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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：US20120023947A1
公开(公告)日：2012-02-02
申请号：US12848002
申请日：2010-07-30
CPC分类号： F23J15/006 , B01D53/002 , B01D2257/504 , B01D2258/0283 , F23J15/06 , F23J2215/50 , Y02C10/12 , Y02E20/16 , Y02E20/18 , 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.
摘要翻译： 本公开涉及从气体混合物中分离CO 2。 可以通过冷却气体混合物来除去CO 2，使得CO 2可以固体或液体除去。 在各种实施方案中，去除CO 2的气体混合物可以包括作为燃烧过程的一部分产生的废气，例如可用于发电过程中，尽管气体混合物可以是包括CO 2的任何气体混合物。
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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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4.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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公开(公告)号：US20110126510A1
公开(公告)日：2011-06-02
申请号：US12627942
申请日：2009-11-30
申请人： Ross Hartley Kenyon , Douglas Carl Hofer , Adam Rasheed , Mark Pombles , Narendra Digamber Joshi
发明人： Ross Hartley Kenyon , Douglas Carl Hofer , Adam Rasheed , Mark Pombles , Narendra Digamber Joshi
CPC分类号： F02C5/00 , Y02T50/671
摘要： In one embodiment, a pulse detonation combustor includes a gas discharge annulus including multiple nozzles engaged with one another via mating surfaces to support the gas discharge annulus in a circumferential direction. The pulse detonation combustor also includes multiple pulse detonation tubes extending to the nozzles.
摘要翻译： 在一个实施例中，脉冲爆震燃烧器包括气体排出环，其包括通过配合表面彼此接合的多个喷嘴，以在圆周方向上支撑气体排出环。 脉冲爆震燃烧器还包括延伸到喷嘴的多个脉冲爆管。
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6.发明授权Hot gas path component cooling for hybrid pulse detonation combustion systems 有权混合脉冲爆震燃烧系统的热气路径组件冷却公开(公告)号：US08978387B2
公开(公告)日：2015-03-17
申请号：US12974085
申请日：2010-12-21
申请人： Venkat Eswarlu Tangirala , Narendra Digamber Joshi , Adam Rasheed , Brian Gene Brzek , Douglas Carl Hofer , Thomas Michael Lavertu , Fuhua Ma
发明人： Venkat Eswarlu Tangirala , Narendra Digamber Joshi , Adam Rasheed , Brian Gene Brzek , Douglas Carl Hofer , Thomas Michael Lavertu , Fuhua Ma
CPC分类号： F02C5/02 , F02C7/18 , F02C9/18 , F05D2260/205 , F23C15/00
摘要： The flow through the core of a hybrid pulse detonation combustion system is passed through a compressor and then separated into a primary flow, that passes directly to the combustor, and a bypass flow, which is routed to a portion of the system to be used to cool components of the system. The bypass flow is routed to a nozzle of the pulse detonation combustor. The flow is then passed back into the primary flow through the core downstream of where it was extracted.
摘要翻译： 通过混合脉冲爆震燃烧系统的核心的流动通过压缩机，然后分离成直接通向燃烧器的主流，以及旁路流，其被路由到系统的一部分以用于 系统的酷组件。 旁路流被引导到脉冲爆震燃烧器的喷嘴。 然后将流体通过芯被提取的下游的核心传回初级流中。
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7.发明申请HOT GAS PATH COMPONENT COOLING FOR HYBRID PULSE DETONATION COMBUSTION SYSTEMS 审中-公开用于混合脉冲爆震燃烧系统的热气路径组件冷却公开(公告)号：US20120151895A1
公开(公告)日：2012-06-21
申请号：US12974031
申请日：2010-12-21
申请人： Venkat Eswarlu Tangirala , Narendra Digamber Joshi , Adam Rasheed , Brian Gene Brzek , Douglas Carl Hofer , Thomas Michael Lavertu , Fuhua Ma
发明人： Venkat Eswarlu Tangirala , Narendra Digamber Joshi , Adam Rasheed , Brian Gene Brzek , Douglas Carl Hofer , Thomas Michael Lavertu , Fuhua Ma
CPC分类号： F02C5/02
摘要： The flow through the core of a hybrid pulse detonation combustion system is passed through a compressor and then separated into a primary flow, that passes directly to the combustor, and a bypass flow, which is routed to a portion of the system to be used to cool components of the system. The bypass includes a pump that raises the pressure of the bypass flow sufficient to deliver it to downstream stations of the engine that contain combustion products that are at a higher pressure than the compressor exit.
摘要翻译： 通过混合脉冲爆震燃烧系统的核心的流动通过压缩机，然后分离成直接通向燃烧器的主流，以及旁路流，其被路由到系统的一部分以用于 系统的酷组件。 旁路包括一个泵，其提高旁路流的压力，足以将其输送到发动机的下游站，该发动机包含比压缩机出口更高的压力的燃烧产物。
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8.发明申请HOT GAS PATH COMPONENT COOLING FOR HYBRID PULSE DETONATION COMBUSTION SYSTEMS 有权用于混合脉冲爆震燃烧系统的热气路径组件冷却公开(公告)号：US20120151896A1
公开(公告)日：2012-06-21
申请号：US12974085
申请日：2010-12-21
申请人： VENKAT ESWARLU TANGIRALA , NARENDRA DIGAMBER JOSHI , ADAM RASHEED , Brian Gene Brzek , Douglas Carl Hofer , Thomas Michael Lavertu , Fuhua MA
发明人： VENKAT ESWARLU TANGIRALA , NARENDRA DIGAMBER JOSHI , ADAM RASHEED , Brian Gene Brzek , Douglas Carl Hofer , Thomas Michael Lavertu , Fuhua MA
IPC分类号： F02C5/00
CPC分类号： F02C5/02 , F02C7/18 , F02C9/18 , F05D2260/205 , F23C15/00
摘要： The flow through the core of a hybrid pulse detonation combustion system is passed through a compressor and then separated into a primary flow, that passes directly to the combustor, and a bypass flow, which is routed to a portion of the system to be used to cool components of the system. The bypass flow is routed to a nozzle of the pulse detonation combustor. The flow is then passed back into the primary flow through the core downstream of where it was extracted.
摘要翻译： 通过混合脉冲爆震燃烧系统的核心的流动通过压缩机，然后分离成直接通向燃烧器的主流，以及旁路流，其被路由到系统的一部分以用于 系统的酷组件。 旁路流被引导到脉冲爆震燃烧器的喷嘴。 然后将流体通过芯被提取的下游的核心传回初级流中。
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9.发明授权System and methods of assembling a supersonic compressor rotor including a radial flow channel 有权组装包括径向流动通道的超音速压缩机转子的系统和方法公开(公告)号：US08827640B2
公开(公告)日：2014-09-09
申请号：US13037675
申请日：2011-03-01
CPC分类号： F04D21/00 , B23P15/006 , F04D17/02 , F04D29/053 , F04D29/282 , F04D29/284 , F04D29/624 , Y10T29/49243 , Y10T29/49245 , Y10T29/49325
摘要： A supersonic compressor rotor that includes a rotor disk that includes a substantially cylindrical endwall, a radially inner surface, and a radially outer surface. The endwall extends between the radially inner surface and the radially outer surface. A plurality of vanes are coupled to the endwall. The vanes extend outwardly from the endwall. Adjacent vanes form a pair and are spaced a circumferential distance apart such that a flow channel is defined between each pair of circumferentially-adjacent vanes. The flow channel extends generally radially between an inlet opening and an outlet opening. A first supersonic compression ramp is coupled to the endwall. The first supersonic compression ramp is positioned within the flow channel to facilitate forming at least one compression wave within the flow channel.
摘要翻译： 一种超音速压缩机转子，其包括转子盘，转子盘包括基本上圆柱形的端壁，径向内表面和径向外表面。 端壁在径向内表面和径向外表面之间延伸。 多个叶片联接到端壁。 叶片从端壁向外延伸。 相邻的叶片形成一对并且隔开间隔开的周向距离，使得在每对周向相邻的叶片之间限定流动通道。 流动通道在入口开口和出口之间大致径向延伸。 第一超音速压缩斜坡连接到端壁。 第一超音速压缩斜坡位于流动通道内以便于在流动通道内形成至少一个压缩波。
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公开(公告)号：US08657571B2
公开(公告)日：2014-02-25
申请号：US12974566
申请日：2010-12-21
IPC分类号： F04D21/00
CPC分类号： F04D21/00 , F04D29/284 , F04D29/321 , Y10T29/49236
摘要： A supersonic compressor rotor that includes a rotor disk that includes a body that extends between a radially inner surface and a radially outer surface. A plurality of vanes are coupled to the body. The vanes extend outwardly from the rotor disk. Adjacent vanes form a pair and are oriented such that a flow channel is defined between each pair of adjacent vanes. The flow channel extends between an inlet opening and an outlet opening. At least one supersonic compression ramp is positioned within the flow channel. The supersonic compression ramp is configured to condition a fluid being channeled through the flow channel such that the fluid includes a first velocity at the inlet opening and a second velocity at the outlet opening. Each of the first velocity and the second velocity being supersonic with respect to said rotor disk surfaces.
摘要翻译： 一种超音速压缩机转子，其包括转子盘，该转子盘包括在径向内表面和径向外表面之间延伸的主体。 多个叶片联接到主体。 叶片从转子盘向外延伸。 相邻的叶片形成一对并且被定向成使得在每对相邻叶片之间限定流动通道。 流动通道在入口和出口之间延伸。 至少一个超音速压缩斜坡位于流动通道内。 超音速压缩斜坡被配置为调节通过流动通道引导的流体，使得流体包括在入口开口处的第一速度和在出口开口处的第二速度。 第一速度和第二速度中的每一个相对于所述转子盘表面是超音速的。
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