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公开(公告)号：US20120102961A1
公开(公告)日：2012-05-03
申请号：US12914776
申请日：2010-10-28
IPC分类号： F02K3/10
摘要： A gas turbine engine augmentor includes at least one fluid based augmentor initiator defining a chamber in flow communication with a source of air and a source of fuel. The chamber includes a plurality of ejection openings in flow communication with an exhaust flowpath. The at least one fluid based augmentor initiator is devoid of any exhaust flowpath protrusions thereby minimizing any pressure drops and loss of thrust during dry work phase of operation. The source of fuel is operable for injecting fuel into the chamber such that at least a portion of the fuel flow is ignited at the plurality of ejection openings to produce a plurality of fuel-rich hot jets radially into the exhaust flowpath.
摘要翻译： 燃气涡轮发动机增压器包括至少一个基于流体的增压器起动器，其限定与空气源和燃料源流动连通的室。 该腔室包括与排气流路流动连通的多个喷射口。 所述至少一个基于流体的增压器引发器没有任何排气流路突起，从而使在操作的干燥工作阶段期间的任何压力下降和推力损失最小化。 燃料源可操作以将燃料喷射到室中，使得燃料流的至少一部分在多个喷射口处被点燃以产生多个富燃料的热喷射流体径向地进入排气流路。
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公开(公告)号：US08991189B2
公开(公告)日：2015-03-31
申请号：US12914776
申请日：2010-10-28
摘要： A gas turbine engine augmentor includes at least one fluid based augmentor initiator defining a chamber in flow communication with a source of air and a source of fuel. The chamber includes a plurality of ejection openings in flow communication with an exhaust flowpath. The at least one fluid based augmentor initiator is devoid of any exhaust flowpath protrusions thereby minimizing any pressure drops and loss of thrust during dry work phase of operation. The source of fuel is operable for injecting fuel into the chamber such that at least a portion of the fuel flow is ignited at the plurality of ejection openings to produce a plurality of fuel-rich hot jets radially into the exhaust flowpath.
摘要翻译： 燃气涡轮发动机增压器包括至少一个基于流体的增压器起动器，其限定与空气源和燃料源流动连通的室。 该腔室包括与排气流路流动连通的多个喷射口。 所述至少一个基于流体的增压器引发器没有任何排气流路突起，从而使在操作的干燥工作阶段期间的任何压力下降和推力损失最小化。 燃料源可操作以将燃料喷射到室中，使得燃料流的至少一部分在多个喷射口处被点燃以产生多个富燃料的热喷射流体径向地进入排气流路。
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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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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
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：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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6.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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8.发明申请GROUND-BASED SIMPLE CYCLE PULSE DETONATION COMBUSTOR BASED HYBRID ENGINE FOR POWER GENERATION 有权基于地基的简单循环脉冲爆轰机组发电机发电机公开(公告)号：US20100192536A1
公开(公告)日：2010-08-05
申请号：US12362783
申请日：2009-01-30
IPC分类号： F02C5/02
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：US08707674B2
公开(公告)日：2014-04-29
申请号：US12895368
申请日：2010-09-30
CPC分类号： F02K7/02 , Y02T50/672
摘要： In one embodiment, a pulse detonation tube includes a continuous base tube having a substantially uniform wall thickness. The pulse detonation tube also includes a local flexural wave modifying feature configured to locally vary a flexural wave speed such that the flexural wave speed through the pulse detonation tube is different than an expected detonation wave speed, and/or to locally dissipate flexural wave energy.
摘要翻译： 在一个实施例中，脉冲爆管包括具有基本均匀壁厚的连续基管。 脉冲爆管还包括局部弯曲波修改特征，其被配置为局部地改变弯曲波速度，使得通过脉冲爆管的弯曲波速度不同于预期的爆震波速度，和/或局部消散弯曲波能量。
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公开(公告)号：US20110047961A1
公开(公告)日：2011-03-03
申请号：US12549920
申请日：2009-08-28
IPC分类号： F02C5/12
CPC分类号： F02C5/12 , F02K7/06 , F23R7/00 , Y02T50/671
摘要： A pulse detonation combustor valve assembly is provided that includes a fixed valve portion having an inlet and a reciprocating valve portion. The valve assembly is coupled to a pulse detonation combustor. The reciprocating valve portion is exterior to the fixed valve portion and coaxially aligned with the fixed valve portion. The reciprocating valve portion is arranged to reciprocate with respect to the fixed valve portion to control inlet flow through the inlet of the valve assembly.
摘要翻译： 提供一种脉冲爆震燃烧器阀组件，其包括具有入口和往复阀部分的固定阀部分。 阀组件连接到脉冲爆震燃烧器。 往复阀部分在固定阀部分的外部并与固定阀部分同轴对齐。 往复阀部分布置成相对于固定阀部分往复运动，以控制通过阀组件入口的入口流。
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