公开(公告)号：US20070256418A1

公开(公告)日：2007-11-08

申请号：US11418613

申请日：2006-05-05

申请人： Mark Mueller ,  Keith McManus ,  Zhongtao Dai ,  Michael Vermeersch ,  Venkatraman Ananthakrishnanlyer ,  Timothy Held ,  Jun Xu

发明人： Mark Mueller ,  Keith McManus ,  Zhongtao Dai ,  Michael Vermeersch ,  Venkatraman Ananthakrishnanlyer ,  Timothy Held ,  Jun Xu

IPC分类号： F02C1/00

CPC分类号： F23R3/00 ,  F23R2900/00017

摘要： A method for assembling a gas turbine engine combustor is provided. The method includes providing a heat shield defined by a perimeter. The perimeter includes a radially inner edge, a radially outer edge, an axially inner edge, an axially outer edge, and an opening that extends from an upstream side of the heat shield to a downstream side of the heat shield. The method further includes coupling the heat shield to a domeplate such that the perimeter of the heat shield is positioned a distance downstream from an edge of the heat shield defining the opening. The method additionally includes coupling at least one fuel injector to the domeplate such that a portion of the fuel injector extends through the heat shield opening.

摘要翻译： 提供了一种用于组装燃气涡轮发动机燃烧器的方法。 该方法包括提供由周边限定的热屏蔽。 周边包括径向内边缘，径向外边缘，轴向内边缘，轴向外边缘和从隔热板的上游侧延伸到隔热罩的下游侧的开口。 该方法还包括将隔热罩联接到三脚架，使得隔热罩的周边定位在限定开口的隔热板的边缘的下游的距离处。 该方法另外包括将至少一个燃料喷射器联接到多孔板，使得燃料喷射器的一部分延伸穿过隔热开口。

公开(公告)号：US20050279083A1

公开(公告)日：2005-12-22

申请号：US10870877

申请日：2004-06-18

申请人： Keith McManus ,  Anthony Dean ,  Venkat Tangirala

发明人： Keith McManus ,  Anthony Dean ,  Venkat Tangirala

IPC分类号： F02K7/02

CPC分类号： F02K7/04 ,  F23C15/00 ,  F23L7/007 ,  F23R7/00 ,  Y02E20/344

摘要： In the present invention, at least one detonation initiator is positioned downstream of a main combustion chamber, with the initiator oriented such that it projects a detonation initiation wave forward into the main combustion chamber. The main combustion chamber contains a wave reflection surface. The detonation initiation wave is directed into the main combustion chamber and at the wave reflector surface and is used to initiate, or assist in the initiation of, a fuel and gas mixture in the main combustion chamber. The fuel and gas mixture is detonated, creating a high temperature and high pressure wave that is directed out of the main combustion chamber.

摘要翻译： 在本发明中，至少一个引爆引发剂位于主燃烧室的下游，其中起爆器被定向为使得爆炸起始波向前推入主燃烧室。 主燃烧室包含波反射面。 引爆起始波被引导到主燃烧室和波浪反射器表面，并用于启动或协助起动主燃烧室中的燃料和气体混合物。 燃料和气体混合物被引爆，产生高温和高压波，该高压和高压波被引导出主燃烧室。

公开(公告)号：US20120164589A1

公开(公告)日：2012-06-28

申请号：US12975742

申请日：2010-12-22

申请人： Shawn Wehe ,  Joel Haynes ,  Keith McManus ,  Gregory Knott ,  Douglas L. Washburn

发明人： Shawn Wehe ,  Joel Haynes ,  Keith McManus ,  Gregory Knott ,  Douglas L. Washburn

IPC分类号： F23C99/00 ,  G01M15/14

CPC分类号： G01N21/766 ,  F02D35/022 ,  F23N5/082 ,  F23N2029/16 ,  G01J3/0218

摘要： The present application provides an optical probe system for use with a combustion flame in a combustion chamber. The optical probe system may include a number of optical probes fixedly attached about the combustion chamber and positioned such that the optical probes collect light generated by the combustion flame in a field of view of each of the optical probes. One or more components external to the combustion chamber may produce and analyze signals indicative of the light generated by the combustion flame in the field of view of each of the optical probes.

摘要翻译： 本申请提供了一种与燃烧室中的燃烧火焰一起使用的光学探针系统。 光学探针系统可以包括固定地安装在燃烧室周围的多个光学探针，并且定位成使得光学探针在每个光学探针的视野中收集由燃烧火焰产生的光。 在燃烧室外部的一个或多个组件可以产生和分析指示在每个光学探针的视场中由燃烧火焰产生的光的信号。

公开(公告)号：US20070186556A1

公开(公告)日：2007-08-16

申请号：US11352773

申请日：2006-02-13

申请人： Adam Rasheed ,  Keith McManus ,  Anthony Dean

发明人： Adam Rasheed ,  Keith McManus ,  Anthony Dean

IPC分类号： F23R7/00

CPC分类号： F23R7/00

摘要： A method for operating a pulse detonation engine, wherein the method includes channeling air flow from a pulse detonation combustor into a flow mixer having an inlet portion, an outlet portion, and a body portion extending therebetween. The method also includes channeling ambient air past the flow mixer and mixing the air flow discharged from the pulse detonation combustor with the ambient air flow such that a combined flow is generated from the flow mixer that has less flow variations than the air flow discharged from the pulse detonation combustor.

摘要翻译： 一种用于操作脉冲爆震引擎的方法，其中所述方法包括将来自脉冲爆震燃烧器的空气流引导到具有入口部分，出口部分和在其间延伸的主体部分的流动混合器。 该方法还包括将环境空气引导通过流动混合器并将从脉冲爆震燃烧器排放的空气流与环境空气流混合，使得从流动混合器产生的组合流量具有比从 脉冲爆震燃烧器。

公开(公告)号：US20050279078A1

公开(公告)日：2005-12-22

申请号：US10870898

申请日：2004-06-18

申请人： Anthony Dean ,  Keith McManus ,  Venkat Tangirala

发明人： Anthony Dean ,  Keith McManus ,  Venkat Tangirala

IPC分类号： F02C5/00 ,  F02K7/02 ,  F23R7/00

CPC分类号： F02C5/00 ,  F02K7/02 ,  F23R7/00

摘要： The present invention is a pulse detonation combustion system, having a plurality of detonation initiation devices coupled to a main combustion chamber, where each of the detonation initiation devices is operating out-of-phase with each other. Each of the detonation initiation devices assists in the initiation of a detonation in the main combustion chamber, out-of-phase from each other such that the operational frequency of the pulse detonation combustion system is related to the number of detonation initiation devices multiplied by the operational frequency of a single detonation initiation device.

摘要翻译： 本发明是一种脉冲爆震燃烧系统，其具有耦合到主燃烧室的多个爆震启动装置，其中每个爆震启动装置彼此不同相运行。 每个爆震启动装置有助于在主燃烧室中引起爆震，彼此不相位，使得脉冲爆震燃烧系统的操作频率与爆震开始装置的数量相乘 单个引爆装置的工作频率。

公开(公告)号：US06820431B2

公开(公告)日：2004-11-23

申请号：US10284881

申请日：2002-10-31

申请人： Keith McManus ,  Simon Sanderson ,  Jeffrey Goldmeer

发明人： Keith McManus ,  Simon Sanderson ,  Jeffrey Goldmeer

IPC分类号： F02C722

CPC分类号： F23R3/28 ,  F23D2210/00 ,  F23M20/00 ,  F23R2900/00014

摘要： A fuel nozzle device suitable for use in a gas turbine engine or the like is provided. The fuel nozzle device includes a fuel line and a plurality of gas orifices disposed at a downstream end of the fuel line, the plurality of gas orifices operable for injecting fuel into an air stream. The acoustic resistance of each of the plurality of gas orifices is chosen to match the acoustic impedance of the fuel line such that the maximum acoustic energy may be transferred between the fuel nozzle device and the combustor, thus enhancing the ability of the fuel nozzle device to control the combustion dynamics of the gas turbine engine system. A fuel injection resonator assembly suitable for use in a gas turbine engine or the like is also provided. The fuel injection resonator assembly includes a plurality of orifices separated by a variable length tube. The area ratio of the plurality of orifices may be adjusted using an automated valve system or the like to modify and/or control the relative flow resistance of the plurality of orifices. The resulting fuel injection resonator assembly acts as a tunable acoustic waveguide operable for delivering fuel to the combustor.