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公开(公告)号：US11905882B2
公开(公告)日：2024-02-20
申请号：US17660540
申请日：2022-04-25
摘要： Apparatus and methods for storing energy in liquid air and releasing the energy through a thermal power cycle, that incorporates liquid carbon dioxide capture and separation from the exhaust stream.
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公开(公告)号：US11879385B2
公开(公告)日：2024-01-23
申请号：US17170272
申请日：2021-02-08
发明人： Andrew J. Eifert
CPC分类号： F02C1/05 , F02C6/18 , F02C7/08 , F02C6/16 , F05D2220/50 , F05D2220/76 , G21D1/006 , G21D1/02 , G21D3/02
摘要： A power-generation system for a nuclear reactor includes a power unit, a reactor heat exchanger, and an auxiliary combustion system. The power unit produces compressed air that is heated by the reactor heat exchanger. The auxiliary combustion system includes an auxiliary combustor located external to the power unit and fluidly connected with the compressed air to increase the temperature of the compressed air.
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公开(公告)号：US11828228B2
公开(公告)日：2023-11-28
申请号：US18110664
申请日：2023-02-16
申请人： ROLLS-ROYCE PLC
IPC分类号： F02C7/18 , F02C7/14 , F02C7/04 , B64D27/10 , B64D33/02 , B64D33/04 , B64D33/08 , B64D27/20 , B64D33/10 , F02K3/06 , F02K3/075 , F02C7/08 , F02C7/12 , F01D9/06 , F02K3/115
CPC分类号： F02C7/04 , B64D27/10 , B64D27/20 , B64D33/02 , B64D33/04 , B64D33/08 , B64D33/10 , F01D9/065 , F02C7/08 , F02C7/12 , F02C7/18 , F02K3/06 , F02K3/075 , B64D2033/024 , B64D2033/0286 , F02C7/14 , F02K3/115 , F05D2220/323 , F05D2220/36 , F05D2260/213
摘要： An aircraft includes a machine body that encloses a turbofan gas turbine engine and a plurality of ancillary systems. The turbofan gas turbine engine includes, in axial flow sequence, a first heat exchanger module, a fan assembly, a compressor module, a combustor module, a turbine module, and an exhaust module. The aircraft includes a second heat exchanger module. The machine body comprises a single fluid inlet aperture, with the fluid inlet aperture being configured to allow a fluid cooling flow to enter the machine body and to pass through the first heat exchanger module. When a temperature of the fluid cooling flow is less than a temperature of a fluid to be cooled, the fluid to be cooled is directed to the first heat exchanger module, and when a temperature of the fluid cooling flow is greater than a temperature of the fluid to be cooled, the fluid to be cooled is directed to the second heat exchanger module and cooled using a fuel supply for the gas turbine engine.
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公开(公告)号：US20230220800A1
公开(公告)日：2023-07-13
申请号：US18001441
申请日：2021-06-15
摘要： Aircraft turbomachine including a centrifugal compressor, a combustion chamber, the combustion chamber being supplied by the compressor via a diffuser and via a straightener, and a heat exchanger, the exchanger including a first circuit, supplied with exhaust gas from the turbomachine, and a second circuit, which are connected by volutes on the one hand to an outlet of the diffuser and on the other hand to an inlet of the straightener, the volutes having reversed winding directions such that their connection ports to the exchanger are independent of one another and are substantially diametrically opposed, and such that the minimum cross section of each duct is situated at a larger cross section of the other duct.
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公开(公告)号：US20230193822A1
公开(公告)日：2023-06-22
申请号：US18110664
申请日：2023-02-16
申请人： ROLLS-ROYCE PLC
IPC分类号： F02C7/04 , F02C7/18 , B64D27/10 , B64D33/02 , B64D33/04 , B64D33/08 , B64D27/20 , B64D33/10 , F02K3/06 , F02K3/075 , F02C7/08 , F02C7/12 , F02C7/14 , F01D9/06
CPC分类号： F02C7/04 , F02C7/18 , B64D27/10 , B64D33/02 , B64D33/04 , B64D33/08 , B64D27/20 , B64D33/10 , F02K3/06 , F02K3/075 , F02C7/08 , F02C7/12 , F02C7/14 , F01D9/065 , F05D2260/213 , B64D2033/0286 , F05D2220/323 , B64D2033/024 , F05D2220/36 , F02K3/115
摘要： An aircraft includes a machine body that encloses a turbofan gas turbine engine and a plurality of ancillary systems. The turbofan gas turbine engine includes, in axial flow sequence, a first heat exchanger module, a fan assembly, a compressor module, a combustor module, a turbine module, and an exhaust module. The aircraft includes a second heat exchanger module. The machine body comprises a single fluid inlet aperture, with the fluid inlet aperture being configured to allow a fluid cooling flow to enter the machine body and to pass through the first heat exchanger module. When a temperature of the fluid cooling flow is less than a temperature of a fluid to be cooled, the fluid to be cooled is directed to the first heat exchanger module, and when a temperature of the fluid cooling flow is greater than a temperature of the fluid to be cooled, the fluid to be cooled is directed to the second heat exchanger module and cooled using a fuel supply for the gas turbine engine.
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公开(公告)号：US11674439B2
公开(公告)日：2023-06-13
申请号：US17385146
申请日：2021-07-26
申请人： PINTAIL POWER LLC
发明人： William M. Conlon
CPC分类号： F02C6/16 , F01K23/10 , F01K23/18 , F01K25/10 , F02C7/08 , F05D2220/32 , F05D2220/60 , F05D2220/72 , Y02E20/16 , Y02E60/16
摘要： Apparatus, systems, and methods store energy by liquefying a gas such as air, for example, and then recover the energy by regasifying the liquid and combusting or otherwise reacting the gas with a fuel to drive a heat engine. The process of liquefying the gas may be powered with electric power from the grid, for example, and the heat engine may be used to generate electricity. Hence, in effect these apparatus, systems, and methods may provide for storing electric power from the grid and then subsequently delivering it back to the grid.
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公开(公告)号：US11668239B2
公开(公告)日：2023-06-06
申请号：US16911263
申请日：2020-06-24
摘要： A system includes a temperature control system configured to couple to an air intake section of a gas turbine system. The temperature control system includes a variable heating system having one or more heaters configured to heat an airflow in the air intake section when the airflow is cooled by an evaporative cooling system. The temperature control system is configured to control the variable heating system to vary an amount of heat supplied by the one or more heaters based on at least one temperature measurement relative to a temperature threshold.
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公开(公告)号：US10036321B2
公开(公告)日：2018-07-31
申请号：US14290580
申请日：2014-05-29
CPC分类号： F02C7/08 , F01D25/145 , F02C1/08 , F02C7/047 , F02C9/18
摘要： Systems and methods for utilizing gas turbine compartment ventilation discharge air. In one embodiment, a system may include a gas turbine engine having a compressor. The system also may include a gas turbine compartment disposed about the gas turbine engine. Moreover, the system may include an inlet bleed heat (IBH) manifold in fluid communication with the compressor. The gas turbine compartment may be in fluid communication with the IBH manifold for providing the IBH manifold with ventilation discharge air from the gas turbine compartment.
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公开(公告)号：US09951644B2
公开(公告)日：2018-04-24
申请号：US14843585
申请日：2015-09-02
发明人： Satoshi Mizukami , Tatsuo Ishiguro , Junichiro Masada , Kazumasa Takata , Yuya Fukunaga , Hiroki Takahashi , Masaki Satoh , Yoshiaki Nishimura , Norio Oogai , Souji Hasegawa , Masato Hayashi
CPC分类号： F01D11/24 , F01D21/00 , F01D21/12 , F02C7/08 , F02C7/12 , F02C7/18 , F05D2260/205 , F05D2260/608
摘要： Provided is a gas turbine capable of achieving high-speed startup of the gas turbine through quick operation control of an ACC system during startup of the gas turbine, improving the cooling efficiency of turbine stationary components, and quickly carrying out an operation required for cat back prevention during shutdown of the gas turbine. Included are a pressurizing device (40) connected to a branching channel (42) branching from the discharge side of a compressor (11) and capable of carrying out an operation for introducing and pressurizing air independently from the compressor (11); a temperature-control-medium supply channel (43) that guides compressed air pressurized at the pressuring device (40) to a turbine-cooling-medium channel (50) provided in stationary components of a turbine (13); and a temperature-control-medium return channel (44) that guides the compressed air that has passed through the turbine-cooling-medium channel (50) to the discharge side of the compressor (11) such that the flows are combined, and the pressurizing device (40) is operated at startup of the gas turbine and in preparation immediately before startup to carry out temperature-raising and cooling by letting the compressed air flow in the turbine-cooling-medium channel (50). The pressurizing device (40) is operated during shutdown of the gas turbine to exhaust the high-temperature gas remaining in the turbine (13).
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公开(公告)号：US20180106192A1
公开(公告)日：2018-04-19
申请号：US15567197
申请日：2016-04-16
CPC分类号： F02C1/007 , F02C3/34 , F02C6/00 , F02C6/003 , F02C7/08 , F02C7/1435 , F05D2240/40 , Y02E10/34 , Y02E10/46
摘要： The present disclosure relates to a novel gas turbine having applications, for example, in thermal power generation in an environmentally friendly manner. In various embodiments, the present disclosure provides a multiloop gas turbine with enhanced efficiency close to Ericsson/Carnot Cycle and a method of operating the multiloop gas turbine.
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