公开(公告)号：US20120131901A1

公开(公告)日：2012-05-31

申请号：US12956868

申请日：2010-11-30

Applicant: Eric Richard Westervelt ,  Narendra Digamber Joshi ,  Adam Rasheed ,  Venkat Eswarlu Tangirala

Inventor： Eric Richard Westervelt ,  Narendra Digamber Joshi ,  Adam Rasheed ,  Venkat Eswarlu Tangirala

IPC: F02K7/06 ,  F02K7/02

CPC classification number: F02C9/266 ,  F02K7/06 ,  F05D2260/99 ,  F05D2270/051

Abstract: In one embodiment, a pulse detonation engine (PDE) includes a controller configured to receive signals indicative of at least one of a desired operating parameter of the PDE and a measured internal parameter of the PDE, and to adjust at least one of a first fluid flow through the PDE and a second fluid flow through at least one of multiple pulse detonation tubes disposed within the PDE based on the signals. The PDE does not include a turbine or a mechanical compressor.

Abstract translation: 在一个实施例中，脉冲爆震引擎（PDE）包括控制器，其被配置为接收指示PDE的期望操作参数和所测量的PDE的内部参数中的至少一个的信号，并且调整至少一个第一流体 基于该信号，流过PDE和通过设置在PDE内的多个脉冲爆管中的至少一个的第二流体流。 PDE不包括涡轮或机械压缩机。

公开(公告)号：US20120079806A1

公开(公告)日：2012-04-05

申请号：US12895368

申请日：2010-09-30

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

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

IPC: F02K7/02

CPC classification number: F02K7/02 ,  Y02T50/672

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US07818956B2

公开(公告)日：2010-10-26

申请号：US11129686

申请日：2005-05-13

Applicant: Adam Rasheed ,  Anthony John Dean ,  Christian Lee Vandervort

Inventor： Adam Rasheed ,  Anthony John Dean ,  Christian Lee Vandervort

IPC: F02C5/00 ,  F02C5/02 ,  F02K5/02

CPC classification number: F02K7/06 ,  F02C5/00 ,  F02K7/075 ,  F23C15/00 ,  F23R7/00 ,  Y02T50/67 ,  Y02T50/672

Abstract: A pulse detonation (PD) assembly includes a number of PD chambers adapted to expel respective detonation product streams and a number of barriers disposed between respective pairs of PD chambers. The barriers define, at least in part, a number of sectors that contain at least one PD chamber. A hybrid engine includes a number of PD chambers and barriers. The hybrid engine further includes a turbine assembly having at least one turbine stage, being in flow communication with the PD chambers and being configured to be at least partially driven by the detonation product streams. A segmented hybrid engine includes a number of PD chambers and segments configured to receive and direct the detonation product streams from respective PD chambers. The segmented hybrid engine further includes a turbine assembly configured to be at least partially driven by the detonation product streams.

Abstract translation: 脉冲爆震（PD）组件包括适于排出各个爆震产物流的多个PD室和设置在各对PD室之间的多个障碍物。 这些障碍至少部分地限定了包含至少一个PD室的多个扇区。 混合动力发动机包括多个PD室和障碍物。 混合动力发动机还包括具有至少一个涡轮级的涡轮组件，其与PD室流体连通并被构造成至少部分地被爆轰产物流驱动。 分段混合动力发动机包括多个PD室和构造成接收和引导来自相应PD室的爆轰产物流的段。 分段式混合动力发动机还包括构造成至少部分地被引爆产物流驱动的涡轮组件。

公开(公告)号：US20100154380A1

公开(公告)日：2010-06-24

申请号：US12317350

申请日：2008-12-22

Applicant: Venkat Eswarlu Tangirala ,  Narendra Digamber Joshi ,  Adam Rasheed ,  Kevin Michael Hinckley

Inventor： Venkat Eswarlu Tangirala ,  Narendra Digamber Joshi ,  Adam Rasheed ,  Kevin Michael Hinckley

IPC: F02C9/48 ,  F02C9/28

CPC classification number: F02C5/10 ,  F02C9/28 ,  F05D2260/16 ,  F05D2270/05 ,  F05D2270/304 ,  F23R7/00

Abstract: A pulse detonation combustor (PDC)-based hybrid engine control system includes a programmable controller directed by algorithmic software to control a rotational shaft speed of the PDC-based hybrid engine, an air inlet valve rotational speed for the PDC, and a fuel fill time period for the PDC in response to a corresponding low pressure turbine (LPT) shaft speed signal or a power difference signal based on a difference between desired power and actual power produced by the PDC-based hybrid engine and further in response to a fuel fill time signal for the PDC, such that a desired fuel fill fraction and stoichiometric ratio are maintained and further such that a mass air flowrate from an air compressor matches a mass air flowrate ingested via the PDC while the PDC-based hybrid engine is operating in an acceleration mode or a deceleration mode.

Abstract translation: 基于脉冲爆震燃烧器（PDC）的混合发动机控制系统包括由算法软件引导的可编程控制器，用于控制基于PDC的混合发动机的转轴转速，PDC的进气阀旋转速度和燃料填充时间 响应于相应的低压涡轮机（LPT）轴速度信号或基于由基于PDC的混合动力发动机产生的期望功率和实际功率之间的差异的功率差信号，并且还响应于燃料填充时间 信号，使得保持期望的燃料填充部分和化学计量比，并且进一步使得来自空气压缩机的质量空气流量匹配通过PDC摄入的质量空气流量，而基于PDC的混合动力发动机以加速度运行 模式或减速模式。

公开(公告)号：US20100071458A1

公开(公告)日：2010-03-25

申请号：US12627843

申请日：2009-11-30

Applicant: James Fredric Wiedenhoefer ,  Adam Rasheed

Inventor： James Fredric Wiedenhoefer ,  Adam Rasheed

IPC: G01F3/08

CPC classification number: F01C1/107

Abstract: A positive displacement flow measurement device includes a rotor portion positioned inside a casing portion to act as a least area rotor that captures a volume of material and moves the volume of material along the length of the device. The device is coupled to a means for counting the number of revolutions of the rotor portion and/or the casing portion over a predetermined period of time. In one embodiment, the counting means comprises a shaft encoder that measures the angular position of a shaft of the rotor portion and sends a signal to a processor of a computing device that determines the volume of material flowing through the device.

Abstract translation: 正位移流量测量装置包括位于壳体部分内部的转子部分，以用作捕获一定体积的材料并沿着装置的长度移动材料体积的最小区域转子。 该装置连接到用于在预定时间段内对转子部分和/或壳体部分的转数进行计数的装置。 在一个实施例中，计数装置包括轴编码器，其测量转子部分的轴的角位置并将信号发送到计算装置的处理器，该计算装置确定流过装置的材料的体积。

公开(公告)号：US07634904B2

公开(公告)日：2009-12-22

申请号：US11328394

申请日：2006-01-09

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

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

IPC: F02K5/02

CPC classification number: F23R7/00

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20070180833A1

公开(公告)日：2007-08-09

申请号：US11348869

申请日：2006-02-07

Applicant: Adam Rasheed ,  Anthony Dean

Inventor： Adam Rasheed ,  Anthony Dean

IPC: F02C5/00

CPC classification number: F02C5/02 ,  F02C5/11

Abstract: A flow control device for use with a pulse detonation chamber including an inlet coupled in flow communication with a source of compressed air. The inlet extends at least partially into the chamber to facilitate controlling air flow into the chamber. The device also includes a body portion extending downstream from and circumferentially around the inlet, wherein the body portion is positioned in flow communication with the inlet.

Abstract translation: 一种用于脉冲爆震室的流量控制装置，包括与压缩空气源流动连通的入口。 入口至少部分地延伸到室中以便于控制进入室的空气流。 该装置还包括从入口的下游和周向延伸的主体部分，其中主体部分定位成与入口流动连通。

公开(公告)号：US20070180811A1

公开(公告)日：2007-08-09

申请号：US11349489

申请日：2006-02-07

Applicant: Adam Rasheed ,  Anthony Dean

Inventor： Adam Rasheed ,  Anthony Dean

IPC: F02C5/00

CPC classification number: F23R7/00 ,  F02C5/00 ,  F02C5/10 ,  F05D2220/326 ,  F05D2220/327

Abstract: A pulse detonation combustor (PDC) assembly includes an upstream chamber forming an inlet plenum, a downstream chamber including a downstream portion of at least one PDC tube, and an integrated PDC head coupled to the upstream chamber and the downstream chamber. The integrated PDC head is configured to facilitate fuel injection and ignition within the PDC tube. The PDC tube includes an inner seal surface and an outer seal surface configured to mate with the inner seal surface, wherein the inner seal surface includes an elevated section thereon that engages with the outer seal surface such that the PDC tube is free to partially pivot about a longitudinal axis thereof.

Abstract translation: 脉冲爆震燃烧器（PDC）组件包括形成入口增压室的上游室，包括至少一个PDC管的下游部分的下游室以及耦合到上游室和下游室的集成PDC头。 集成的PDC头构造成便于PDC管内的燃料喷射和点火。 PDC管包括内密封表面和构造成与内密封表面配合的外密封表面，其中内密封表面包括在其上的升高部分，其与外密封表面接合，使得PDC管能够围绕 其纵轴。

公开(公告)号：US20070137616A1

公开(公告)日：2007-06-21

申请号：US11312409

申请日：2005-12-21

Applicant: Bruce Badding ,  Adam Rasheed ,  Anthony Dean

Inventor： Bruce Badding ,  Adam Rasheed ,  Anthony Dean

IPC: F02P5/00 ,  F02B19/00 ,  F02C7/26

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：US20050279077A1

公开(公告)日：2005-12-22

申请号：US10870876

申请日：2004-06-18

Applicant: Edward Hall ,  Adam Rasheed ,  Anthony Dean

Inventor： Edward Hall ,  Adam Rasheed ,  Anthony Dean

IPC: F02C5/00 ,  F02C5/02 ,  F02K5/02 ,  F02K7/02 ,  F02K9/78

CPC classification number: F02C5/00 ,  F02K7/02 ,  F02K9/78

Abstract: The present invention is a gas turbine engine system containing a compressor stage, a pulse detonation stage, and a turbine stage. During operation of the engine system, compressed flow from the compressor stage is directed to at least one off-axis pulse detonation tube in the pulse detonation stage. The off-axis pulse detonation tube detonates a mixture containing the compressed flow and a fuel to create a detonation wave, which is routed to an inlet portion of a reverse flow turbine. The exhaust flow from the reverse flow turbine is then directed away from the engine through ducting.

Abstract translation: 本发明是一种包含压缩机级，脉冲爆震级和涡轮级的燃气轮机发动机系统。 在发动机系统运行期间，来自压缩机级的压缩流被引导到脉冲爆震级中的至少一个离轴脉冲爆管。 离轴脉冲爆震管引爆包含压缩流和燃料的混合物以产生爆震波，该爆震波被引导到逆流涡轮机的入口部分。 然后，来自逆流涡轮机的废气流通过管道被引导离开发动机。