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1. 发明授权

US07634904B2 Methods and apparatus to facilitate generating power from a turbine engine 有权
标题翻译：用于从涡轮发动机产生动力的方法和装置
公开(公告)号：US07634904B2
公开(公告)日：2009-12-22
申请号：US11328394
申请日：2006-01-09
申请人： Adam Rasheed , Anthony John Dean , Venkat Eswarlu Tangirala , Pierre Francois Pinard , Christian Lee Vandervort
发明人： Adam Rasheed , Anthony John Dean , Venkat Eswarlu Tangirala , Pierre Francois Pinard , Christian Lee Vandervort
IPC分类号： F02K5/02
CPC分类号： F23R7/00
摘要： A turbine disk assembly including a rotatable cylindrical member rotatably coupled to a shaft and a plurality of turbine blades extend circumferentially outward from said cylindrical member. The turbine blades include at least two different geometrical shapes, a first of the geometrical shapes is configured to facilitate extracting power from a first pulsed detonation combustor product stream. A second of said geometrical shapes is configured to facilitate extracting power from a second pulsed detonation combustor product stream that is different from the first pulsed detonation combustor product stream.
摘要翻译：包括可旋转地联接到轴的可旋转圆柱形构件和多个涡轮机叶片的涡轮盘组件从所述圆柱形构件周向向外延伸。涡轮机叶片包括至少两个不同的几何形状，第一几何形状被配置为便于从第一脉冲爆炸燃烧器产物流提取动力。所述几何形状中的第二个被配置为便于从与第一脉冲爆炸燃烧器产物流不同的第二脉冲爆炸燃烧器产物流提取功率。

2. 发明申请

US20080115480A1 PULSE DETONATION ENGINE BYPASS AND COOLING FLOW WITH DOWNSTREAM MIXING VOLUME 失效
标题翻译：脉冲爆震发动机旁路和冷却流量与下游混合体积
公开(公告)号：US20080115480A1
公开(公告)日：2008-05-22
申请号：US11561155
申请日：2006-11-17
申请人： Adam Rasheed , Anthony John Dean , Pierre Francois Pinard , Christian Lee Vandervort , Venkat Eswarlu Tangirala
发明人： Adam Rasheed , Anthony John Dean , Pierre Francois Pinard , Christian Lee Vandervort , Venkat Eswarlu Tangirala
IPC分类号： F02C5/00
CPC分类号： F02C5/11 , F02C5/02 , F02K7/04
摘要： An engine contains at least one pulse detonation combustor which is surrounded by a bypass flow air duct, through which bypass air flow is directed. The bypass air duct contains at least one converging-diverging structure to dampen or choke the upstream propagation of shock waves from the pulse detonation combustor through the bypass flow air duct. The bypass air also serves to cool the outer surfaces of the pulse detonation combustor. The bypass air flow is controlled in tandem with the heat release from the PDC to provide the appropriate amount of thermal energy to a downstream energy conversion device, such as a turbine. A mixing plenum is positioned downstream of the pulse detonation combustor and bypass flow air duct.
摘要翻译：发动机包含至少一个脉冲爆震燃烧器，其被旁路气流导管包围，旁路气流通过旁路气流引导。旁路空气管道包含至少一个会聚发散结构，以阻尼或阻塞来自脉冲爆震燃烧器的冲击波的上游传播通过旁路流动空气管道。旁路空气还用于冷却脉冲爆震燃烧器的外表面。旁路空气流与PDC的放热一起控制，以向下游能量转换装置（例如涡轮机）提供适当量的热能。混合气室位于脉冲爆震燃烧器和旁路流动空气管道的下游。

3. 发明申请

US20080229756A1 SYSTEM AND METHOD FOR PASSIVE VALVING FOR PULSE DETONATION COMBUSTORS 有权
标题翻译：用于脉冲爆炸燃烧器的被动阀的系统和方法
公开(公告)号：US20080229756A1
公开(公告)日：2008-09-25
申请号：US11566041
申请日：2006-12-01
申请人： Pierre Francois Pinard , Kevin Michael Hinckley , Venkat Eswarlu Tangirala , Adam Rasheed , David Michael Chapin , Anthony John Dean
发明人： Pierre Francois Pinard , Kevin Michael Hinckley , Venkat Eswarlu Tangirala , Adam Rasheed , David Michael Chapin , Anthony John Dean
IPC分类号： F02C7/26 , F02C7/22
CPC分类号： F02K7/02 , F02C5/00
摘要： A pulse detonation device contains a pulse detonation combustor which detonates a mixture of oxidizer and fuel. The fuel is supplied through fuel ducts and the fuel flow is controlled by fuel flow control devices. Oxidizer flow is provided through a main inlet portion and a flow control device directs the oxidizer flow to either the combustor or to a bypass duct, or both. The combustor further contains an ignition source. Each of the flow control devices, fuel flow control devices and ignition source are controlled by a control system to optimize performance at different thrust/power settings for the device.
摘要翻译：脉冲爆震装置包含爆震氧化剂和燃料混合物的脉冲爆震燃烧器。燃料通过燃料管道供应，燃料流由燃料流量控制装置控制。通过主入口部分提供氧化剂流，并且流量控制装置将氧化剂流引导至燃烧器或旁路管道，或两者。燃烧器还包含点火源。每个流量控制装置，燃料流量控制装置和点火源由控制系统控制，以在设备的不同推力/功率设置下优化性能。

4. 发明授权

US08726630B2 System and method for passive valving for pulse detonation combustors 有权
标题翻译：用于脉冲爆震燃烧器的无源阀的系统和方法
公开(公告)号：US08726630B2
公开(公告)日：2014-05-20
申请号：US11566041
申请日：2006-12-01
申请人： Pierre Francois Pinard , Kevin Michael Hinckley , Venkat Eswarlu Tangirala , Adam Rasheed , David Michael Chapin , Anthony John Dean
发明人： Pierre Francois Pinard , Kevin Michael Hinckley , Venkat Eswarlu Tangirala , Adam Rasheed , David Michael Chapin , Anthony John Dean
IPC分类号： F02G1/00 , F02C5/00 , F02K5/02 , F02C5/02 , F02C1/00
CPC分类号： F02K7/02 , F02C5/00
摘要： A pulse detonation device contains a pulse detonation combustor which detonates a mixture of oxidizer and fuel. The fuel is supplied through fuel ducts and the fuel flow is controlled by fuel flow control devices. Oxidizer flow is provided through a main inlet portion and a flow control device directs the oxidizer flow to either the combustor or to a bypass duct, or both. The combustor further contains an ignition source. Each of the flow control devices, fuel flow control devices and ignition source are controlled by a control system to optimize performance at different thrust/power settings for the device.
摘要翻译：脉冲爆震装置包含爆震氧化剂和燃料混合物的脉冲爆震燃烧器。燃料通过燃料管道供应，燃料流由燃料流量控制装置控制。通过主入口部分提供氧化剂流，并且流量控制装置将氧化剂流引导至燃烧器或旁路管道，或两者。燃烧器还包含点火源。每个流量控制装置，燃料流量控制装置和点火源由控制系统控制，以在设备的不同推力/功率设置下优化性能。

5. 发明授权

US07669405B2 Shaped walls for enhancement of deflagration-to-detonation transition 有权
标题翻译：形状的墙壁，用于加强爆燃转爆
公开(公告)号：US07669405B2
公开(公告)日：2010-03-02
申请号：US11315407
申请日：2005-12-22
申请人： Pierre Francois Pinard , Venkat Eswarlu Tangirala , Adam Rasheed , Anthony John Dean , Ronald Scott Bunker , David Michael Chapin
发明人： Pierre Francois Pinard , Venkat Eswarlu Tangirala , Adam Rasheed , Anthony John Dean , Ronald Scott Bunker , David Michael Chapin
IPC分类号： F02K5/02
CPC分类号： F23R7/00
摘要： A detonation chamber for a pulse detonation combustor including: a plurality of dimples disposed on at least a portion of an inner surface of the detonation chamber wherein the plurality of dimples enhance a turbulence of a fluid flow through the detonation chamber.
摘要翻译：一种用于脉冲爆震燃烧器的爆炸室，包括：多个凹坑，其布置在所述爆震室的内表面的至少一部分上，其中所述多个凹坑增强通过所述引爆室的流体流动的紊流。

6. 发明申请

US20090139199A1 PULSE DETONATION COMBUSTOR VALVE FOR HIGH TEMPERATURE AND HIGH PRESSURE OPERATION 审中-公开
标题翻译：用于高温和高压运行的脉冲爆炸式气动阀
公开(公告)号：US20090139199A1
公开(公告)日：2009-06-04
申请号：US12271082
申请日：2008-11-14
申请人： Ross Hartley Kenyon , Narendra Digamber Joshi , Venkat Eswarlu Tangirala , Anthony John Dean , Adam Rasheed , Aaron Jerome Glaser , James Fredric Wiedenhoefer , David Chapin , Kevin Hinckley , Pierre Francois Pinard
发明人： Ross Hartley Kenyon , Narendra Digamber Joshi , Venkat Eswarlu Tangirala , Anthony John Dean , Adam Rasheed , Aaron Jerome Glaser , James Fredric Wiedenhoefer , David Chapin , Kevin Hinckley , Pierre Francois Pinard
IPC分类号： F02C5/12
CPC分类号： F02C5/02 , F23R7/00
摘要： A pulse detonation combustor valve assembly contains at least one pulse detonation combustor having an inlet portion through which air and/or fuel enters the chamber of the combustor. An annular rotating valve portion is positioned adjacent to an outer surface of the pulse detonation combustor and concentrically with the pulse detonation combustor so that the annular rotating valve portion can be rotated with respect to the combustor. The annular rotating valve portion contains at least one inlet portion through which air and/or fuel passes to enter the inlet portion of the pulse detonation combustor.
摘要翻译：脉冲爆震燃烧器阀组件包含至少一个具有入口部分的脉冲爆燃燃烧器，空气和/或燃料通过该入口部分进入燃烧室的腔室。环形旋转阀部分定位成与脉冲爆震燃烧器的外表面相邻并且与脉冲爆震燃烧器同心地定位，使得环形旋转阀部分可相对于燃烧器旋转。环形旋转阀部分包含至少一个入口部分，空气和/或燃料通过该入口部分进入脉冲爆震燃烧器的入口部分。

7. 发明授权

US07841167B2 Pulse detonation engine bypass and cooling flow with downstream mixing volume 失效
标题翻译：脉冲爆震发动机旁路和冷却流量与下游混合量
公开(公告)号：US07841167B2
公开(公告)日：2010-11-30
申请号：US11561155
申请日：2006-11-17
申请人： Adam Rasheed , Anthony John Dean , Peirre Francois Pinard , Christian Lee Vandervort , Venkat Eswarlu Tangirala
发明人： Adam Rasheed , Anthony John Dean , Peirre Francois Pinard , Christian Lee Vandervort , Venkat Eswarlu Tangirala
IPC分类号： F02K5/02
CPC分类号： F02C5/11 , F02C5/02 , F02K7/04
摘要： An engine contains at least one pulse detonation combustor which is surrounded by a bypass flow air duct, through which bypass air flow is directed. The bypass air duct contains at least one converging-diverging structure to dampen or choke the upstream propagation of shock waves from the pulse detonation combustor through the bypass flow air duct. The bypass air also serves to cool the outer surfaces of the pulse detonation combustor. The bypass air flow is controlled in tandem with the heat release from the PDC to provide the appropriate amount of thermal energy to a downstream energy conversion device, such as a turbine. A mixing plenum is positioned downstream of the pulse detonation combustor and bypass flow air duct.
摘要翻译：发动机包含至少一个脉冲爆震燃烧器，其被旁路气流导管包围，旁路气流通过旁路气流引导。旁路空气管道包含至少一个会聚发散结构，以阻尼或阻塞来自脉冲爆震燃烧器的冲击波的上游传播通过旁路流动空气管道。旁路空气还用于冷却脉冲爆震燃烧器的外表面。旁路空气流与PDC的放热一起控制，以向下游能量转换装置（例如涡轮机）提供适当量的热能。混合气室位于脉冲爆震燃烧器和旁路流动空气管道的下游。

8. 发明授权

US07526912B2 Pulse detonation engines and components thereof 失效
标题翻译：脉冲爆震发动机及其部件
公开(公告)号：US07526912B2
公开(公告)日：2009-05-05
申请号：US11262652
申请日：2005-10-31
申请人： Venkat Eswarlu Tangirala , Adam Rasheed , Christian Lee Vandervort , Anthony John Dean
发明人： Venkat Eswarlu Tangirala , Adam Rasheed , Christian Lee Vandervort , Anthony John Dean
IPC分类号： F02C5/02
CPC分类号： F23R3/005 , F23C15/00 , F23R7/00 , Y02T50/675
摘要： A pulse detonation engine comprises a primary air inlet; a primary air plenum located in fluid communication with the primary air inlet; a secondary air inlet; a secondary air plenum located in fluid communication with the secondary air inlet, wherein the secondary air plenum is substantially isolated from the primary air plenum; a pulse detonation combustor comprising a pulse detonation chamber, wherein the pulse detonation chamber is located downstream of and in fluid communication with the primary air plenum; a coaxial liner surrounding the pulse detonation combustor defining a cooling plenum, wherein the cooling plenum is in fluid communication with the secondary air plenum; an axial turbine assembly located downstream of and in fluid communication with the pulse detonation combustor and the cooling plenum; and a housing encasing the primary air plenum, the secondary air plenum, the pulse detonation combustor, the coaxial liner, and the axial turbine assembly.
摘要翻译：脉冲爆震发动机包括一次空气入口; 位于与一次空气入口流体连通的主要空气室; 二次空气入口; 位于与二次空气入口流体连通的二次空气增压室，其中二次空气增压室基本上与一次空气通风室隔离; 脉冲爆震燃烧器，其包括脉冲爆震室，其中所述脉冲爆震室位于所述主要空气通风室的下游并且与所述主要空气通风室流体连通; 环绕所述脉冲爆震燃烧器的同轴衬套限定冷却气室，其中所述冷却气室与所述二次空气通风室流体连通; 轴向涡轮机组件，位于脉冲爆震燃烧器和冷却气室的下游并与流体连通; 以及包围主空气增压室，二次空气增压室，脉冲爆震燃烧器，同轴衬套和轴向涡轮机组件的壳体。

9. 发明授权

US07614211B2 Swirling flows and swirler to enhance pulse detonation engine operation 有权
标题翻译：旋流和旋流器，以增强脉冲爆震发动机的运行
公开(公告)号：US07614211B2
公开(公告)日：2009-11-10
申请号：US11304411
申请日：2005-12-15
申请人： David Michael Chapin , Anthony John Dean , Christian Lee Vandervort , Venkat Eswarlu Tangirala , Edward Randall Furlong
发明人： David Michael Chapin , Anthony John Dean , Christian Lee Vandervort , Venkat Eswarlu Tangirala , Edward Randall Furlong
IPC分类号： F02K5/02
CPC分类号： F02K7/02 , F02C5/00 , F23C7/004 , F23R3/14 , F23R7/00
摘要： A swirler having cross-sectional area comparable to the area of a detonation chamber is placed upstream of the detonation chamber to enhance the fuel-air mixing. The swirler has a first region and a second region, each of which induces swirl in the flow through the swirler. Each region induces a different direction of swirl in the flow. The residual net swirl present in the flow downstream of the swirler is controlled by the relative properties of each region of the swirler. The swirler also provides high optical blockage to inhibit the upstream propagation of flow due to the detonation shockwave.
摘要翻译：具有与爆震室的面积相当的横截面面积的旋流器设置在爆震室的上游，以增强燃料 - 空气混合。旋流器具有第一区域和第二区域，每个区域在流过旋流器的流中引起漩涡。每个区域在流动中引起不同的旋流方向。旋流器下游的流动中存在的残余净涡流由旋流器的每个区域的相对特性控制。旋流器还提供高的光学阻塞，以抑制由于爆震冲击波引起的上游流动传播。

10. 发明申请

US20090241507A1 GROUND BASED PULSE DETONATION COMBUSTOR FOR POWER GENERATION 有权
标题翻译：用于发电的基于地基的脉冲爆炸燃烧器
公开(公告)号：US20090241507A1
公开(公告)日：2009-10-01
申请号：US12060557
申请日：2008-04-01
申请人： Venkat Eswarlu Tangirala , Adam Rasheed , Narendra Digamber Joshi , Anthony John Dean
发明人： Venkat Eswarlu Tangirala , Adam Rasheed , Narendra Digamber Joshi , Anthony John Dean
IPC分类号： F02C5/00 , F01D5/08 , F02C7/143
CPC分类号： F02C5/00 , F02C7/08 , F02C7/143 , Y02T50/675
摘要： A ground based power generation system contains at least two compressor stages, a combustion stage and a turbine stage. An intercooler is positioned between the two compressor stages and a regenerator is positioned between the compressor stages and the combustion stage. The combustion stage contains at least one of a pulse detonation combustor and constant volume combustor. Downstream of the combustion stage is the turbine stage. Heat for the regenerator is supplied from the turbine stage. Further, a bypass flow device is included which re-directs flow upstream of the combustion stage to downstream of the combustion stage and upstream of the turbine stage.
摘要翻译：基于地面的发电系统包含至少两个压缩机级，燃烧级和涡轮级。中间冷却器位于两个压缩机级之间，并且再生器位于压缩机级和燃烧级之间。燃烧阶段包括脉冲爆震燃烧器和恒定体积燃烧器中的至少一个。燃烧阶段的下游是涡轮机阶段。用于再生器的热量由涡轮级供给。此外，还包括旁路流动装置，其将燃烧阶段上游的流动重新引导到燃烧阶段的下游以及涡轮级的上游。

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