公开(公告)号：US20230313735A1

公开(公告)日：2023-10-05

申请号：US17708095

申请日：2022-03-30

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Lance L. Smith ,  David Lei Ma ,  Joseph B. Staubach ,  Brian M. Holley ,  Sean C. Emerson

IPC: F02C3/24 ,  F02C7/224 ,  C01B3/04

CPC classification number: F02C3/24 ,  F02C7/224 ,  C01B3/047

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

公开(公告)号：US11629858B2

公开(公告)日：2023-04-18

申请号：US17665063

申请日：2022-02-04

Applicant: Raytheon Technologies Corporation

Inventor： Malcolm MacDonald ,  Sean C. Emerson ,  Brian M. Holley ,  Lance L. Smith ,  Peter Cocks

IPC: F02C7/224 ,  F02C3/22 ,  F23R3/40 ,  F02C3/20 ,  F02C3/30 ,  F02C6/00

Abstract: A turbo-expanding cracking assembly includes a plurality of stages each including a rotating blade coupled to an output shaft and a fixed stator, at least one heat exchanger configured to transfer heat to an ammonia containing fuel flow, and a catalyst that is configured to decompose an ammonia containing fuel flow into a flow containing hydrogen (H2).

公开(公告)号：US11802508B2

公开(公告)日：2023-10-31

申请号：US17708095

申请日：2022-03-30

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Lance L. Smith ,  David Lei Ma ,  Joseph B. Staubach ,  Brian M. Holley ,  Sean C. Emerson

IPC: F02C3/22 ,  F02C7/224 ,  F02C3/04 ,  F23R3/30 ,  F02C3/24 ,  C01B3/04

CPC classification number: F02C3/22 ,  F02C3/04 ,  F02C7/224 ,  F23R3/30 ,  C01B3/047 ,  F02C3/24

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

公开(公告)号：US11920524B2

公开(公告)日：2024-03-05

申请号：US17231742

申请日：2021-04-15

Applicant: Raytheon Technologies Corporation

Inventor： Lance L. Smith ,  Timothy S. Snyder ,  Jeffrey M. Cohen ,  Peter Cocks ,  Sean C. Emerson

IPC: F02C9/40 ,  F02C7/22

CPC classification number: F02C9/40 ,  F02C7/22

Abstract: An assembly is provided for a turbine engine with a flowpath. This turbine engine assembly includes a fuel injection system. The fuel injection system includes a first fuel injector and a second fuel injector. The fuel injection system is configured to provide the first fuel injector with first fuel and provide the second fuel injector with second fuel. The first fuel may be or include ammonia. The second fuel is different than the first fuel. The second fuel may be or include hydrogen gas. The first fuel injector is configured to direct the first fuel into the flowpath for combustion. The second fuel injector is configured to direct the second fuel into the flowpath for combustion.

公开(公告)号：US20220333534A1

公开(公告)日：2022-10-20

申请号：US17231742

申请日：2021-04-15

Applicant: Raytheon Technologies Corporation

Inventor： Lance L. Smith ,  Timothy S. Snyder ,  Jeffrey M. Cohen ,  Peter Cocks ,  Sean C. Emerson

IPC: F02C9/40 ,  F02C7/22

Abstract: An assembly is provided for a turbine engine with a flowpath. This turbine engine assembly includes a fuel injection system. The fuel injection system includes a first fuel injector and a second fuel injector. The fuel injection system is configured to provide the first fuel injector with first fuel and provide the second fuel injector with second fuel. The first fuel may be or include ammonia. The second fuel is different than the first fuel. The second fuel may be or include hydrogen gas. The first fuel injector is configured to direct the first fuel into the flowpath for combustion. The second fuel injector is configured to direct the second fuel into the flowpath for combustion.

公开(公告)号：US20220299205A1

公开(公告)日：2022-09-22

申请号：US17665063

申请日：2022-02-04

Applicant: Raytheon Technologies Corporation

Inventor： Malcolm MacDonald ,  Sean C. Emerson ,  Brian M. Holley ,  Lance L. Smith ,  Peter Cocks

IPC: F23R3/40 ,  F02C7/224 ,  F02C6/00 ,  F02C3/30 ,  F02C3/20

Abstract: A turbo-expanding cracking assembly includes a plurality of stages each including a rotating blade coupled to an output shaft and a fixed stator, at least one heat exchanger configured to transfer heat to an ammonia containing fuel flow, and a catalyst that is configured to decompose an ammonia containing fuel flow into a flow containing hydrogen (H2).