公开(公告)号：US20240328358A1

公开(公告)日：2024-10-03

申请号：US18577686

申请日：2022-07-07

申请人： Reaction Engines Ltd.

发明人： James E. Barth

IPC分类号： F02C3/20 ,  F02C6/18

CPC分类号： F02C7/224 ,  F02C3/20 ,  F02C6/18

摘要： A propulsion system comprising, an ammonia cracking module and an engine module, wherein ammonia is supplied to the ammonia cracking module to produce a fuel blend of hydrogen, nitrogen and ammonia, said fuel blend subsequently being fed to said engine module to produce energy; and wherein there is a thermal balance between the ammonia cracking module and the engine module.

公开(公告)号：US12095264B2

公开(公告)日：2024-09-17

申请号：US18140381

申请日：2023-04-27

申请人： Mitsubishi Power Americas, Inc.

发明人： David Hunt ,  David McDeed ,  Mark Peak ,  Peter Luessen ,  Brian Allen ,  Jeanfils Saint-Cyr

IPC分类号： H02J3/38 ,  F02C3/20 ,  F02C6/00 ,  H02J3/32 ,  H02J15/00 ,  H02J3/18

CPC分类号： H02J15/008 ,  F02C3/20 ,  F02C6/00 ,  H02J3/32 ,  H02J3/381 ,  F05D2220/32 ,  F05D2220/76 ,  H02J3/18 ,  H02J2300/24 ,  H02J2300/28 ,  Y02E20/16 ,  Y02E60/36

摘要： A power plant is configured to output power to a grid power system and comprises a hydrogen generation system configured to produce hydrogen, a gas turbine combined cycle power plant comprising a gas turbine engine configured to combust hydrogen from the hydrogen generation system to generate a gas stream that can be used to rotate a turbine shaft and a heat recovery steam generator (HRSG) configured to generate steam with the gas stream of the gas turbine engine to rotate a steam turbine, a storage system configured to store hydrogen produced by the hydrogen generation system, and a controller configured to operate the hydrogen generation system with electricity from the grid power system when the grid power system has excess energy and balance active and reactive loads on the grid power system using at least one of the hydrogen generation system and the gas turbine combined cycle power plant.

公开(公告)号：US12078104B2

公开(公告)日：2024-09-03

申请号：US18317545

申请日：2023-05-15

申请人： RAYTHEON TECHNOLOGIES CORPORATION

发明人： Neil J. Terwilliger ,  Joseph B. Staubach ,  Charles E. Lents

IPC分类号： F02C7/143 ,  F02C3/20 ,  F02C3/22 ,  F02C3/30 ,  F02C7/224 ,  F02C7/22 ,  F02C7/36

CPC分类号： F02C7/1435 ,  F02C3/20 ,  F02C3/22 ,  F02C3/30 ,  F02C3/305 ,  F02C7/143 ,  F02C7/224 ,  F02C7/22 ,  F02C7/36

摘要： A propulsion system includes a core engine generating a high energy gas flow, a condenser configured to extract water from the high energy gas flow and an evaporator transforming the extracted water into a steam flow. The steam flow is injected into a core flow path of the core engine increase mass flow.

公开(公告)号：US12038177B1

公开(公告)日：2024-07-16

申请号：US18121436

申请日：2023-03-14

申请人： Raytheon Technologies Corporation

发明人： Stephen K. Kramer ,  Zhongtao Dai ,  Lance L Smith ,  Gregory Boardman

IPC分类号： F23R3/14 ,  F02C3/20 ,  F02C3/30 ,  F23R3/28

CPC分类号： F23R3/14 ,  F02C3/20 ,  F02C3/30 ,  F23R3/283

摘要： An assembly is provided for a turbine engine. This assembly includes a fuel injector assembly, and the fuel injector assembly includes a fuel passage, an air passage and a steam passage. The fuel injector assembly is configured to direct fuel out of the fuel passage along an axis into a volume as a fuel flow. The fuel injector assembly is configured to direct air out of the air passage along the axis into the volume as an air flow, where the air flow circumscribes the fuel flow. The fuel injector assembly is configured to direct steam out of the steam passage along the axis into the volume as a steam flow, where the steam flow circumscribes the fuel flow and provides a radial buffer between the fuel flow and the air flow.

公开(公告)号：US11970975B2

公开(公告)日：2024-04-30

申请号：US17476129

申请日：2021-09-15

申请人： ROLLS-ROYCE PLC

发明人： Chloe J Palmer ,  Guy D Snowsill ,  Jonathan E Holt

IPC分类号： F02C7/224 ,  F02C3/20 ,  F02C3/22 ,  F02C7/04 ,  F02C7/14 ,  F02C7/143 ,  F02C7/18 ,  F02C7/22 ,  F23R3/04 ,  F23R3/28 ,  F02C9/40

CPC分类号： F02C7/224 ,  F02C3/20 ,  F02C3/22 ,  F02C7/04 ,  F02C7/14 ,  F02C7/143 ,  F02C7/18 ,  F02C7/22 ,  F02C7/222 ,  F23R3/04 ,  F23R3/286 ,  F02C9/40 ,  F05D2220/32 ,  F05D2240/35

摘要： A fuel delivery system (201) is shown for delivering the hydrogen fuel from a cryogenic storage system to a fuel injection system in a gas turbine engine. The fuel delivery system includes a pump (301), a metering device (302), and a fuel heating system (303,304) for heating the hydrogen fuel to an injection temperature for the fuel injection system.

公开(公告)号：US11959417B2

公开(公告)日：2024-04-16

申请号：US17998824

申请日：2020-09-25

申请人： Tohoku University

发明人： Hisashi Nakamura

IPC分类号： F02C3/30 ,  F02C3/20 ,  F02C3/22 ,  F02C3/34

CPC分类号： F02C3/30 ,  F02C3/20 ,  F02C3/22 ,  F02C3/34

摘要： A gas turbine (A, B, C) is provided that includes at least a compressor (1), a combustor (2), and a turbine (3) and combusts ammonia serving as fuel in the combustor (2), including a reducing agent supply device (6) configured to supply a reducing agent for reducing nitrogen oxides in a combustion gas to at least one of: a combustion gas flow path between the combustor (2) and the turbine (3); and the turbine (3).

公开(公告)号：US11846234B2

公开(公告)日：2023-12-19

申请号：US17999832

申请日：2021-05-27

申请人： SAFRAN

发明人： Thierry Sibilli ,  Sarah Rebholz

IPC分类号： F02C7/224 ,  F02C3/20 ,  F02C7/14

CPC分类号： F02C7/224 ,  F02C3/20 ,  F02C7/14

摘要： An installation for supplying a cryogenic fuel to a combustion chamber of a turbine engine of an aircraft including a tank, a mixing chamber, and one or more heat exchangers. The tank stores cryogenic fuel in a and connects to a combustion chamber for supplying the combustion chamber with cryogenic fuel in the supercritical or gaseous state. The one or more heat exchangers are provided between the cryogenic fuel and air of an air-conditioning circuit of the aircraft, mounted in a line connecting the tank for cryogenic fuel to the mixing chamber and in a line to be connected to the air-conditioning circuit of the aircraft, the heat exchange taking place therein so as to cool the air of the air-conditioning circuit of the aircraft and to increase the temperature of the cryogenic fuel coming from the tank.

公开(公告)号：US20230383950A1

公开(公告)日：2023-11-30

申请号：US18231384

申请日：2023-08-08

申请人： 8 Rivers Capital, LLC

发明人： Xijia Lu ,  Jeremy Eron Fetvedt ,  Peter Michael McGroddy

IPC分类号： F23R3/36 ,  F23L7/00 ,  F23N1/00 ,  F02C9/40 ,  F23D14/32 ,  F02C9/28 ,  F23N5/24 ,  F23N3/00 ,  F02C3/30 ,  F02C3/20 ,  F23C1/00 ,  F23K5/00 ,  F23N1/02 ,  F23N5/26

CPC分类号： F23R3/36 ,  F23L7/007 ,  F23N1/00 ,  F02C9/40 ,  F23D14/32 ,  F02C9/28 ,  F23N5/24 ,  F23N3/00 ,  F02C3/30 ,  F02C3/20 ,  F23C1/00 ,  F23K5/007 ,  F23N1/02 ,  F23N5/26 ,  F23L2900/07006 ,  F23L2900/07007 ,  F05D2270/303 ,  F23L2900/07003 ,  F23L2900/07005 ,  F23L2900/07001 ,  F23C2900/99011 ,  F23N2221/06 ,  F23N2221/08 ,  F23N2237/08 ,  F23N2241/20 ,  Y02E20/32 ,  Y02E20/34 ,  F23C2700/04 ,  F23K2900/05004 ,  F23R2900/00002

摘要： The present disclosure relates to systems and methods that are useful for controlling one or more aspects of a power production plant. More particularly, the disclosure relates to power production plants and methods of carrying out a power production method utilizing different fuel chemistries. Combustion of the different fuel mixtures can be controlled so that a defined set of combustion characteristics remains substantially constant across a range of different fuel chemistries.

公开(公告)号：US11808204B2

公开(公告)日：2023-11-07

申请号：US18007082

申请日：2021-07-21

申请人： SAFRAN ,  ARIANEGROUP SAS

发明人： Pierre-Alain Lambert ,  Hugo Pierre Mohamed Jouan ,  Samer Maalouf ,  Louis-Vianney Mabille De La Paumeliere ,  Carlos Alberto Cruz ,  Davide Duri

IPC分类号： F02C7/224 ,  F02C3/20 ,  F02C7/14 ,  F02C6/20 ,  F02C9/40 ,  F02C9/36

CPC分类号： F02C3/20 ,  F02C7/224 ,  F02C6/20 ,  F02C7/14 ,  F02C9/36 ,  F02C9/40

摘要： A fuel supply circuit for an aeronautical cryogenic turbomachine including: at least one cryogenic reservoir containing a liquid fuel topped with a boil-off gas and including a high-pressure liquid pump to supply at least one main propulsion device of the turbomachine with liquid fuel, an auxiliary turbomachine including an electric generator, a gas compressor to supply the auxiliary turbomachine with gaseous fuel, and a buffer gas reservoir connecting the gas compressor to the cryogenic reservoir to reinject gas into the cryogenic reservoir in order to maintain the pressure in the cryogenic reservoir above a predefined value, the electric generator supplying the high-pressure liquid pump and the gas compressor.

公开(公告)号：US11761381B2

公开(公告)日：2023-09-19

申请号：US17402502

申请日：2021-08-14

申请人： Pratt & Whitney Canada Corp.

发明人： Scott Smith

IPC分类号： F02C7/224 ,  F02C3/20 ,  F02C6/08 ,  F02C6/10 ,  F02C7/14 ,  F02C7/32 ,  F02C7/36 ,  F02C9/28

CPC分类号： F02C7/224 ,  F02C3/20 ,  F02C6/08 ,  F02C6/10 ,  F02C7/14 ,  F02C7/32 ,  F02C7/36 ,  F02C9/28

摘要： In accordance with at least on aspect of this disclosure, there is provided a hydrogen fuel system for aircraft. The hydrogen fuel system includes a gas turbine engine and a fuel feed conduit. The fuel feed conduit is defined at least in part by, in fluid series, a liquid hydrogen tank fluidly connected to a combustor of the gas turbine engine, a liquid hydrogen pump to drive fuel to the combustor of the gas turbine engine, an evaporator, and an electric heat source in thermal communication with the evaporator to add heat into a flow of hydrogen passing through the evaporator. In embodiments, the electric energy source associated with the electric heat source to power the electric heat source.