公开(公告)号：US20110214407A1

公开(公告)日：2011-09-08

申请号：US12717799

申请日：2010-03-04

Applicant: Brian Gene Brzek ,  Adam Rasheed ,  Narendra Digamber Joshi

Inventor： Brian Gene Brzek ,  Adam Rasheed ,  Narendra Digamber Joshi

IPC: F02C5/00

CPC classification number: F02K7/02 ,  F01D5/28 ,  F02K7/08 ,  F05D2230/80 ,  F05D2300/13 ,  F05D2300/133 ,  F05D2300/174 ,  F05D2300/176 ,  Y02T50/67 ,  Y02T50/672

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US07950219B2

公开(公告)日：2011-05-31

申请号：US11554929

申请日：2006-10-31

Applicant: Venkat Eswarlu Tangirala ,  Adam Rasheed ,  Anthony John Dean

Inventor： Venkat Eswarlu Tangirala ,  Adam Rasheed ,  Anthony John Dean

IPC: F02K5/02

CPC classification number: F02K7/06 ,  F02K3/06 ,  F23R3/286 ,  F23R7/00

Abstract: A dual mode combustor of a gas turbine engine contains at least one dual mode combustor device having a combustion chamber, a fuel air mixing element, a high frequency solenoid valve and a fuel injector. During a first mode of operation the dual mode combustor device operates in a steady, constant pressure deflagration mode, receiving its fuel from the fuel injector. In a second mode of operation the dual mode combustor device operates in a pulse detonation mode, receiving its fuel from the high frequency solenoid valve.

Abstract translation: 燃气涡轮发动机的双模式燃烧器包含至少一个具有燃烧室，燃料空气混合元件，高频电磁阀和燃料喷射器的双模燃烧器装置。 在第一操作模式期间，双模式燃烧器装置以稳定的恒定压力爆燃模式工作，从燃料喷射器接收燃料。 在第二操作模式中，双模式燃烧器装置以脉冲爆震模式操作，从高频电磁阀接收燃料。

公开(公告)号：US07784287B2

公开(公告)日：2010-08-31

申请号：US11312409

申请日：2005-12-21

Applicant: Bruce John Badding ,  Adam Rasheed ,  Anthony John Dean

Inventor： Bruce John Badding ,  Adam Rasheed ,  Anthony John Dean

IPC: F02C7/22

CPC classification number: F02P23/04 ,  F02C5/02 ,  F02C7/264 ,  F02K1/34 ,  F05D2260/96 ,  F05D2260/962 ,  F05D2270/14

Abstract: An aircraft engine is provided with at least one pulse detonation device, and the operational frequency of the pulse detonation device is varied over an operational range of frequencies around a mean frequency value. The pulse detonation device can be positioned upstream, downstream or adjacent to a turbine section of the engine. An additional embodiment of the present invention is an aircraft engine provided with more than one pulse detonation device, and the operational frequency of one, or more, of the pulse detonation devices is varied over an operational range of frequencies around a mean frequency value.

Abstract translation: 飞机发动机设置有至少一个脉冲爆震装置，并且脉冲爆震装置的工作频率在围绕平均频率值的频率的工作范围内变化。 脉冲爆震装置可以位于发动机的涡轮机部分的上游，下游或邻近。 本发明的另外的实施例是设置有多于一个脉冲爆震装置的飞机发动机，并且脉冲爆震装置中的一个或多个的操作频率在围绕平均频率值的频率的工作范围内变化。

公开(公告)号：US07721523B2

公开(公告)日：2010-05-25

申请号：US12060557

申请日：2008-04-01

Applicant: Venkat Eswarlu Tangirala ,  Adam Rasheed ,  Narendra Digamber Joshi ,  Anthony John Dean

Inventor： Venkat Eswarlu Tangirala ,  Adam Rasheed ,  Narendra Digamber Joshi ,  Anthony John Dean

IPC: F02C7/10

CPC classification number: F02C5/00 ,  F02C7/08 ,  F02C7/143 ,  Y02T50/675

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20090266047A1

公开(公告)日：2009-10-29

申请号：US12271070

申请日：2008-11-14

Applicant: Ross Hartley Kenyon ,  Narendra Digamber Joshi ,  Venkat Eswarlu Tangirala ,  Anthony John Dean ,  Adam Rasheed ,  Aaron Jerome Glaser

Inventor： Ross Hartley Kenyon ,  Narendra Digamber Joshi ,  Venkat Eswarlu Tangirala ,  Anthony John Dean ,  Adam Rasheed ,  Aaron Jerome Glaser

IPC: F02C5/02

CPC classification number: F02C5/02 ,  F02C5/12 ,  F05D2250/322 ,  F23C15/00 ,  F23D14/42 ,  F23R3/425 ,  F23R7/00 ,  F23R2900/00014

Abstract: An engine contains a compressor stage, a pulse detonation combustion stage and a turbine stage. The pulse detonation combustion stage contains at least one pulse detonation combustor which has an inlet portion. The pulse detonation combustor is oriented longitudinally and/or tangentially with respect to a centerline of the engine.

Abstract translation: 发动机包含压缩机级，脉冲爆震燃烧级和涡轮级。 脉冲爆震燃烧阶段包含至少一个具有入口部分的脉冲爆震燃烧器。 脉冲爆震燃烧器相对于发动机的中心线纵向和/或切向地定向。

公开(公告)号：US20090220368A1

公开(公告)日：2009-09-03

申请号：US12040161

申请日：2008-02-29

Applicant: James Fredric Wiedenhoefer ,  Adam Rasheed

Inventor： James Fredric Wiedenhoefer ,  Adam Rasheed

IPC: F04C2/107

CPC classification number: F01C1/107

Abstract: A positive displacement capture apparatus contains a plurality of positive displacement capture devices which each contain a rotor portion positioned inside a casing portion to act as a least area rotor which captures a volume and moves the volume along the length of the separator. The rotor portion contains a plurality of lobes which interact with grooves in the casing portion, such that the interaction of the lobes and grooves create barriers which capture the volume. The creation of the volume creates a flow barrier between a downstream end of the separator and an upstream end of the separator. The flow separator is coupled to a combustion portion to provide a flow of material to the combustion portion. The plurality of positive displacement capture devices are positioned, oriented and rotational timed such that eccentric loads created by the rotation of the rotor portions cancel each other out during operation.

Abstract translation: 正位移捕获装置包括多个正位移捕获装置，每个容积捕获装置包含位于壳体部分内的转子部分，以用作捕获体积并沿着分离器的长度移动体积的最小区域转子。 转子部分包含与壳体部分中的凹槽相互作用的多个凸角，使得凸角和凹槽的相互作用产生捕获体积的障碍物。 卷的创建在分离器的下游端和分离器的上游端之间产生流动阻挡。 流动分离器联接到燃烧部分以向燃烧部分提供材料流。 多个正位移捕获装置被定位，定向和旋转定时，使得由转子部分的旋转产生的偏心负载在操作期间相互抵消。

公开(公告)号：US07526912B2

公开(公告)日：2009-05-05

申请号：US11262652

申请日：2005-10-31

Applicant: Venkat Eswarlu Tangirala ,  Adam Rasheed ,  Christian Lee Vandervort ,  Anthony John Dean

Inventor： Venkat Eswarlu Tangirala ,  Adam Rasheed ,  Christian Lee Vandervort ,  Anthony John Dean

IPC: F02C5/02

CPC classification number: F23R3/005 ,  F23C15/00 ,  F23R7/00 ,  Y02T50/675

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20080155959A1

公开(公告)日：2008-07-03

申请号：US11963212

申请日：2007-12-21

Applicant: Adam Rasheed ,  Anthony John Dean ,  James Fredric Wiedenhoefer ,  Venkat Eswarlu Tangirala ,  Narendra Digamber Joshi

Inventor： Adam Rasheed ,  Anthony John Dean ,  James Fredric Wiedenhoefer ,  Venkat Eswarlu Tangirala ,  Narendra Digamber Joshi

IPC: F02C5/00 ,  F01D25/30 ,  F02C7/00

CPC classification number: F02C5/00 ,  F01D9/023 ,  F05D2250/141 ,  F05D2260/16 ,  Y02T50/675

Abstract: A transition piece for use within a gas turbine engine provides a path between the exhaust from one or more pressure-rise combustors and a downstream turbine for the extraction of work from the exhaust flow. The transition piece provides a non-expanding path for the exhaust flow through the transition piece, and directs the flow so as to be effective in driving the turbine when it reaches the end of the transition piece.

Abstract translation: 在燃气涡轮发动机内使用的过渡件提供了来自一个或多个压力升高燃烧器的排气和用于从排气流中提取工作的下游涡轮之间的路径。 过渡件为通过过渡件的排气提供非扩张路径，并引导流动，以便在涡轮到达过渡件的端部时有效驱动涡轮机。

公开(公告)号：US20060260291A1

公开(公告)日：2006-11-23

申请号：US11135195

申请日：2005-05-20

Applicant: Christian Vandervort ,  Adam Rasheed ,  Anthony Dean ,  Venkat Tangirala ,  Pierre Pinard ,  James Wiedenhoefer

Inventor： Christian Vandervort ,  Adam Rasheed ,  Anthony Dean ,  Venkat Tangirala ,  Pierre Pinard ,  James Wiedenhoefer

IPC: F02C5/00

CPC classification number: F02C5/00 ,  F02K7/02 ,  F02K7/06 ,  F05D2260/202 ,  F23C15/00 ,  F23R7/00 ,  Y02T50/675

Abstract: A pulse detonation (PD) assembly includes at least one PD chamber having a wall, which defines cooling holes arranged along at least a portion of the PD chamber. A manifold extends around the PD chamber. The manifold and PD chamber are separated by a bypass region. A PD assembly with reverse flow cooling includes at least one PD chamber. A sleeve extends around the PD chamber. The sleeve and PD chamber are separated by a reverse flow cooling passage configured to receive a flow of air and to flow the air in a reverse direction to supply the PD chamber. A PD assembly with bypass flow cooling includes at least one PD chamber and a manifold extending around the PD chamber(s), which are separated by a bypass region. The PD assembly further includes a mixing plenum configured to receive and mix the bypass flow from the bypass region and the detonation by-products from the PD chamber(s).

Abstract translation: 脉冲爆震（PD）组件包括具有壁的至少一个PD室，其限定沿着PD室的至少一部分布置的冷却孔。 歧管围绕PD室延伸。 歧管和PD室由旁路区域分开。 具有逆流冷却的PD组件包括至少一个PD室。 套筒围绕PD室延伸。 套筒和PD室由逆流冷却通道隔开，反流冷却通道构造成接收空气流并使空气沿相反方向流动以供应PD室。 具有旁路流冷却的PD组件包括至少一个PD室和围绕PD室延伸的歧管，其由旁路区域分开。 PD组件还包括配置为接收和混合来自旁路区域的旁路流和来自PD室的爆炸副产物的混合增压室。

公开(公告)号：US07055308B2

公开(公告)日：2006-06-06

申请号：US10452422

申请日：2003-05-30

Applicant: Pierre Francois Pinard ,  Anthony John Dean ,  Adam Rasheed

Inventor： Pierre Francois Pinard ,  Anthony John Dean ,  Adam Rasheed

IPC: F02K5/02 ,  F02C7/24

CPC classification number: F02K7/02 ,  F02C5/00 ,  F05D2260/96

Abstract: An engine includes at least one pulse detonation chamber configured to receive and detonate a fuel and an oxidizer. The pulse detonation chamber has an outlet end and includes a porous liner adapted to fit within an inner surface of the pulse detonation chamber within a vicinity of the outlet end. The engine also includes a casing housing the pulse detonation chamber.

Abstract translation: 发动机包括至少一个脉冲爆震室，其配置成接收和引爆燃料和氧化剂。 脉冲爆震室具有出口端，并且包括适于装配在出口端附近的脉冲爆震室的内表面内的多孔衬里。 发动机还包括容纳脉冲爆震室的壳体。