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    Lean direct injection combustion system
    11.
    发明申请
    Lean direct injection combustion system 有权
    精益直喷式燃烧系统

    公开(公告)号：US20090229269A1

    公开(公告)日：2009-09-17

    申请号：US12073939

    申请日：2008-03-12

    申请人： Benjamin Lacy ,  Balachandar Varatharajan ,  Willy Steve Ziminsky ,  Gilbert O. Kraemer ,  Gregory Allen Boardman ,  Ertan Yilmaz ,  Patrick Melton

    发明人： Benjamin Lacy ,  Balachandar Varatharajan ,  Willy Steve Ziminsky ,  Gilbert O. Kraemer ,  Gregory Allen Boardman ,  Ertan Yilmaz ,  Patrick Melton

    IPC分类号： F02C1/00

    CPC分类号： F23R3/28

    摘要： The present invention is directed to a lean direct injection (LDI) combustion system for a gas turbine using a shell and tube heat exchanger concept to construct a shell and tube lean direct injector (“LDI”) for the combustion system. One side of the LDI injector, either the shell side or the tube side, carries an oxidizer, such as air, to the combustor, while the other side of the LDI injector carries fuel to the combustor. Straight or angled holes drilled in an end plate of the combustor allow the fuel to enter the combustor and mix with air being injected into the combustor.

    摘要翻译： 本发明涉及一种用于燃气轮机的精馏直接喷射（LDI）燃烧系统，其使用壳管式热交换器概念来构建用于燃烧系统的壳管式稀燃直喷式喷射器（“LDI”）。 LDI注射器的一侧（外壳侧或管侧）将氧化剂（例如空气）携带到燃烧器，而LDI喷射器的另一侧将燃料运送到燃烧器。 在燃烧器的端板中钻出的直的或成角度的孔允许燃料进入燃烧器并与注入燃烧器的空气混合。

    FUEL BLANKETING BY INERT GAS OR LESS REACTIVE FUEL LAYER TO PREVENT FLAME HOLDING IN PREMIXERS
    15.
    发明申请
    FUEL BLANKETING BY INERT GAS OR LESS REACTIVE FUEL LAYER TO PREVENT FLAME HOLDING IN PREMIXERS 审中-公开
    燃油通过惰性气体或无反应性燃料层进行燃烧以预防火焰燃烧

    公开(公告)号：US20100281876A1

    公开(公告)日：2010-11-11

    申请号：US12435651

    申请日：2009-05-05

    申请人： Abdul Rafey Khan ,  Balachandar Varatharajan ,  Gilbert Otto Kraemer ,  Ertan Yilmaz ,  Benjamin Lacy ,  William David York

    发明人： Abdul Rafey Khan ,  Balachandar Varatharajan ,  Gilbert Otto Kraemer ,  Ertan Yilmaz ,  Benjamin Lacy ,  William David York

    IPC分类号： F02C7/22 ,  F02C3/20

    CPC分类号： F23R3/286 ,  F23C2900/07022 ,  F23L2900/07002 ,  F23L2900/07009

    摘要： A premixer for a gas turbine combustor includes a first passage configured to inject a highly reactive fuel; and a second passage configured to inject an inert gas or a less reactive fuel or a mixture of both. The second passage is configured to form a layer of the inert gas or less reactive fuel or the mixture of both that blankets a layer of the highly reactive fuel. Another premixer includes a plurality of nozzles, each nozzle including a pair of concentric tubes, the pair of concentric tubes including a first tube configured to inject a highly reactive fuel and a second tube surrounding the first tube and configured to dispense an inert gas or a less reactive fuel or a mixture of both that blankets the highly reactive fuel.

    摘要翻译： 燃气轮机燃烧器的预混合器包括：第一通道，其构造成喷射高反应性燃料; 以及构造成喷射惰性气体或较少反应性燃料或二者的混合物的第二通道。 第二通道被配置成形成一层惰性气体或较少的反应性燃料或两者的混合物，这些层覆盖高反应性燃料层。 另一个预混合器包括多个喷嘴，每个喷嘴包括一对同心管，该对同心管包括构造成喷射高反应性燃料的第一管和围绕第一管的第二管，并且构造成分配惰性气体或 较少的反应性燃料或两者的混合物，其覆盖高反应性燃料。

    Internal baffling for fuel injector
    16.
    发明授权
    Internal baffling for fuel injector 有权
    燃油喷射器内部挡板

    公开(公告)号：US08794545B2

    公开(公告)日：2014-08-05

    申请号：US12567022

    申请日：2009-09-25

    申请人： Thomas Edward Johnson ,  Benjamin Lacy ,  Christian Stevenson

    发明人： Thomas Edward Johnson ,  Benjamin Lacy ,  Christian Stevenson

    IPC分类号： F23D11/10

    CPC分类号： F23D14/02 ,  F23C2900/9901 ,  F23D14/78 ,  F23D2214/00 ,  F23R3/286

    摘要： A fuel injector includes a fuel delivery tube; a plurality of pre-mixing tubes, each pre-mixing tube comprising at least one fuel injection hole; an upstream tube support plate that supports upstream ends of the plurality of pre-mixing tubes; a downstream tube support plate that supports downstream ends of the plurality of pre-mixing tubes; an outer wall connecting the upstream tube support plate and the downstream tube support plate and defining a plenum therewith; and a baffle provided in the plenum. The baffle includes a radial portion. A fuel delivered in the upstream direction by the fuel delivery tube is directed radially outwardly in the plenum between the radial portion of the baffle and the downstream tube support plate, then in the downstream direction around an outer edge portion of the radial portion, and then radially inwardly between the radial portion and the upstream tube support plate.

    摘要翻译： 燃料喷射器包括燃料输送管; 多个预混合管，每个预混合管包括至少一个燃料喷射孔; 上游管支撑板，其支撑所述多个预混合管的上游端; 下游管支撑板，其支撑所述多个预混合管的下游端; 连接所述上游管支撑板和所述下游管支撑板并且与所述下游管支撑板连接的外壁; 以及设置在气室中的挡板。 挡板包括径向部分。 通过燃料输送管沿上游方向输送的燃料径向向外指向在挡板的径向部分和下游管支撑板之间的增压室中，然后在径向部分的外边缘部分的下游方向上，然后 在径向部分和上游管支撑板之间径向向内。

    Temperature detection in a gas turbine
    17.
    发明授权
    Temperature detection in a gas turbine 失效
    燃气轮机中的温度检测

    公开(公告)号：US08334749B1

    公开(公告)日：2012-12-18

    申请号：US12568348

    申请日：2009-09-28

    申请人： Benjamin Lacy ,  Gilbert Kraemer ,  Christian Stevenson

    发明人： Benjamin Lacy ,  Gilbert Kraemer ,  Christian Stevenson

    IPC分类号： H01C7/10

    CPC分类号： F01D17/085 ,  G01K3/10 ,  G01K7/02 ,  G01K7/16 ,  G01K13/02 ,  G01K2205/04

    摘要： A temperature detector includes a first metal and a second metal different from the first metal. The first metal includes a plurality of wires and the second metal includes a wire. The plurality of wires of the first metal are connected to the wire of the second metal in parallel junctions. Another temperature detector includes a plurality of resistance temperature detectors. The plurality of resistance temperature detectors are connected at a plurality of junctions. A method of detecting a temperature change of a component of a turbine includes providing a temperature detector include ing a first metal and a second metal different from the first metal connected to each other at a plurality of junctions in contact with the component; and detecting any voltage change at any junction.

    摘要翻译： 温度检测器包括不同于第一金属的第一金属和第二金属。 第一金属包括多根电线，第二金属包括电线。 第一金属的多根导线以平行结连接到第二金属的导线上。 另一温度检测器包括多个电阻温度检测器。 多个电阻温度检测器以多个连接点连接。 一种检测涡轮机部件的温度变化的方法包括提供温度检测器，该温度检测器包括第一金属和不同于第一金属的第二金属，所述第一金属和第二金属在与所述部件接触的多个接合处彼此连接; 并检测任何接点处的任何电压变化。

    Lean direct injection diffusion tip and related method
    18.
    发明授权
    Lean direct injection diffusion tip and related method 有权
    精益直接注射扩散尖及相关方法

    公开(公告)号：US08240150B2

    公开(公告)日：2012-08-14

    申请号：US12222423

    申请日：2008-08-08

    申请人： Balachandar Varatharajan ,  Willy S. Ziminsky ,  John Lipinski ,  Gilbert O. Kraemer ,  Ertan Yilmaz ,  Benjamin Lacy

    发明人： Balachandar Varatharajan ,  Willy S. Ziminsky ,  John Lipinski ,  Gilbert O. Kraemer ,  Ertan Yilmaz ,  Benjamin Lacy

    IPC分类号： F02C1/00 ,  F02G3/00

    CPC分类号： F23R3/14 ,  F23D2900/00008 ,  F23D2900/14004 ,  F23R3/286 ,  F23R3/343

    摘要： A nozzle for a gas turbine combustor includes a first radially outer tube defining a first passage having an inlet and an outlet, the inlet adapted to supply air to a reaction zone of the combustor. A center body is located within the first radially outer tube, the center body including a second radially intermediate tube for supplying fuel to the reaction zone and a third radially inner tube for supplying air to the reaction zone. The second intermediate tube has a first outlet end closed by a first end wall that is formed with a plurality of substantially parallel, axially-oriented air outlet passages for the additional air in the third radially inner tube, each air outlet passage having a respective plurality of associated fuel outlet passages in the first end wall for the fuel in the second radially intermediate tube. The respective plurality of associated fuel outlet passages have non-parallel center axes that intersect a center axis of the respective air outlet passage to locally mix fuel and air exiting said center body.

    摘要翻译： 用于燃气轮机燃烧器的喷嘴包括限定具有入口和出口的第一通道的第一径向外管，该入口适于将空气供应到燃烧器的反应区。 中心体位于第一径向外管内，中心体包括用于向反应区供应燃料的第二径向中间管和用于向反应区供应空气的第三径向内管。 第二中间管具有由第一端壁封闭的第一出口端，第一端壁形成有用于第三径向内管中的附加空气的多个基本上平行的轴向定向的空气出口通道，每个空气出口通道具有相应的多个 在第二径向中间管中用于燃料的第一端壁中的相关燃料出口通道。 相应的多个相关联的燃料出口通道具有与相应空气出口通道的中心轴线相交的非平行的中心轴线，以局部混合离开所述中心体的燃料和空气。

    Methods and systems for combustion dynamics reduction
    19.
    发明授权
    Methods and systems for combustion dynamics reduction 有权
    燃烧动力学减少的方法和系统

    公开(公告)号：US07578130B1

    公开(公告)日：2009-08-25

    申请号：US12123876

    申请日：2008-05-20

    申请人： Gilbert Otto Kraemer ,  Balachandar Varatharajan ,  Shiva Srinivasan ,  John Joseph Lynch ,  Ertan Yilmaz ,  Kwanwoo Kim ,  Benjamin Lacy ,  Sarah Crothers ,  Kapil Kumar Singh

    发明人： Gilbert Otto Kraemer ,  Balachandar Varatharajan ,  Shiva Srinivasan ,  John Joseph Lynch ,  Ertan Yilmaz ,  Kwanwoo Kim ,  Benjamin Lacy ,  Sarah Crothers ,  Kapil Kumar Singh

    IPC分类号： F02C1/00

    CPC分类号： F23R3/286 ,  F23C2900/07001 ,  F23R3/14 ,  F23R2900/00014

    摘要： Methods and systems for combustion dynamics reduction are provided. A combustion chamber may include a first premixer and a second premixer. Each premixer may include at least one fuel injector, at least one air inlet duct, and at least one vane pack for at least partially mixing the air from the air inlet duct or ducts and fuel from the fuel injector or injectors. Each vane pack may include a plurality of fuel orifices through which at least a portion of the fuel and at least a portion of the air may pass. The vane pack or packs of the first premixer may be positioned at a first axial position and the vane pack or packs of the second premixer may be positioned at a second axial position axially staggered with respect to the first axial position.

    摘要翻译： 提供了减少燃烧动力学的方法和系统。 燃烧室可以包括第一预混合器和第二预混合器。 每个预混合器可以包括至少一个燃料喷射器，至少一个空气入口管道和至少一个叶片组件，用于至少部分地混合来自进气管道或管道的空气以及来自燃料喷射器或喷射器的燃料。 每个叶片组件可以包括多个燃料喷口，燃料的至少一部分和空气的至少一部分可通过该燃料喷口通过。 第一预混合器的叶片组件或组件可以定位在第一轴向位置，并且第二预混合器的叶片组件或组件可以位于相对于第一轴向位置轴向交错的第二轴向位置。

    METHOD AND APPARATUS FOR OPERATING A TURBINE ENGINE
    20.
    发明申请
    METHOD AND APPARATUS FOR OPERATING A TURBINE ENGINE 有权
    用于运行涡轮发动机的方法和装置

    公开(公告)号：US20080078160A1

    公开(公告)日：2008-04-03

    申请号：US11537730

    申请日：2006-10-02

    申请人： Gilbert O Kraemer ,  Benjamin Lacy ,  John Joseph Lipinski

    发明人： Gilbert O Kraemer ,  Benjamin Lacy ,  John Joseph Lipinski

    IPC分类号： B64G1/40

    CPC分类号： F23R3/286 ,  F23D2900/00002 ,  F23D2900/00018 ,  F23D2900/14241 ,  F23R3/02 ,  F23R3/12 ,  F23R3/34

    摘要： A method of operating a turbine engine includes providing at least one combustor having a chamber defined therein. The assembly includes at least one combustor wall defining the chamber and a first fluid passage defining a first fluid inlet within the wall. The first fluid passage is coupled in flow communication with the chamber and is configured to inject a first fluid stream. The assembly further includes at least one second fluid passage defining at least one second fluid inlet within the wall. The second fluid inlet is adjacent to the first fluid inlet and is coupled in flow communication with the chamber. The method also includes injecting the first fluid stream and injecting the second fluid stream into the chamber at an oblique angle with respect to the first fluid stream, thereby intersecting and mixing the second fluid stream with the first fluid stream.

    摘要翻译： 一种操作涡轮发动机的方法包括提供至少一个具有限定在其中的室的燃烧器。 组件包括限定腔室的至少一个燃烧器壁和限定壁内的第一流体入口的第一流体通道。 第一流体通道与室流动连通地联接并且被配置为注入第一流体流。 组件还包括限定壁内的至少一个第二流体入口的至少一个第二流体通道。 第二流体入口与第一流体入口相邻并且与腔室流动连通地联接。 该方法还包括注射第一流体流并将第二流体流以相对于第一流体流倾斜的角度注入到腔室中，从而将第二流体流与第一流体流交叉并混合。