. ,  LEI MA, David ,  STAUBACH, Joseph B. ,  HOLLEY, Brian M. ,  EMERSON, Sean C.

IPC分类号： F02C3/22 ,  F02C7/143 ,  F02C7/18 ,  F02C7/224

摘要： A gas turbine engine (20) includes a core engine that includes a core flow path (C) where air is compressed in a compressor section (22), communicated to a combustor section (24), mixed with an ammonia based fuel and ignited to generate a high energy combusted gas flow (46) that is expanded through a turbine section (26). The turbine section (26) is mechanically coupled to drive the compressor section (22). An ammonia flow path communicates an ammonia flow (42) to the combustor section (24). A cracking device (48) is disposed in the ammonia flow path. The cracking device (48) is configured to decompose the ammonia flow (42) into a fuel flow (58) containing hydrogen (H2). At least one heat exchanger (62, 64, 50) is upstream of the cracking device (48) that provides thermal communication between the ammonia flow (42) and a working fluid flow (44, 60, 66) such that the ammonia fluid flow accepts thermal energy from the working fluid flow (44, 60, 66).

公开(公告)号：EP4116556A1

公开(公告)日：2023-01-11

申请号：EP22184112.5

申请日：2022-07-11

申请人： Raytheon Technologies Corporation

发明人： WIEDENHOEFER, James ,  STAUBACH, Joseph B. ,  MULDOON, Marc J. ,  LENTS, Charles E. ,  HOLLEY, Brian M.

IPC分类号： F02C3/22 ,  F02C7/18 ,  F02C7/224

摘要： A turbine engine system (200) includes at least one hydrogen fuel tank (224), a core flow path heat exchanger (300) in a core flow path; and engine systems located in the core flow path. The engine system (200) including at least a compressor section, a combustor (210) section having a burner, and a turbine section. The core flow path heat exchanger (300) is arranged in the core flow path downstream of the combustor section. The hydrogen fuel is supplied from the at least one hydrogen fuel tank (224) through a hydrogen fuel supply line (226), passing through the core flow path heat exchanger (300) and then supplied into the burner for combustion.

公开(公告)号：EP4063629A1

公开(公告)日：2022-09-28

申请号：EP22162576.7

申请日：2022-03-16

申请人： Raytheon Technologies Corporation

发明人： MacDONALD, Malcolm ,  EMERSON, Sean C. ,  HOLLEY, Brian M. ,  SMITH, Lance L. ,  COCKS, Peter

IPC分类号： F02C3/22 ,  F02C7/224

摘要： A turbo-expanding cracking assembly (40) includes a plurality of stages (52A-F) each including a rotating blade (54A-F) coupled to an output shaft (42) and a fixed stator (56A-F), at least one heat exchanger (58A-F) configured to transfer heat (76) to an ammonia containing fuel flow (48), and a catalyst (60) that is configured to decompose an ammonia containing fuel flow (48) into a flow containing hydrogen, H 2 , (50).