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    Ground-based simple cycle pulse detonation combustor based hybrid engine for power generation
    4.
    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

    申请人： Adam Rasheed ,  Narendra Digamber Joshi ,  Venkat Eswarlu Tangirala

    发明人： Adam Rasheed ,  Narendra Digamber Joshi ,  Venkat Eswarlu Tangirala

    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。

    CONTROL SYSTEM FOR A PULSE DETONATION TURBINE ENGINE
    6.
    发明申请
    CONTROL SYSTEM FOR A PULSE DETONATION TURBINE ENGINE 审中-公开
    一种脉冲爆震涡轮发动机的控制系统

    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。

    THRUST MODULATION IN A MULTIPLE COMBUSTOR PULSE DETONATION ENGINE USING CROSS-COMBUSTOR DETONATION INITIATION
    7.
    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

    申请人： Aaron Jerome Glaser ,  Adam Rasheed ,  Douglas Carl Hofer ,  Narendra Digamber Joshi

    发明人： Aaron Jerome Glaser ,  Adam Rasheed ,  Douglas Carl Hofer ,  Narendra Digamber Joshi

    IPC分类号： F02K5/02 ,  F02C9/00

    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。