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51 条记录 (耗时 0.016 秒)

    Pulse detonation combustor
    4.
    发明授权
    Pulse detonation combustor 有权
    脉冲爆震燃烧器

    公开(公告)号：US08899010B2

    公开(公告)日：2014-12-02

    申请号：US12948181

    申请日：2010-11-17

    申请人： Ross Hartley Kenyon ,  Adam Rasheed ,  Paul Whitson Dom, Jr. ,  Mark Joseph Pombles

    发明人： Ross Hartley Kenyon ,  Adam Rasheed ,  Paul Whitson Dom, Jr. ,  Mark Joseph Pombles

    IPC分类号： F02C5/00 ,  F02C7/20 ,  F23R7/00 ,  F02C5/02

    CPC分类号： F23R7/00 ,  F02C5/02 ,  F05D2260/16 ,  F23D2211/00

    摘要： A pulse detonation combustor including a plurality of nozzles engaged with one another via mating surfaces to support a gas discharge annulus in a circumferential direction. The pulse detonation combustor also including multiple pulse detonation tubes extending for the nozzles and a plurality of thermal expansion control joints coupled to the plurality of pulse detonation tubes. Each of the plurality of thermal expansion control joints is configured to facilitate independent thermal growth of each of the plurality of pulse detonation tubes. The thermal expansion control joints may be configured as a bellows expansion joint or a sliding expansion joint.

    摘要翻译： 一种脉冲爆震燃烧器，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排气环。 脉冲爆震燃烧器还包括为喷嘴延伸的多个脉冲爆管和连接到多个脉冲爆管的多个热膨胀控制接头。 多个热膨胀控制接头中的每一个构造成促进多个脉冲爆管中的每一个独立的热生长。 热膨胀控制接头可以构造为波纹管膨胀接头或滑动膨胀接头。

    Detecting ice buildup on an aircraft engine and actuating the turbofan exit nozzle to break the ice
    5.
    发明授权
    Detecting ice buildup on an aircraft engine and actuating the turbofan exit nozzle to break the ice 有权
    检测飞机发动机上的积冰并启动涡轮风扇出口喷嘴以打破冰块

    公开(公告)号：US08209950B2

    公开(公告)日：2012-07-03

    申请号：US12441587

    申请日：2006-10-12

    申请人： Ashok K. Jain ,  Michael Winter

    发明人： Ashok K. Jain ,  Michael Winter

    IPC分类号： F02G3/00

    CPC分类号： F02K1/16 ,  B64D15/16 ,  B64D29/00 ,  F02C7/047 ,  F02K1/06 ,  F05D2260/16 ,  F05D2260/80 ,  F05D2270/44

    摘要： A turbofan engine deicing system includes a core nacelle (12) housing a turbine. A turbofan (20) is arranged upstream from the core nacelle. A controller (50) manipulates the turbofan in response to detecting an icing condition for avoiding undesired ice buildup on the turbofan engine (10) and nacelle parts. In one example, a variable area nozzle (40) is actuated to generate pressure pulses or a surge condition to break up any ice buildup. The icing condition can be determined by at least one sensor (52) and/or predicted based upon icing conditions schedules.

    摘要翻译： 涡轮风扇发动机除冰系统包括容纳涡轮的核心机舱（12）。 涡轮风扇（20）布置在核心机舱的上游。 控制器（50）响应于检测到结冰条件来操纵涡扇风扇，以避免涡轮风扇发动机（10）和机舱部件上的不期望的积冰。 在一个示例中，致动可变区域喷嘴（40）以产生压力脉冲或喘振状况以分解任何积冰。 结冰条件可以由至少一个传感器（52）确定和/或基于结冰条件计划预测。

    Control system for a land-based simple cycle hybrid engine for power generation
    6.
    发明申请
    Control system for a land-based simple cycle hybrid engine for power generation 审中-公开
    用于发电的陆基简单循环混合动力发动机的控制系统

    公开(公告)号：US20100154380A1

    公开(公告)日：2010-06-24

    申请号：US12317350

    申请日：2008-12-22

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

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

    IPC分类号： F02C9/48 ,  F02C9/28

    CPC分类号： F02C5/10 ,  F02C9/28 ,  F05D2260/16 ,  F05D2270/05 ,  F05D2270/304 ,  F23R7/00

    摘要： 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.

    摘要翻译： 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。

    Magnetohydrodynamic flow control for pulse detonation engines
    7.
    发明申请
    Magnetohydrodynamic flow control for pulse detonation engines 有权

    公开(公告)号：US20020088219A1

    公开(公告)日：2002-07-11

    申请号：US09756895

    申请日：2001-01-09

    发明人： Gregory Vincent Meholic ,  William Randolph Stowell

    IPC分类号： F02K007/02

    CPC分类号： F03H1/00 ,  F02K7/02 ,  F02K7/06 ,  F05D2260/16

    摘要： Flow control in pulse detonation engines is accomplished using magnetohydrodynamic principles. The pulse detonation engine includes a tube having an open forward end and an open aft end and a fuel-air inlet formed in the tube at the forward end. An igniter is disposed in the tube at a location intermediate the forward end and the aft end. A magnetohydrodynamic flow control system is located between the igniter and the fuel-air inlet for controlling detonation in the tube forward of the igniter. The magnetohydrodynamic flow control system utilizes magnetic and electric fields forward of the igniter to dissipate or at least reduce the ignition potential of the forward traveling detonation flame front.

    Pulsation valve
    8.
    发明授权
    Pulsation valve 失效
    脉动阀

    公开(公告)号：US4581887A

    公开(公告)日：1986-04-15

    申请号：US662485

    申请日：1984-10-19

    申请人： Charles E. Scheffler ,  Richard E. McClelland

    发明人： Charles E. Scheffler ,  Richard E. McClelland

    IPC分类号： F02C7/18 ,  F02C7/12

    CPC分类号： F02C7/18 ,  F05D2260/16

    摘要： A valve mechanism for delivering time-spaced pulses of coolant air to coog passages within a turbine engine. The mechanism is designed for varying the pulse frequency to ascertain the affect that pulse frequency variations have on the cooling effect. The valve mechanism is manufacturable at relatively low cost, using standard shelf components and easily machined parts.

    摘要翻译： 一种阀机构，用于将冷却剂空气的时间间隔脉冲输送到涡轮发动机内的冷却通道。 该机制设计用于改变脉冲频率，以确定脉冲频率变化对冷却效果的影响。 阀门机构可以以相对较低的成本制造，使用标准货架部件和易加工零件。

    Plasma flow control inlet particle separator system
    9.
    发明授权
    Plasma flow control inlet particle separator system 有权

    公开(公告)号：US09638103B2

    公开(公告)日：2017-05-02

    申请号：US13951592

    申请日：2013-07-26

    申请人： HONEYWELL INTERNATIONAL INC.

    发明人： Jeff Howe ,  Nick Nolcheff ,  Harry Lester Kington

    IPC分类号： F02C7/052

    CPC分类号： F02C7/052 ,  F05D2250/71 ,  F05D2260/16 ,  F05D2270/172

    摘要： An inlet particle separator system for an engine includes a hub section, a shroud section, a splitter, and a plasma flow control actuator. The shroud section surrounds at least a portion of the hub section and is spaced apart therefrom to define a passageway having an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the passageway into a scavenge flow path and an engine flow path. The plasma flow control actuator is coupled to the hub section and is disposed between the air inlet and the splitter.

    Vortex cannon with enhanced ring vortex generation
    10.
    发明授权
    Vortex cannon with enhanced ring vortex generation 有权
    涡旋炮与增强的环涡生成

    公开(公告)号：US09217392B2

    公开(公告)日：2015-12-22

    申请号：US13316704

    申请日：2011-12-12

    申请人： Curtis E. Graber

    发明人： Curtis E. Graber

    IPC分类号： F02K7/02 ,  F02K9/97 ,  F41H13/00 ,  A01G13/08

    CPC分类号： F02K7/02 ,  A01G13/08 ,  F02K9/97 ,  F05D2260/16 ,  F41H13/0043

    摘要： A vortex cannon based on pulse detonation engine comprises a combustion chamber, a fuel source, an oxidizer source, a purge gas source, a valve allowing delivery of fuel from the fuel source to the combustion chamber, a valve allowing deliver of either oxidizer or purge gas from the oxidizer and purge gas sources to the combustion chamber, an ignition source for the combustion chamber for initiating detonation of fuel and oxidizer, and a conical barrel outlet from the combustion chamber. The combustion chamber is configured for control over the detonation front. A control system provides for varying the rate and quantity of fuel and oxidizer injected to the combustion chamber for varying the frequency and strength of pulse generation. Ring vortices may be generated either in single pulses or at high rates of fire which maintain a consistent track.

    摘要翻译： 基于脉冲爆震发动机的涡流炮包括燃烧室，燃料源，氧化剂源，净化气体源，允许燃料从燃料源输送到燃烧室的阀，允许输送氧化剂或吹扫 来自氧化剂和净化气体源的气体到达燃烧室，用于燃烧室的点燃源，用于引发燃料和氧化剂的爆震，以及来自燃烧室的锥形出口。 燃烧室被配置为控制爆震前部。 控制系统提供改变喷射到燃烧室的燃料和氧化剂的速率和数量，以改变脉冲产生的频率和强度。 环形涡旋可以以单脉冲或高速率的火焰产生，其保持一致的轨迹。