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1.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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2.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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公开(公告)号：US20120192546A1
公开(公告)日：2012-08-02
申请号：US13015617
申请日：2011-01-28
IPC分类号： F02K7/02
摘要： The present application provides a pulse detonation turbine engine. The pulse detonation turbine engine may include one or more pulse detonation combustors to produce a flow of combustion gases, a turbine positioned downstream of the pulse detonation combustors such that the flow of combustion gases drives the turbine, and a catalytic converter positioned downstream of the pulse detonation combustors such that the flow of combustion gases passes therethrough.
摘要翻译： 本申请提供了一种脉冲爆震涡轮发动机。 脉冲爆震涡轮发动机可以包括一个或多个脉冲爆震燃烧器以产生燃烧气体流，涡轮机位于脉冲爆震燃烧器的下游，使得燃烧气体的流动驱动涡轮，以及位于脉冲下游的催化转化器 爆炸燃烧器，使得燃烧气体流过其中。
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