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    Method of protecting gas turbine combustor components against water erosion and hot corrosion
    11.
    发明授权
    Method of protecting gas turbine combustor components against water erosion and hot corrosion 失效
    保护燃气轮机燃烧器部件防止水侵蚀和热腐蚀的方法

    公开(公告)号：US6047539A

    公开(公告)日：2000-04-11

    申请号：US70053

    申请日：1998-04-30

    申请人： Gilbert Farmer

    发明人： Gilbert Farmer

    IPC分类号： F23M5/00 ,  F23R3/00 ,  F02G3/00

    CPC分类号： F23R3/007 ,  F23M5/00 ,  F23R3/002 ,  F23L2900/07008 ,  F23M2900/05001

    摘要： A method of preventing water erosion and hot corrosion in a combustor of a gas turbine engine, wherein water is injected into said combustor for NOx abatement, which involves the step of applying a dense vertically cracked thermal barrier coating to certain components thereof The dense vertically cracked thermal barrier coating has a porosity of less than approximately 8% and a tensile strength in the range of approximately 4-7 ksi. The dense vertically cracked thermal barrier coating is applied to such combustor components so as to produce a segmented ceramic structure having macrocracks formed therein which are oriented substantially perpendicular to an interface of the combustor component and the segmented ceramic structure.

    摘要翻译： 一种防止燃气涡轮发动机的燃烧器中的水侵蚀和热腐蚀的方法，其中将水注入到所述燃烧器中用于NOx减排，其涉及向其某些组分施加致密的垂直裂纹热障涂层的步骤。致密的垂直裂纹 热障涂层的孔隙率小于约8％，拉伸强度在约4-7ksi的范围内。 致密的垂直裂纹热障涂层被施加到这种燃烧器部件上，以便产生一个分段的陶瓷结构，其中形成有宏观裂纹，其中基本垂直于燃烧器部件和分段陶瓷结构的界面。

    Electroplated fuel nozzle/swirler wear coat
    13.
    发明申请
    Electroplated fuel nozzle/swirler wear coat 审中-公开
    电镀喷嘴/旋流器外套

    公开(公告)号：US20060073348A1

    公开(公告)日：2006-04-06

    申请号：US10959843

    申请日：2004-10-06

    申请人： Gilbert Farmer ,  James Groeschen

    发明人： Gilbert Farmer ,  James Groeschen

    IPC分类号： B32B15/04

    CPC分类号： C25D5/022 ,  C09D5/44 ,  C25D7/00 ,  C25D13/04 ,  F23D2213/00 ,  F23R2900/00018 ,  Y10T428/31678

    摘要： A method of applying a wear coat to a surface portion of a fuel assembly. The engine component is dipped in wax and a desired portion of the wax is removed with a fluid. The removed wax exposes a surface of the component. This surface can then be electroplated with a wear coat while the non-exposed surfaces are protected from electrodeposition.

    摘要翻译： 将耐磨涂层施加到燃料组件的表面部分的方法。 将发动机部件浸入蜡中，用流体除去蜡的所需部分。 去除的蜡暴露组件的表面。 然后可以用耐磨涂层对该表面进行电镀，同时防止未暴露的表面电沉积。

    Outer and inner cowl-wire wrap to one piece cowl conversion
    14.
    发明授权
    Outer and inner cowl-wire wrap to one piece cowl conversion 有权
    外部和内部整流罩缠绕成一体式整流罩转换

    公开(公告)号：US06779268B1

    公开(公告)日：2004-08-24

    申请号：US10436842

    申请日：2003-05-13

    申请人： Gilbert Farmer

    发明人： Gilbert Farmer

    IPC分类号： B23P1500

    CPC分类号： F23R3/60 ,  B23P6/005 ,  B23P2700/13 ,  F23M20/005 ,  F23R3/002 ,  F23R3/52 ,  F23R2900/00016 ,  Y10T29/49346 ,  Y10T29/4973

    摘要： A method facilitates replacing a portion of a gas turbine engine combustor. The combustor includes a combustor liner and a wire-wrapped cowl assembly that includes an inner cowl and an outer cowl. The method comprises cutting through the wire-wrapped cowl assembly upstream from fastener openings used to couple the inner and outer cowls to the combustor liner, removing a portion of the cowl assembly from the combustor, and coupling a replacement cowl to the portion of the existing cowl assembly that is downstream from the cut, wherein the replacement cowl includes an inner annular portion, an outer annular portion, and a plurality of circumferentially-spaced radial ligaments extending therebetween.

    摘要翻译： 一种方法有助于更换燃气涡轮发动机燃烧器的一部分。 燃烧器包括燃烧器衬套和包括内罩和外罩的电线包裹整流罩组件。 该方法包括在用于将内罩和外罩连接到燃烧器衬套的紧固件开口的上游切割出线缠绕的前围管组件，从燃烧器移除罩组件的一部分，以及将替换罩与现有部分 整流罩组件，其在所述切口的下游，其中所述替换整流罩包括内部环形部分，外部环形部分和在其间延伸的多个周向间隔开的径向韧带。

    Method of repairing combustion chamber liners
    15.
    发明授权
    Method of repairing combustion chamber liners 失效
    修理燃烧室衬套的方法

    公开(公告)号：US06345441B1

    公开(公告)日：2002-02-12

    申请号：US09618379

    申请日：2000-07-18

    申请人： Gilbert Farmer ,  James Michael Caldwell ,  Steven Allen Stiverson ,  David Bruce Patterson ,  Edward John Emilianowicz

    发明人： Gilbert Farmer ,  James Michael Caldwell ,  Steven Allen Stiverson ,  David Bruce Patterson ,  Edward John Emilianowicz

    IPC分类号： B23P1500

    CPC分类号： B23P6/005 ,  B23P2700/13 ,  F23R3/002 ,  F23R2900/00019 ,  Y10T29/49318 ,  Y10T29/4932 ,  Y10T29/49737

    摘要： A method of repairing an annular transpiration cooled liner for a combustion chamber of a gas turbine engine. An annular portion of the liner including a damaged region is removed from between an upstream section and a downstream section of the liner. Sheet metal is formed into an annular replacement section having at least one axial seam extending between an upstream end and a downstream end of the replacement section. The replacement section is sized and shaped similarly to the removed annular portion of the liner. The upstream end of the formed annular section is joined to the upstream section of the liner and the downstream end of the formed annular section is joined to the downstream section of the liner.

    摘要翻译： 一种修复用于燃气涡轮发动机的燃烧室的环形蒸发冷却衬套的方法。 包括受损区域的衬垫的环形部分从衬套的上游部分和下游部分之间移除。 钣金形成为具有在更换部分的上游端和下游端之间延伸的至少一个轴向接缝的环形更换部分。 替换部分的尺寸和形状类似于衬垫的移除的环形部分。 形成的环形部分的上游端连接到衬套的上游部分，并且所形成的环形部分的下游端连接到衬套的下游部分。

    Adjusting airflow in turbine component by depositing overlay metallic coating
    16.
    发明申请
    Adjusting airflow in turbine component by depositing overlay metallic coating 有权
    通过沉积覆盖金属涂层来调节涡轮机部件中的气流

    公开(公告)号：US20060059918A1

    公开(公告)日：2006-03-23

    申请号：US10934172

    申请日：2004-09-03

    申请人： James Caldwell ,  Thomas Tomlinson ,  Robert Zimmerman ,  Raymond Heidorn ,  Gilbert Farmer

    发明人： James Caldwell ,  Thomas Tomlinson ,  Robert Zimmerman ,  Raymond Heidorn ,  Gilbert Farmer

    IPC分类号： F23R3/42

    CPC分类号： F23R3/06 ,  B23P2700/06 ,  F23R2900/03042 ,  Y10T29/49341

    摘要： A method for adjusting the airflow in a turbine component having a plurality of airflow holes. The method comprises the step of depositing an overlay metallic coating on the surface of the turbine component in a manner such that at least some of the airflow holes are partially filled such that the volume of the partially filled airflow holes is changed so as to adjust the airflow through the turbine component. Also provided is a turbine component having a plurality of airflow holes, at least some of the airflow holes being partially filled with the overlay metallic coating to change the volume thereof so as to adjust the airflow through the turbine component.

    摘要翻译： 一种用于调节具有多个气流孔的涡轮机部件中的气流的方法。 该方法包括以下方式沉积覆盖金属涂层的步骤：使得至少一些气流孔部分地被填充，使得部分填充的气流孔的体积被改变，以便调节 气流通过涡轮机组件。 还提供了具有多个气流孔的涡轮机部件，至少一些气流孔部分地被覆盖金属涂层填充以改变其体积，以便调节通过涡轮机部件的气流。

    Combustor dome for gas turbine engine
    18.
    发明授权
    Combustor dome for gas turbine engine 失效
    燃气涡轮发动机燃烧器顶盖

    公开(公告)号：US06725667B2

    公开(公告)日：2004-04-27

    申请号：US10225757

    申请日：2002-08-22

    申请人： Gilbert Farmer ,  James Anthony Groeschen

    发明人： Gilbert Farmer ,  James Anthony Groeschen

    IPC分类号： F02C314

    CPC分类号： F23R3/002 ,  F23R3/50

    摘要： A combustor for a gas turbine engine having a longitudinal axis extending therethrough, including an inner liner, an outer liner spaced radially from the inner liner, an annular dome connected to the inner and outer liners, a plurality of air/fuel mixers connected to the dome and circumferentially spaced within the dome, an outer cowl connected to the outer liner, and an inner cowl connected to the inner liner, wherein a combustion chamber is formed by the inner liner, the outer liner and the dome. The dome further includes a first end connected to a liner of the combustor, a second end spaced radially from the first end, a first portion extending rearwardly from the first end adjacent the liner, a second portion extending rearwardly from the second end and flaring radially outward from the longitudinal axis, and a nonlinear third portion connecting the first and second dome portions.

    摘要翻译： 一种用于燃气涡轮发动机的燃烧器，其具有延伸穿过其中的纵向轴线，包括内衬，与内衬片径向间隔开的外衬套，连接到内衬和内衬的环形圆顶，多个空气/燃料混合器， 穹顶，圆周间隔开，连接到外衬套的外罩和连接到内衬的内罩，其中燃烧室由内衬，外衬和圆顶形成。 穹顶还包括连接到燃烧器的衬套的第一端，与第一端径向间隔开的第二端，从邻近衬套的第一端向后延伸的第一部分，从第二端向后延伸并径向扩张的第二部分 以及连接第一和第二圆顶部分的非线性第三部分。

    Corrugated cowl for combustor of a gas turbine engine and method for configuring same
    19.
    发明授权
    Corrugated cowl for combustor of a gas turbine engine and method for configuring same 失效
    用于燃气涡轮发动机的燃烧器的波纹罩及其配置方法

    公开(公告)号：US06672067B2

    公开(公告)日：2004-01-06

    申请号：US10085767

    申请日：2002-02-27

    申请人： Gilbert Farmer ,  Ronald D. Redden ,  Balena B. Shorter ,  James A. Groeschen ,  Mehmet M. Dede ,  Daniel L. Durstock

    发明人： Gilbert Farmer ,  Ronald D. Redden ,  Balena B. Shorter ,  James A. Groeschen ,  Mehmet M. Dede ,  Daniel L. Durstock

    IPC分类号： F02C100

    CPC分类号： F23R3/04

    摘要： A cowl for use with a combustor of a gas turbine engine, the cowl includes a main body with an annular corrugation. A combustor of a gas turbine engine, the combustor includes: a hollow body defining a combustion chamber, the hollow body having a liner; an outer cowl having an annular corrugation, the cowl connecting to the liner; and an inner cowl connecting to the liner. A method of configuring a cowl for a gas turbine engine combustor, the method includes forming an annular corrugation in a main body of the cowl.

    摘要翻译： 一种与燃气涡轮发动机的燃烧器一起使用的整流罩，整流罩包括具有环形波纹的主体。 燃气涡轮发动机的燃烧器，所述燃烧器包括：限定燃烧室的空心体，所述中空体具有衬套; 具有环形波纹的外整流罩，连接到衬套的整流罩; 以及连接到衬管的内罩。 一种配置燃气涡轮发动机燃烧室的整流罩的方法，包括在整流罩的主体中形成环形波纹。