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    METHOD AND APPARATUS FOR TAILORING THE EQUIVALENCE RATIO IN A VALVED PULSE DETONATION COMBUSTOR
    12.
    发明申请
    METHOD AND APPARATUS FOR TAILORING THE EQUIVALENCE RATIO IN A VALVED PULSE DETONATION COMBUSTOR 审中-公开
    在阀门脉冲爆炸装置中定量等效比的方法和装置

    公开(公告)号：US20090139203A1

    公开(公告)日：2009-06-04

    申请号：US12271091

    申请日：2008-11-14

    Applicant: Adam Rasheed ,  Ross Hartley Kenyon ,  David Chapin ,  Kevin Hinckley ,  Pierre Francois Pinard

    Inventor： Adam Rasheed ,  Ross Hartley Kenyon ,  David Chapin ,  Kevin Hinckley ,  Pierre Francois Pinard

    IPC: F02K7/02

    CPC classification number: F02C5/02 ,  F23R7/00

    Abstract: A pulse detonation combustor assembly contains at least one PDC tube, a mechanical air flow valve which directs an air flow into the PDC tube, where the mechanical air flow assembly changes a rate of the air flow into the PDC tube during a fill stage of the PDC tube. The assembly also contains a fuel flow control valve which directs fuel to the PDC tube and changes the rate of the fuel flow into PDC tube. By controlling the flow of the fuel and air into the PDC tube the equivalence ratio profile of the PDC tube can be tailored and controlled.

    Abstract translation: 脉冲爆震燃烧器组件包含至少一个PDC管，机械气流阀，其将空气流引导到PDC管中，其中机械空气流组件在填充阶段期间改变进入PDC管的空气流的速率 PDC管。 组件还包含燃料流量控制阀，其将燃料引导到PDC管并且将燃料流量改变为PDC管。 通过控制燃料和空气流入PDC管中，可以调节和控制PDC管的等效比分布。

    DUAL MODE COMBUSTION OPERATION OF A PULSE DETONATION COMBUSTOR IN A HYBRID ENGINE
    15.
    发明申请
    DUAL MODE COMBUSTION OPERATION OF A PULSE DETONATION COMBUSTOR IN A HYBRID ENGINE 失效
    混合发动机中脉冲爆炸燃烧器的双模式燃烧操作

    公开(公告)号：US20080098748A1

    公开(公告)日：2008-05-01

    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: F02C3/06

    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。

    Methods and apparatus to facilitate generating power from a turbine engine
    16.
    发明申请
    Methods and apparatus to facilitate generating power from a turbine engine 有权
    用于从涡轮发动机产生动力的方法和装置

    公开(公告)号：US20070157622A1

    公开(公告)日：2007-07-12

    申请号：US11328394

    申请日：2006-01-09

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

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

    IPC: F23R7/00

    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。

    Naturally aspirated fluidic control for diverting strong pressure waves
    17.
    发明申请
    Naturally aspirated fluidic control for diverting strong pressure waves 有权
    自然吸气流体控制用于转移强压波

    公开(公告)号：US20070015099A1

    公开(公告)日：2007-01-18

    申请号：US11172304

    申请日：2005-06-30

    Applicant: James Wiedenhoefer ,  Adam Rasheed ,  Anthony Dean ,  Pierre Pinard

    Inventor： James Wiedenhoefer ,  Adam Rasheed ,  Anthony Dean ,  Pierre Pinard

    IPC: F23D14/82

    CPC classification number: F02K7/02

    Abstract: A pulse detonation device for dividing a pulse detonation shock wave into an primary and control portion to reduce the strength of a propagating shock wave and/or change its direction. The device contains a flow separator which directs a portion of the shock wave into itself, thus reducing the shock wave's strength. In one configuration, the control region converges in cross-sectional area so as to accelerate the flow in the control region, while the primary region diverges to slow the flow in the primary region. The flow in the control region is directed, at an angle, into the flow of the primary region to impede and/or redirect the flow of the primary region.

    Abstract translation: 一种脉冲爆震装置，用于将脉冲爆震冲击波分解成初级和控制部分，以减小传播冲击波的强度和/或改变其方向。 该装置包含一个流动分离器，其将冲击波的一部分引导到其中，从而降低冲击波的强度。 在一种构造中，控制区域以横截面积收敛，以便加速控制区域中的流动，而主区域发散以减缓主区域中的流动。 控制区域中的流动以一定角度被引导到主区域的流动中，以阻止和/或重定向主区域的流动。

    Fluidic deflagration-to-detonation initiation obstacles
    19.
    发明授权
    Fluidic deflagration-to-detonation initiation obstacles 有权
    流体爆燃至起爆障碍

    公开(公告)号：US08650856B2

    公开(公告)日：2014-02-18

    申请号：US12964968

    申请日：2010-12-10

    Applicant: Justin Thomas Brumberg ,  Adam Rasheed

    Inventor： Justin Thomas Brumberg ,  Adam Rasheed

    IPC: F02K5/02 ,  F02K7/00

    CPC classification number: F02K7/02 ,  F02C5/11

    Abstract: A detonation chamber and a pulse detonation combustor including a detonation chamber, wherein the detonation chamber includes a plurality of aerodynamic jets disposed adjacent an exterior of a sidewall of the detonation chamber. The detonation chamber further includes a plurality of openings formed in the sidewall of the detonation chamber, wherein each of the plurality of openings is in fluidic communication with one of the plurality of aerodynamic jets. The plurality of aerodynamic jets are adapted to create a plurality of jet flows of a fluid within the detonation chamber during a combustion cycle defining a plurality of initiation obstacles within the detonation chamber to enhance a turbulence of a fluid flow and flame acceleration through the detonation chamber.

    Abstract translation: 一个引爆室和一个包括爆震室的脉冲爆炸燃烧室，其中爆炸室包括邻近爆炸室侧壁外部设置的多个空气动力射流。 引爆室还包括形成在爆炸室的侧壁中的多个开口，其中多个开口中的每一个开口与多个空气动力学射流中的一个流体连通。 多个空气动力学射流适于在燃烧循环期间在引爆室内产生流体的多个喷射流，该循环在爆震室内限定多个起始障碍物，以增强流体流动的紊流和通过爆轰室的火焰加速 。

    Ground-based simple cycle pulse detonation combustor based hybrid engine for power generation
    20.
    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

    Applicant: Adam Rasheed ,  Narendra Digamber Joshi ,  Venkat Eswarlu Tangirala

    Inventor： Adam Rasheed ,  Narendra Digamber Joshi ,  Venkat Eswarlu Tangirala

    IPC: F02K5/02

    CPC classification number: F02K7/06 ,  F02C5/02 ,  F05D2220/62 ,  F05D2260/96 ,  F23R7/00

    Abstract: 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.

    Abstract translation: 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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