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71 条记录 (耗时 0.028 秒)

    Flow conditioner for use in gas turbine component in which combustion occurs
    32.
    发明授权
    Flow conditioner for use in gas turbine component in which combustion occurs 失效
    用于燃烧发生的燃气轮机部件的流量​​调节器

    公开(公告)号：US08387397B2

    公开(公告)日：2013-03-05

    申请号：US12360490

    申请日：2009-01-27

    申请人： Wei Chen ,  Ronald James Chila ,  Eric William King

    发明人： Wei Chen ,  Ronald James Chila ,  Eric William King

    IPC分类号： F02C1/00 ,  F02G3/00

    CPC分类号： F23R3/06 ,  F23R2900/03045

    摘要： A gas turbine component in which combustion occurs. The gas turbine component includes a liner, including a first surface facing a first space and a second surface facing a second space, the liner being interposed between the first and second spaces and having a through-hole defined therein extending from the first to the second surface by which incoming flows proceed from the first space and to the second space. At least the first surface is formed to flow condition the incoming flows to resist separating from sidewalls of the through-hole.

    摘要翻译： 燃烧发生的燃气轮机部件。 所述燃气涡轮机部件包括衬套，所述衬套包括面对第一空间的第一表面和面向第二空间的第二表面，所述衬垫插入在所述第一和第二空间之间，并且具有限定在其中的通孔，所述通孔从所述第一空间延伸到第二空间 输入流从第一空间和第二空间进入的表面。 至少第一表面形成为使进入的流动流动以抵抗与通孔的侧壁分离。

    High temperature seal for a turbine engine
    33.
    发明授权
    High temperature seal for a turbine engine 有权
    涡轮发动机的高温密封

    公开(公告)号：US08322976B2

    公开(公告)日：2012-12-04

    申请号：US12098860

    申请日：2008-04-07

    申请人： Ronald James Chila ,  Kevin Weston McMahan ,  Timur Repikov

    发明人： Ronald James Chila ,  Kevin Weston McMahan ,  Timur Repikov

    IPC分类号： F04D29/04

    CPC分类号： F01D9/023 ,  F01D11/005 ,  F02C7/28 ,  F05D2240/57 ,  F16J15/0887 ,  F16J15/104

    摘要： A turbine includes a static member, a moveable member fluidly connected to the static member, and a flexible seal. The flexible seal includes a spring component having a base section mounted to one of the static member and the moveable member of the turbine and a plurality of biasing members. Each of the plurality of biasing members includes a first portion extending from the base section and a cantilevered portion. The flexible seal further includes a seal component provided on the cantilevered portion of each of the plurality of biasing members. The seal component is biased into contact with the other of the static member and the moveable member.

    摘要翻译： 涡轮机包括静态构件，流体连接到静止构件的可动构件和柔性密封件。 柔性密封件包括弹簧部件，其具有安装到涡轮机的静止部件和可移动部件之一的基部以及多个偏置部件。 多个偏置构件中的每一个包括从基部延伸的第一部分和悬臂部分。 柔性密封件还包括设置在多个偏置构件中的每一个的悬臂部分上的密封部件。 密封部件被偏置成与静止部件和可移动部件中的另一个接触。

    System for cooling turbine combustor transition piece
    34.
    发明授权
    System for cooling turbine combustor transition piece 有权
    涡轮机燃烧器过渡段冷却系统

    公开(公告)号：US08307655B2

    公开(公告)日：2012-11-13

    申请号：US12784477

    申请日：2010-05-20

    申请人： Ronald James Chila ,  David William Cihlar

    发明人： Ronald James Chila ,  David William Cihlar

    IPC分类号： F02C1/00

    CPC分类号： F23R3/002 ,  F01D9/023 ,  F02C7/12 ,  Y02T50/675

    摘要： An air cooling hood offset from an exterior of the transition piece to define an air cooling passage between the air cooling hood and the exterior of the transition piece, wherein the air cooling hood comprises a plurality of air outlets disposed along the exterior of the transition piece, and the plurality of air outlets is configured to expel an airflow from the air cooling passage away from the exterior of the transition piece.

    摘要翻译： 空气冷却罩从过渡件的外部偏移以限定空气冷却罩和过渡件的外部之间的空气冷却通道，其中空气冷却罩包括沿着过渡件的外部设置的多个空气出口 并且多个空气出口构造成从空气冷却通道排出远离过渡件外部的气流。

    IMPINGEMENT SLEEVE AND METHODS FOR DESIGNING AND FORMING IMPINGEMENT SLEEVE
    35.
    发明申请
    IMPINGEMENT SLEEVE AND METHODS FOR DESIGNING AND FORMING IMPINGEMENT SLEEVE 有权
    IMPINGEMENT SLEEVE AND METHODS FOR DESIGN AND FORMING IMPINGEMENT SLEEVE

    公开(公告)号：US20120234012A1

    公开(公告)日：2012-09-20

    申请号：US13048394

    申请日：2011-03-15

    申请人： Jerome David Brown ,  Ronald James Chila ,  Patrick Benedict Melton ,  Russell DeForest ,  David William Cihlar

    发明人： Jerome David Brown ,  Ronald James Chila ,  Patrick Benedict Melton ,  Russell DeForest ,  David William Cihlar

    IPC分类号： F23R3/42 ,  B23P17/00

    CPC分类号： F01D9/023 ,  F05D2260/201 ,  F23R2900/03044 ,  Y10T29/49229

    摘要： An impingement sleeve and methods for designing and forming an impingement sleeve are disclosed. In one embodiment, a method for designing an impingement sleeve is disclosed. The method includes determining a desired operational value for a transition piece, inputting a combustor characteristic into a processor, and utilizing the combustor characteristic in the processor to determine a cooling hole pattern for the impingement sleeve, the cooling hole pattern comprising a plurality of cooling holes, at least a portion of the plurality of cooling holes being generally longitudinally asymmetric, the cooling hole pattern providing the desired operational value.

    摘要翻译： 公开了一种冲击套筒和用于设计和形成冲击套筒的方法。 在一个实施例中，公开了一种用于设计冲击套筒的方法。 该方法包括确定过渡件的期望操作值，将燃烧器特性输入到处理器中，以及利用处理器中的燃烧器特性来确定冲击套筒的冷却孔图案，冷却孔图案包括多个冷却孔 所述多个冷却孔的至少一部分大致纵向不对称，所述冷却孔图案提供期望的操作值。

    Combustor exit temperature profile control via fuel staging and related method
    36.
    发明授权
    Combustor exit temperature profile control via fuel staging and related method 有权
    通过燃油分段控制燃烧器出口温度曲线及相关方法

    公开(公告)号：US08082739B2

    公开(公告)日：2011-12-27

    申请号：US12758296

    申请日：2010-04-12

    申请人： Ronald James Chila ,  Mark Hadley

    发明人： Ronald James Chila ,  Mark Hadley

    IPC分类号： F02C7/22

    CPC分类号： F23R3/346

    摘要： A gas turbine combustor includes a combustion chamber defined by a combustor liner, the combustor liner having an upstream end cover supporting one or more nozzles arranged to supply fuel to the combustion chamber where the fuel mixes with air supplied from a compressor. A transition duct is connected between an aft end of the combustion chamber liner and a first stage turbine casing, the transition duct supplying gaseous products of combustion to the first stage turbine nozzle. One or more additional fuel injection nozzles are arranged at an aft end of the transition duct for introducing additional fuel into the transition duct upstream of the first stage turbine nozzle.

    摘要翻译： 燃气轮机燃烧器包括由燃烧器衬套限定的燃烧室，所述燃烧器衬套具有支撑一个或多个喷嘴的上游端盖，所述喷嘴布置成将燃料供应到燃烧室，在燃烧室中燃料与从压缩机供应的空气混合。 过渡管道连接在燃烧室衬套的后端和第一级涡轮机壳体之间，该过渡管道向第一级涡轮喷嘴提供燃烧气体产物。 一个或多个附加的燃料喷射喷嘴布置在过渡管道的后端，用于将额外的燃料引入到在第一级涡轮喷嘴上游的过渡管道中。

    COMBUSTOR LINER HELICAL COOLING APPARATUS
    37.
    发明申请
    COMBUSTOR LINER HELICAL COOLING APPARATUS 有权
    COMBUSTOR LINER HELIC冷却装置

    公开(公告)号：US20110247341A1

    公开(公告)日：2011-10-13

    申请号：US12757610

    申请日：2010-04-09

    申请人： Kevin Weston McMahan ,  Ronald James Chila

    发明人： Kevin Weston McMahan ,  Ronald James Chila

    IPC分类号： F02C7/18

    CPC分类号： F23M5/085 ,  F23R3/002 ,  F23R2900/03043 ,  F23R2900/03045

    摘要： A combustor liner is provided. The combustor liner may include an upstream portion and a downstream end portion. The upstream portion may have a radius and a length along a generally longitudinal axis. The downstream end portion may have a radius and a length along the generally longitudinal axis. The downstream end portion may define a plurality of channels. Each of the plurality of channels may extend helically through the length of the downstream end portion. Each of the plurality of channels may be configured to flow an air flow therethrough, cooling the downstream end portion.

    摘要翻译： 提供燃烧器衬套。 燃烧器衬套可以包括上游部分和下游端部分。 上游部分可以具有沿着大致纵向轴线的半径和长度。 下游端部可以具有沿着大致纵向轴线的半径和长度。 下游端部可以限定多个通道。 多个通道中的每一个可以螺旋地延伸穿过下游端部的长度。 多个通道中的每一个可以被配置为使空气流通过其中，从而冷却下游端部。

    COOLING APPARATUS FOR COMBUSTOR TRANSITION PIECE
    38.
    发明申请
    COOLING APPARATUS FOR COMBUSTOR TRANSITION PIECE 有权
    用于燃烧器过渡部件的冷却装置

    公开(公告)号：US20090252593A1

    公开(公告)日：2009-10-08

    申请号：US12099352

    申请日：2008-04-08

    申请人： Ronald James Chila ,  David Purnell

    发明人： Ronald James Chila ,  David Purnell

    IPC分类号： F02C7/12 ,  F04D29/58

    CPC分类号： F01D9/023 ,  F01D25/12 ,  F02C7/18 ,  F05D2230/21 ,  F05D2230/232 ,  Y02T50/675

    摘要： Disclosed is an apparatus for cooling a transition piece of a combustor includes at least one wrapper disposed at the transition piece located outboard of the transition piece. At least one support boss is located between the at least one wrapper and the transition piece. The at least one support boss, the at least one wrapper, and transition piece define at least one cooling flow channel for directing flow for cooling the transition piece. A method of cooling a transition piece of a combustor includes flowing cooling flow into at least one cooling flow channel located at the transition piece, the at least one cooling flow channel defined by the transition piece, at least one wrapper located at the transition piece and located outboard of the transition piece, and at least one support boss located between the at least one wrapper and the transition piece. The cooling flow is directed via the at least one support boss and flows across an outer surface of the transition piece thereby cooling the transition piece.

    摘要翻译： 公开了一种用于冷却燃烧器的过渡件的设备，包括设置在过渡件外侧的过渡件上的至少一个包装纸。 至少一个支撑凸台位于至少一个包装件和过渡件之间。 至少一个支撑凸台，至少一个包装件和过渡件限定至少一个冷却流动通道，用于引导流动以冷却过渡件。 一种冷却燃烧器的过渡件的方法包括将冷却流流入位于过渡件的至少一个冷却流动通道，由过渡件限定的至少一个冷却流动通道，位于过渡件处的至少一个包装物， 位于过渡件的外侧，以及位于至少一个包装件和过渡件之间的至少一个支撑凸起。 冷却流动经由至少一个支撑凸台引导并且流过过渡件的外表面，从而冷却过渡件。