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40 条记录 (耗时 0.027 秒)

    MULTI-SIDED DIFFUSER FOR A VENTURI IN A FUEL INJECTOR FOR A GAS TURBINE
    22.
    发明申请
    MULTI-SIDED DIFFUSER FOR A VENTURI IN A FUEL INJECTOR FOR A GAS TURBINE 失效
    用于燃气涡轮机燃油喷射器的多功能搅拌器

    公开(公告)号：US20060000218A1

    公开(公告)日：2006-01-05

    申请号：US10879102

    申请日：2004-06-30

    申请人： Constantin Dinu ,  Iris Hu ,  James Storey

    发明人： Constantin Dinu ,  Iris Hu ,  James Storey

    IPC分类号： F23R3/28

    CPC分类号： F23R3/34 ,  F23R3/286 ,  F23R3/40

    摘要： A combustor for a gas turbine includes a main fuel injector for receiving compressor discharge air and mixing the air with fuel for flow to a downstream catalytic section. The main fuel injector includes an array of venturis each having an inlet, a throat and a diffuser. A main fuel supply plenum between forward and aft plates supplies fuel to secondary annular plenums having openings for supplying fuel into the inlets of the venturis upstream of the throats. Each diffuser transitions from a circular cross-section at the throat to multiple discrete angularly related side walls at the diffuser exit. Gaps between circumferentially and radially spaced diffusers at their exits are eliminated. With this arrangement, uniform flow distribution of the fuel/air, velocity and temperature is provided at the catalyst inlet.

    摘要翻译： 用于燃气轮机的燃烧器包括主燃料喷射器，用于接收压缩机排放空气并将空气与用于流动的燃料混合到下游催化部分。 主燃料喷射器包括每个具有入口，喉部和扩散器的孔的阵列。 前后板之间的主要燃料供应气室将燃料供给到具有用于将燃料供应到喉部上游的通风口的入口的开口的次级环形增压室。 每个扩散器从喉部的圆形横截面到扩散器出口处的多个离散的角度相关的侧壁。 在其出口处的周向和径向间隔的扩散器之间的间隙被消除。 通过这种布置，在催化剂入口处提供了燃料/空气，速度和温度的均匀流量分布。

    Control systems and method for controlling a load point of a gas turbine engine
    24.
    发明授权
    Control systems and method for controlling a load point of a gas turbine engine 有权

    公开(公告)号：US08240152B2

    公开(公告)日：2012-08-14

    申请号：US13218712

    申请日：2011-08-26

    申请人： Constantin Dinu

    发明人： Constantin Dinu

    IPC分类号： F02C9/00

    CPC分类号： F02C9/54 ,  F02K1/16 ,  F05D2270/082 ,  F05D2270/0831 ,  F05D2270/3013 ,  F05D2270/303

    摘要： Control systems and a method for controlling a load point of a gas turbine engine are provided. A control system includes a controller that receives a temperature signal and a pressure signal associated with exhaust gases from the gas turbine engine. The controller is further configured to generate the fuel control signal. The controller is further configured to generate an actuator control signal such that flow restriction member is moved from the first operational position to the second operational position to restrict the flow path such that the exhaust gases have a temperature level within a desired turndown temperature range, the pressure level in the exhaust gases is less than a threshold pressure level, and the load point of the gas turbine engine is adjusted to toward a target load point.

    Turbine fuel nozzle having heat control
    25.
    发明授权
    Turbine fuel nozzle having heat control 失效
    涡轮燃油喷嘴具有热控制

    公开(公告)号：US08186165B2

    公开(公告)日：2012-05-29

    申请号：US12405195

    申请日：2009-03-16

    申请人： Constantin Dinu

    发明人： Constantin Dinu

    IPC分类号： F02C1/00

    CPC分类号： F23R3/32 ,  F23R3/30

    摘要： In one embodiment, a system includes a turbine engine fuel nozzle having an air path, a fuel path, and a surface along the air path. The fuel path may be directed toward the surface. The turbine engine fuel nozzle also may include a heating element configured to heat the surface.

    摘要翻译： 在一个实施例中，系统包括具有空气路径，燃料路径和沿着空气路径的表面的涡轮发动机燃料喷嘴。 燃料路径可以指向表面。 涡轮发动机燃料喷嘴还可以包括构造成加热表面的加热元件。

    Re-heat combustor for a gas turbine engine
    26.
    发明授权
    Re-heat combustor for a gas turbine engine 失效
    燃气轮机的再加热燃烧器

    公开(公告)号：US08006477B2

    公开(公告)日：2011-08-30

    申请号：US12060481

    申请日：2008-04-01

    申请人： Constantin Dinu

    发明人： Constantin Dinu

    IPC分类号： F02C1/06

    CPC分类号： F23R3/34 ,  F02C3/14 ,  F02C6/003 ,  F05D2250/71 ,  F23R3/04

    摘要： A turbine engine includes a turbine section having a first turbine portion and a second turbine portion arranged along a central axis. A re-heat combustor is arranged between the first and second turbine portions. The re-heat combustor includes a combustion duct having a curvilinear flow portion. The curvilinear flow portion provides an increased residence time of combustion products passing through the re-heat combustor.

    摘要翻译： 涡轮发动机包括具有沿中心轴线布置的第一涡轮机部分和第二涡轮机部分的涡轮部分。 在第一涡轮部分和第二涡轮部分之间布置有再热燃烧器。 再热燃烧器包括具有曲线流动部分的燃烧通道。 曲线流动部分提供通过再热燃烧器的燃烧产物的停留时间增加。

    METHOD AND SYSTEM FOR SEALING AN ANNULUS
    27.
    发明申请
    METHOD AND SYSTEM FOR SEALING AN ANNULUS 有权
    用于密封ANNULUS的方法和系统

    公开(公告)号：US20100288474A1

    公开(公告)日：2010-11-18

    申请号：US12464579

    申请日：2009-05-12

    申请人： Constantin Dinu ,  James Michael Storey ,  Aaron John Avagliano ,  Douglas S. Byrd ,  Shaoping Shi ,  Judeth Brannon Corry ,  Allyson Joy Jimenez Huyke

    发明人： Constantin Dinu ,  James Michael Storey ,  Aaron John Avagliano ,  Douglas S. Byrd ,  Shaoping Shi ,  Judeth Brannon Corry ,  Allyson Joy Jimenez Huyke

    IPC分类号： F28C3/06 ,  F16J15/447 ,  C10K1/04 ,  F28D7/00

    CPC分类号： F01K23/068 ,  Y02E20/16 ,  Y02E20/18

    摘要： A method and systems for a purged seal for an annular space are provided. The purged seal includes a first baffle element that extends from an inner surface of the annular space into the annular space at an oblique angle and a second baffle element that extends from an outer surface of the annular space above the first baffle element in a direction opposite gravity flow into the annular space wherein the second baffle element extends at an oblique angle. The system also includes a third baffle element that extends from the inner surface above the first baffle element in a direction of gravity flow into the annular space wherein the third baffle element extends into the annular space at an oblique angle with respect to the inner surface and wherein a distal end of the third baffle element is positioned proximate a distal end of the second baffle element.

    摘要翻译： 提供了一种用于环形空间的清洗密封件的方法和系统。 清除的密封件包括第一挡板元件，其从环形空间的内表面以倾斜角延伸到环形空间中，第二挡板元件从第一挡板元件上方的环形空间的外表面沿相反方向延伸 重力流入环形空间，其中第二挡板元件以倾斜角延伸。 该系统还包括第三挡板元件，其从第一挡板元件上方的内表面沿着重力流向环形空间的方向延伸，其中第三挡板元件以相对于内表面倾斜的角度延伸到环形空间中， 其中所述第三挡板元件的远端位于所述第二挡板元件的远端附近。

    APPARATUS HAVING THERMALLY ISOLATED VENTURI TUBE JOINTS
    29.
    发明申请
    APPARATUS HAVING THERMALLY ISOLATED VENTURI TUBE JOINTS 失效
    具有热隔离VENTURI管接头的装置

    公开(公告)号：US20060213178A1

    公开(公告)日：2006-09-28

    申请号：US10907248

    申请日：2005-03-25

    申请人： James Storey ,  Constantin Dinu

    发明人： James Storey ,  Constantin Dinu

    IPC分类号： F02C3/22

    CPC分类号： F02C3/22 ,  F23R3/286 ,  F23R3/40

    摘要： A gas fuel injector includes a first header plate, a second header plate, and a plurality of venturi tubes. The second header plate is spaced downstream from the first header plate. The plurality of venturi tubes is sealably secured to the first and second header plates. Each venturi tube of the plurality of venturi tubes is defined by a plurality of fixable components.

    摘要翻译： 气体燃料喷射器包括第一集管板，第二集管板和多个文氏管。 第二集管板与第一集管板的下游间隔开。 多个文丘里管可密封地固定到第一和第二集管板。 多个文丘里管的每个文氏管由多个可固定部件限定。

    MULTI-VENTURI TUBE FUEL INJECTOR FOR A GAS TURBINE COMBUSTOR
    30.
    发明申请
    MULTI-VENTURI TUBE FUEL INJECTOR FOR A GAS TURBINE COMBUSTOR 失效
    多功能涡轮机燃油喷射器

    公开(公告)号：US20060000217A1

    公开(公告)日：2006-01-05

    申请号：US10879059

    申请日：2004-06-30

    申请人： Constantin Dinu

    发明人： Constantin Dinu

    IPC分类号： F23R3/28

    CPC分类号： F23R3/40 ,  F23R3/286 ,  F23R3/34

    摘要： A combustor for a gas turbine includes a main fuel injector for receiving compressor discharge air and mixing the air with fuel for flow to a downstream catalytic section. The main fuel injector includes an array of venturis each having an inlet, a throat and a diffuser. A main fuel supply plenum between forward and aft plates supplies fuel to secondary annular plenums having openings for supplying fuel into the inlet of the venturis upstream of the throat. The diffusers transition from a circular cross-section at the throat to multiple discrete angularly related side walls at the diffuser exits without substantial gaps therebetween. With this arrangement, uniform flow distribution of the fuel/air, velocity and temperature is provided at the catalyst inlet.

    摘要翻译： 用于燃气轮机的燃烧器包括主燃料喷射器，用于接收压缩机排放空气并将空气与用于流动的燃料混合到下游催化部分。 主燃料喷射器包括每个具有入口，喉部和扩散器的孔的阵列。 前后板之间的主要燃料供应气室将燃料供给到具有用于将燃料供应到喉部上游的通风口的入口的开口的次级环形增压室。 扩散器从喉部处的圆形横截面转变到扩散器出口处的多个离散的有角度的相关侧壁，而在它们之间没有实质的间隙。 通过这种布置，在催化剂入口处提供了燃料/空气，速度和温度的均匀流量分布。