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    Dual ignition system for a gas turbine engine
    1.
    发明申请
    Dual ignition system for a gas turbine engine 有权

    公开(公告)号：US20060037326A1

    公开(公告)日：2006-02-23

    申请号：US10922471

    申请日：2004-08-20

    Applicant: Michael Mehrer ,  Daih-Yeou Chen

    Inventor： Michael Mehrer ,  Daih-Yeou Chen

    IPC: F02C7/264

    CPC classification number: F02P15/08 ,  F02C7/264 ,  F02P15/003 ,  F23N2027/02 ,  F23N2041/20

    Abstract: A dual channel ignition circuit (Channel A and a Channel B). In a start sequence in which a successful ignition event occurs, an exciter controller first energizes only a primary ignition channel (Channel A). Once the exciter controller recognizes a success light-off, the alternate channel (Channel B) will also then be excited as the gas turbine engine is accelerated to a self-sustaining speed. The exciter controller will then switch the primary alternative designation of the channels for the next start attempt. In a start sequence in which an unsuccessful ignition event occurs, the exciter controller sets a fail-to-start on the primary ignition channel on a failure to start A/B counter such that a failed ignition channel is diagnosed without dedicated electronic diagnostic circuits while still attempting to excite both circuits to enhance the dependability of a successful engine light-off.

    Scalable pyrospin combustor
    3.
    发明申请
    Scalable pyrospin combustor 审中-公开
    可扩展的火焰燃烧器

    公开(公告)号：US20090199563A1

    公开(公告)日：2009-08-13

    申请号：US12069107

    申请日：2008-02-07

    Applicant: Daih-Yeou Chen

    Inventor： Daih-Yeou Chen

    IPC: F23R3/20 ,  F02C7/22 ,  F02C7/12

    CPC classification number: F23R3/52 ,  F02C7/222 ,  F23R3/06 ,  F23R2900/03041 ,  Y02T50/67 ,  Y02T50/675

    Abstract: An axial-flow pyrospin combustor comprises inner and outer combustor liners and a plurality of pyrospin effusion holes. The inner liner is coaxially mounted inside the outer liner, about a central combustor axis. The pyrospin effusion holes are formed in at least one of the outer combustor liner and the inner combustor liner. Each of the pyrospin effusion holes has a down angle and a back angle, which control a global swirl flow about the central axis, and promote film cooling without detachment.

    Abstract translation: 轴流式火焰喷射燃烧器包括内部和外部燃烧器衬套和多个焦油喷射孔。 内衬层围绕中心燃烧器轴线同轴地安装在外衬里内。 火焰喷射孔形成在外燃烧器衬套和内燃烧器衬套中的至少一个中。 每个焦油喷射孔具有向下的角度和后角，其控制围绕中心轴线的全局旋转流动，并且促进薄膜冷却而不脱离。

    Dual ignition system for a gas turbine engine
    4.
    发明授权
    Dual ignition system for a gas turbine engine 有权
    燃气涡轮发动机的双重点火系统

    公开(公告)号：US07509812B2

    公开(公告)日：2009-03-31

    申请号：US10922471

    申请日：2004-08-20

    Applicant: Michael E. Mehrer ,  Daih-Yeou Chen

    Inventor： Michael E. Mehrer ,  Daih-Yeou Chen

    IPC: F02C7/22

    CPC classification number: F02P15/08 ,  F02C7/264 ,  F02P15/003 ,  F23N2027/02 ,  F23N2041/20

    Abstract: A dual channel ignition circuit (Channel A and a Channel B). In a start sequence in which a successful ignition event occurs, an exciter controller first energizes only a primary ignition channel (Channel A). Once the exciter controller recognizes a success light-off, the alternate channel (Channel B) will also then be excited as the gas turbine engine is accelerated to a self-sustaining speed. The exciter controller will then switch the primary alternative designation of the channels for the next start attempt. In a start sequence in which an unsuccessful ignition event occurs, the exciter controller sets a fail-to-start on the primary ignition channel on a failure to start A/B counter such that a failed ignition channel is diagnosed without dedicated electronic diagnostic circuits while still attempting to excite both circuits to enhance the dependability of a successful engine light-off.

    Abstract translation: 双通道点火电路（通道A和通道B）。 在其中发生成功的点火事件的启动顺序中，励磁机控制器首先仅激励初级点火通道（通道A）。 一旦励磁机控制器识别到成功点亮，则随着燃气涡轮发动机加速到自持速度，备用通道（通道B）也将被激励。 然后，激励器控制器将切换下一次启动尝试的通道的主要替代指定。 在发生不成功的点火事件的启动顺序中，激励器控制器在启动A / B计数器的故障时在初级点火通道上设置故障启动，使得在没有专用电子诊断电路的情况下诊断故障点火通道，而 仍然试图激励两个电路，以增强成功引擎熄灭的可靠性。

    Active thrust management system
    5.
    发明授权
    Active thrust management system 有权
    主动推力管理系统

    公开(公告)号：US07559696B2

    公开(公告)日：2009-07-14

    申请号：US10929803

    申请日：2004-08-30

    Applicant: Carlos Oncina ,  Michael E. Mehrer ,  Bing Tong ,  Pete Suttie ,  Daih-Yeou Chen ,  William Dornfield

    Inventor： Carlos Oncina ,  Michael E. Mehrer ,  Bing Tong ,  Pete Suttie ,  Daih-Yeou Chen ,  William Dornfield

    IPC: F16C32/06

    CPC classification number: F01D3/04 ,  F16C39/04

    Abstract: An active thrust management system varies pressure responsive to changes in rotor assembly thrust to maintain a desired position. The system includes a bearing supporting rotation of a rotor assembly within a pressurizing chamber. The rotor assembly is supported on a cushion of air generated between the bearing and the rotor assembly. Pressure within a cavity adjacent the rotor assembly opposes a thrust force to maintain a desired position of the rotor assembly. Modulating airflow into the pressurizing chamber adjacent the rotor assembly compensates for changes in the thrust generated by the rotor assembly to maintain the desired rotor assembly position.

    Abstract translation: 主动推力管理系统根据转子组件推力的变化来改变压力以保持期望的位置。 该系统包括支撑转子组件在加压室内的旋转的轴承。 转子组件支撑在轴承和转子组件之间产生的空气衬垫上。 与转子组件相邻的空腔内的压力抵抗推力以保持转子组件的期望位置。 调节与转子组件相邻的加压室中的气流补偿由转子组件产生的推力的变化，以维持所需的转子组件位置。

    Lean-staged pyrospin combustor
    6.
    发明授权
    Lean-staged pyrospin combustor 有权
    精馏级焦油燃烧器

    公开(公告)号：US07302801B2

    公开(公告)日：2007-12-04

    申请号：US10827573

    申请日：2004-04-19

    Applicant: Daih-Yeou Chen

    Inventor： Daih-Yeou Chen

    IPC: F23R3/34

    CPC classification number: F23R3/54 ,  F23D2900/00014 ,  F23R3/34

    Abstract: A combustor assembly includes a combustor chamber having a primary and intermediate zone that provides for reduced flame temperatures. The combustor assembly includes first and second pluralities of injectors. The first plurality of injectors introduces fuel to a primary zone. A second plurality of injectors introduces fuel to an intermediate zone. During operation between initial start up and before the introduction of engine load, fuel is introduced into the primary zone only by the first plurality of injectors. Once engine load is applied to the engine, fuel is introduced into the intermediate zone by the second plurality of injectors. Introduction of additional volume of fuel allows the fuel-air ratio to remain constant regardless of engine operating conditions. The constant fuel-air ratio is maintained at a desired rate to lower flame temperatures and reduce nitrous oxide emissions.

    Abstract translation: 燃烧器组件包括具有主要和中间区域的燃烧器室，其提供降低的火焰温度。 燃烧器组件包括第一和第二多个喷射器。 第一组多个喷射器将燃料引入主区域。 第二组多个喷射器将燃料引入中间区域。 在初始启动之前和引入发动机负载之前的操作期间，燃料仅由第一多个喷射器引入主区域。 一旦发动机负载被施加到发动机，燃料通过第二多个喷射器被引入中间区域。 引入附加体积的燃料允许燃料 - 空气比保持恒定，不管发动机的运行条件如何。 恒定的燃料空气比保持在期望的速率以降低火焰温度并减少一氧化二氮排放。

    Lean-staged pyrospin combustor
    8.
    发明申请
    Lean-staged pyrospin combustor 有权
    精馏级焦油燃烧器

    公开(公告)号：US20050229604A1

    公开(公告)日：2005-10-20

    申请号：US10827573

    申请日：2004-04-19

    Applicant: Daih-Yeou Chen

    Inventor： Daih-Yeou Chen

    IPC: F23R3/34 ,  F23R3/54

    CPC classification number: F23R3/54 ,  F23D2900/00014 ,  F23R3/34

    Abstract: A combustor assembly includes a combustor chamber having a primary and intermediate zone that provides for reduced flame temperatures. The combustor assembly includes first and second pluralities of injectors. The first plurality of injectors introduces fuel to a primary zone. A second plurality of injectors introduces fuel to an intermediate zone. During operation between initial start up and before the introduction of engine load, fuel is introduced into the primary zone only by the first plurality of injectors. Once engine load is applied to the engine, fuel is introduced into the intermediate zone by the second plurality of injectors. Introduction of additional volume of fuel allows the fuel-air ratio to remain constant regardless of engine operating conditions. The constant fuel-air ratio is maintained at a desired rate to lower flame temperatures and reduce nitrous oxide emissions.

    Abstract translation: 燃烧器组件包括具有主要和中间区域的燃烧器室，其提供降低的火焰温度。 燃烧器组件包括第一和第二多个喷射器。 第一组多个喷射器将燃料引入主区域。 第二组多个喷射器将燃料引入中间区域。 在初始启动之前和引入发动机负载之前的操作期间，燃料仅由第一多个喷射器引入主区域。 一旦发动机负载被施加到发动机，燃料通过第二多个喷射器被引入中间区域。 引入附加体积的燃料允许燃料 - 空气比保持恒定，不管发动机的运行条件如何。 恒定的燃料空气比保持在期望的速率以降低火焰温度并减少一氧化二氮排放。

    GAS TURBINE ENGINE FUEL INJECTOR
    9.
    发明申请
    GAS TURBINE ENGINE FUEL INJECTOR 审中-公开
    燃气涡轮发动机燃油喷射器

    公开(公告)号：US20110072823A1

    公开(公告)日：2011-03-31

    申请号：US12570103

    申请日：2009-09-30

    Applicant: Daih-Yeou Chen ,  Xiaolan Hu

    Inventor： Daih-Yeou Chen ,  Xiaolan Hu

    IPC: F02C7/22

    CPC classification number: F02C7/222 ,  F23R3/28 ,  F23R3/50

    Abstract: An example gas turbine engine fuel injector nozzle assembly includes a nozzle tip secured relative to a combustion area within a gas turbine engine. The nozzle establishes a plurality of first apertures that are configured to communicate a fuel to the combustion area. The nozzle establishes at least one second aperture that is configured to communicate a fluid to the combustion area. The fluid is different than the fuel. An example method of providing fuel to a combustion area within a gas turbine engine includes communicating a fuel through a first aperture in a nozzle tip to a combustion area in a gas turbine engine. The nozzle tip establishes an axis. The method also includes influencing fuel moving from the nozzle tip using a fluid directed through a second aperture in the nozzle tip. The fluid is different than the fuel. A portion of the second aperture is radially closer to the axis than the first aperture.

    Abstract translation: 示例性燃气涡轮发动机燃料喷射器喷嘴组件包括相对于燃气涡轮发动机内的燃烧区域固定的喷嘴尖端。 喷嘴建立多个第一孔，其构造成将燃料传送到燃烧区。 喷嘴建立至少一个第二孔，其构造成将流体传送到燃烧区。 流体与燃料不同。 向燃气涡轮发动机内的燃烧区域提供燃料的示例性方法包括将燃料通过喷嘴尖端中的第一孔连通到燃气涡轮发动机的燃烧区域。 喷嘴尖端建立一个轴。 该方法还包括影响使用引导通过喷嘴尖端中的第二孔的流体从喷嘴尖端移动的燃料。 流体与燃料不同。 第二孔的一部分比第一孔径向更靠近轴线。

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