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公开(公告)号：US08584464B2
公开(公告)日：2013-11-19
申请号：US11312225
申请日：2005-12-20
CPC分类号： F02C6/18 , F02C3/10 , F02C3/113 , F02C6/04 , F02C7/143 , F05D2270/023 , F05D2270/304
摘要： A method for assembling a gas turbine engine assembly includes providing a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, and coupling a low-pressure compressor between the core gas turbine engine and a motor such that the low-pressure compressor is driven only by the motor.
摘要翻译： 燃气涡轮发动机组件的组装方法包括提供包括高压压缩机，燃烧室和高压汽轮机的核心燃气涡轮发动机，并且在核心燃气涡轮发动机和电动机之间连接低压压缩机 低压压缩机只由电机驱动。
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公开(公告)号：US07272933B2
公开(公告)日：2007-09-25
申请号：US10766437
申请日：2004-01-28
CPC分类号： A63B71/0605 , A63B63/00 , A63B2024/0043 , A63B2243/0025 , F01D25/32 , F02C3/305 , F02C7/143 , F02C7/1435 , F05D2260/211 , Y02T50/675
摘要： A method for operating a gas turbine engine, including a first compressor, a second compressor, and a turbine, coupled together in serial flow arrangement. The method includes channeling compressed airflow discharged from the first compressor through an intercooler having a cooling medium flowing therethrough, operating the intercooler such that condensate is formed in the intercooler from the compressed airflow, and channeling the condensate to an inlet of the first or second compressor to facilitate reducing an operating temperature of the gas turbine engine.
摘要翻译： 一种用于操作包括第一压缩机，第二压缩机和涡轮机的燃气涡轮发动机的方法，其以串联流动布置耦合在一起。 该方法包括将从第一压缩机排出的压缩气流引导通过具有流过其中的冷却介质的中间冷却器，操作中间冷却器，使冷凝物从压缩空气流形成在中间冷却器中，并将冷凝物引导至第一或第二压缩机的入口 以便于降低燃气轮机的工作温度。
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公开(公告)号：US07685827B2
公开(公告)日：2010-03-30
申请号：US11852802
申请日：2007-09-10
CPC分类号： A63B71/0605 , A63B63/00 , A63B2024/0043 , A63B2243/0025 , F01D25/32 , F02C3/305 , F02C7/143 , F02C7/1435 , F05D2260/211 , Y02T50/675
摘要： A method for operating a gas turbine engine, including a first compressor, a second compressor, and a turbine, coupled together in serial flow arrangement. The method includes channeling compressed airflow discharged from the first compressor through an intercooler having a cooling medium flowing therethrough, operating the intercooler such that condensate is formed in the intercooler from the compressed airflow, and channeling the condensate to an inlet of the first or second compressor to facilitate reducing an operating temperature of the gas turbine engine.
摘要翻译： 一种用于操作包括第一压缩机，第二压缩机和涡轮机的燃气涡轮发动机的方法，其以串联流动布置耦合在一起。 该方法包括将从第一压缩机排出的压缩气流引导通过具有流过其中的冷却介质的中间冷却器，操作中间冷却器，使冷凝物从压缩空气流形成在中间冷却器中，并将冷凝物引导至第一或第二压缩机的入口 以便于降低燃气轮机的工作温度。
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4.发明授权Method and apparatus for operating an intercooler for a gas turbine engine 有权用于操作燃气涡轮发动机的中间冷却器的方法和装置公开(公告)号：US07284377B2
公开(公告)日：2007-10-23
申请号：US10856640
申请日：2004-05-28
CPC分类号： F02C7/224 , F02C3/305 , F02C7/143 , Y02T50/675
摘要： A method for operating a gas turbine engine includes channeling compressed airflow discharged from a first compressor through an intercooler having a cooling medium flowing therethrough, channeling a working fluid through the intercooler to facilitate increasing an operating temperature of the working fluid, and channeling the discharged working fluid to a combustor to facilitate increasing an operating efficiency of the gas turbine engine.
摘要翻译： 一种用于操作燃气涡轮发动机的方法包括将从第一压缩机排出的压缩气流引导通过具有流过其中的冷却介质的中间冷却器，将工作流体引导通过中间冷却器，以便于增加工作流体的工作温度，并引导排出的工作 流体到燃烧器以便于提高燃气涡轮发动机的运行效率。
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公开(公告)号：US08955303B2
公开(公告)日：2015-02-17
申请号：US12717799
申请日：2010-03-04
CPC分类号： F02K7/02 , F01D5/28 , F02K7/08 , F05D2230/80 , F05D2300/13 , F05D2300/133 , F05D2300/174 , F05D2300/176 , Y02T50/67 , Y02T50/672
摘要： In one embodiment, a pulse detonation system includes a pulse detonation tube including a base tube and a thermally protective layer disposed adjacent to an inner surface of the base tube. The thermally protective layer is configured to limit temperature fluctuations at the inner surface of the base tube to less than approximately 20 degrees Celsius during operation of the pulse detonation system, and the thermally protective layer does not comprise a ceramic coating.
摘要翻译： 在一个实施例中，脉冲爆震系统包括脉冲爆管，该脉冲爆管包括基管和邻近基管的内表面设置的热保护层。 热保护层被配置为在脉冲爆震系统的操作期间将基管的内表面处的温度波动限制在小于约20摄氏度，并且热保护层不包括陶瓷涂层。
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公开(公告)号：US20130186059A1
公开(公告)日：2013-07-25
申请号：US13876738
申请日：2011-09-30
申请人： Michael Jay Epstein , Kurt David Murrow , Nicholas Rowe Dinsmore , Samuel Martin , Randy Vondrell , Robert Harold Weisgerber , Narendra Digamber Joshi
发明人： Michael Jay Epstein , Kurt David Murrow , Nicholas Rowe Dinsmore , Samuel Martin , Randy Vondrell , Robert Harold Weisgerber , Narendra Digamber Joshi
IPC分类号： F02K9/42
CPC分类号： F02K9/42 , F02C3/22 , F02C7/22 , F02C7/224 , F02C7/236 , F02C9/40 , F05D2260/85 , F05D2270/08 , F05D2270/082 , Y02T50/672 , Y02T50/677
摘要： A dual fuel propulsion system comprising a gas turbine engine configured to generate a propulsive thrust using a cryogenic liquid fuel.
摘要翻译： 一种双燃料推进系统，包括配置为使用低温液体燃料产生推进推力的燃气涡轮发动机。
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7.发明授权Ground-based simple cycle pulse detonation combustor based hybrid engine for power generation 有权用于发电的基于地基的简单循环脉冲爆震燃烧器混合发动机公开(公告)号：US08302377B2
公开(公告)日：2012-11-06
申请号：US12362783
申请日：2009-01-30
IPC分类号： F02K5/02
CPC分类号： F02K7/06 , F02C5/02 , F05D2220/62 , F05D2260/96 , F23R7/00
摘要： An engine contains a compressor stage, a compressor plenum, an inlet valving stage, a PDC stage, a PDC exit nozzle stage, a transition stage, a high pressure turbine stage, a turbine plenum, and a low pressure turbine stage. The PDC stage contains at least one pulse detonation combustor and each of the compressor plenum, PDC exit nozzle stage and turbine plenum contain a volume used to reduce and/or widen pressure peaks generated by the operation of the PDC stage.
摘要翻译： 发动机包括压缩机级，压缩机增压室，入口阀级，PDC级，PDC出口喷嘴级，过渡级，高压涡轮级，涡轮增压室和低压涡轮级。 PDC级包含至少一个脉冲爆震燃烧器，并且压缩机增压室，PDC出口喷嘴级和涡轮增压室中的每一个包含用于减少和/或加宽由PDC级的操作产生的压力峰值的体积。
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公开(公告)号：US20120023892A1
公开(公告)日：2012-02-02
申请号：US12847954
申请日：2010-07-30
CPC分类号： F23J15/006 , B01D53/002 , B01D2257/504 , B01D2258/0283 , F23J15/06 , F23J2215/50 , Y02C10/12 , Y02E20/326 , Y02E20/363
摘要： The present disclosure relates to the separation of CO2 from a gas mixture. The CO2 may be removed by cooling the gas mixture such that the CO2 can be removed as a solid or liquid. In various embodiments the gas mixture from which the CO2 is removed may include exhaust gases generated as part of a combustion process, such as may be employed in a power generation process, though the gas mixture may be any gas mixture that includes CO2.
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公开(公告)号：US20110146232A1
公开(公告)日：2011-06-23
申请号：US12645480
申请日：2009-12-23
申请人： Eric Richard Westervelt , Douglas Carl Hofer , Narendra Digamber Joshi , Kit Yan Siu , Ruijie Shi , Adam Rasheed , Venkat Eswarlu Tangirala
发明人： Eric Richard Westervelt , Douglas Carl Hofer , Narendra Digamber Joshi , Kit Yan Siu , Ruijie Shi , Adam Rasheed , Venkat Eswarlu Tangirala
IPC分类号： F02K5/02
CPC分类号： F02C5/11
摘要： A pulse detonation turbine engine (PDTE) includes at least one controllable multi-tube pulse detonation combustor (PDC) configured to initiate firing of one or more pulse detonation tubes in response to operation of a plurality of controllable peripheral PDC components to regulate PDTE output characteristics. A control system including a programmable controller directed by algorithmic software operates to generate control inputs for the plurality of controllable peripheral PDC components in response to PDTE input conditions, such that one or more PD tube controllable inputs can be different for at least one PD tube relative to another PD tube within the multi-tube PDC, and further such that detonation timing can be different for at least one PD tube relative to another PD tube within the multi-tube PDC.
摘要翻译： 脉冲爆震涡轮发动机（PDTE）包括至少一个可控多管脉冲爆震燃烧器（PDC），其被配置为响应于多个可控周边PDC部件的操作而启动一个或多个脉冲爆管的点火，以调节PDTE输出特性 。 包括由算法软件引导的可编程控制器的控制系统操作以响应于PDTE输入条件来生成针对多个可控周边PDC组件的控制输入，使得一个或多个PD管可控输入对于至少一个PD管相对 到多管PDC内的另一个PD管，并且进一步使得至少一个PD管相对于多管PDC内的另一PD管的引爆定时可以不同。
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10.发明申请THRUST MODULATION IN A MULTIPLE COMBUSTOR PULSE DETONATION ENGINE USING CROSS-COMBUSTOR DETONATION INITIATION 审中-公开使用跨燃烧器爆震启动在多个燃烧器脉冲爆震发动机中进行调速公开(公告)号：US20110126511A1
公开(公告)日：2011-06-02
申请号：US12627763
申请日：2009-11-30
CPC分类号： F02C5/00 , F05D2270/051
摘要： A method and apparatus for modulating the thrust during a flight envelope of a multiple combustor chamber detonation engine using cross-combustor chamber detonation initiation are provided. The detonation combustor chambers are filled with a combustible mixture of fuel and oxidizer. The combustible mixture in one of the detonation combustor chambers is ignited by an ignition source, and the remaining detonation combustor chambers are ignited by detonation cross-firing via connectors. A controller controls the ignition source and the supply of oxidizer and fuel to the detonation combustor chambers to modulate the thrust of the engine during the flight envelope.
摘要翻译： 提供了一种使用交叉燃烧器室爆震启动来调节多燃烧室室爆震发动机的飞行包络内的推力的方法和装置。 爆炸燃烧室中充满燃料和氧化剂的可燃混合物。 其中一个引爆燃烧室中的可燃混合物被点火源点燃，剩余的爆炸燃烧室通过连接器的爆炸交叉点燃。 控制器控制点火源，并将氧化剂和燃料供应到爆炸燃烧器室，以在飞行包络内调节发动机的推力。
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