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33 条记录 (耗时 0.028 秒)

    Method of repairing combustion chamber liners
    1.
    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。

    Coated component with through-hole having improved surface finish
    4.
    发明授权
    Coated component with through-hole having improved surface finish 失效
    具有通孔的涂层部件具有改进的表面光洁度

    公开(公告)号：US06908657B2

    公开(公告)日：2005-06-21

    申请号：US10605241

    申请日：2003-09-17

    申请人： Gilbert Farmer ,  Jeffrey Arnold Fehrenbach

    发明人： Gilbert Farmer ,  Jeffrey Arnold Fehrenbach

    IPC分类号： B24C1/00 ,  B23P6/00 ,  B24C11/00 ,  C23C4/00 ,  F01D5/18 ,  F01D5/28 ,  B32B3/10 ,  F02G1/00

    CPC分类号： B23P6/002 ,  B23P2700/06 ,  C23C4/00 ,  F01D5/186 ,  F01D5/288 ,  F05D2230/13 ,  F05D2260/607 ,  Y10T29/49318 ,  Y10T29/49339 ,  Y10T428/12361 ,  Y10T428/24273 ,  Y10T428/249953

    摘要： A process of removing deposits from through-holes in a component, such as metallic bond coat and ceramic materials from cooling holes in an air-cooled gas turbine engine. The process is particularly effective in removing a TBC material deposited in a cooling hole of a component as a result of depositing a coating of the TBC material on a surface of the component, in which the deposit is removed from the cooling hole without damaging the cooling hole or the TBC coating surrounding the cooling hole on the coated surface of the component. A preferred feature is that the cooling hole, including the entrance to the hole at a surface of the component opposite the coated surface and the coating surrounding the exit of the hole at the coated surface, exhibits improved surface characteristics that increase the discharge coefficient of the cooling hole, as evidenced by an increase in the effective area of the cooling hole.

    摘要翻译： 从空气冷却燃气涡轮发动机的冷却孔中除去金属结合层和陶瓷材料等成分的通孔的沉积物的工序。 该方法特别有效地除去沉积在部件的冷却孔中的TBC材料，这是因为在组件的表面上沉积TBC材料的涂层，其中沉积物从冷却孔移除而不损坏冷却 孔或TBC涂层，围绕组件的涂覆表面上的冷却孔。 一个优选的特征是，包括在与涂覆表面相对的部件的表面处的孔的入口和围绕涂覆表面的孔的出口的涂层的冷却孔表现出改进的表面特性，其增加了 如冷却孔的有效面积的增加所证明的。

    Venturi for use in the swirl cup package of a gas turbine combustor having water injected therein
    7.
    发明授权
    Venturi for use in the swirl cup package of a gas turbine combustor having water injected therein 失效
    文丘里管用于其中注入有水的燃气轮机燃烧器的涡流杯组件

    公开(公告)号：US06286302B1

    公开(公告)日：2001-09-11

    申请号：US09283428

    申请日：1999-04-01

    申请人： Gilbert Farmer ,  James A. Groeschen ,  Mark G. Rettig

    发明人： Gilbert Farmer ,  James A. Groeschen ,  Mark G. Rettig

    IPC分类号： F02C700

    CPC分类号： F23L7/002 ,  F23D2211/00 ,  F23R3/14

    摘要： A combustion apparatus for a gas turbine engine including a combustor structure having at least one combustion chamber, a dual cone fuel nozzle for injecting both fuel and water to the combustion chamber, and a swirl cup package upstream of and adjacent to the combustion chamber. The swirl cup package further includes a swirler and a venturi extending between the nozzle and the combustion chamber for mixing the fuel and water with air. The venturi is configured to have a non-uniform thickness from an upstream end to a downstream end resulting in a cross-sectional area which provides a heat transfer conduction path that reduces axial stresses imposed on the venturi when water impinges on an upstream portion of the venturi.

    摘要翻译： 一种用于燃气涡轮发动机的燃烧装置，其包括具有至少一个燃烧室的燃烧器结构，用于将燃料和水喷射到燃烧室的双锥形燃料喷嘴，以及在燃烧室上游和邻近燃烧室的涡流杯组件。 涡流杯包装还包括在喷嘴和燃烧室之间延伸的旋流器和文氏管，用于将燃料和水与空气混合。 文丘里管构造成具有从上游端到下游端的不均匀的厚度，从而产生横截面积，该横截面面积提供传热传导路径，当水冲击在文丘里管的上游部分时，该导热路径减小施加在文氏管上的轴向应力 文丘里

    Process of removing a coating deposit from a through-hole in a component and component processed thereby
    9.
    发明授权
    Process of removing a coating deposit from a through-hole in a component and component processed thereby 失效
    从被处理的部件和部件中的通孔中去除涂层沉积物的过程

    公开(公告)号：US06663919B2

    公开(公告)日：2003-12-16

    申请号：US10086266

    申请日：2002-03-01

    申请人： Gilbert Farmer ,  Jeffrey Arnold Fehrenbach

    发明人： Gilbert Farmer ,  Jeffrey Arnold Fehrenbach

    IPC分类号： C23C418

    CPC分类号： B23P6/002 ,  B23P2700/06 ,  C23C4/00 ,  F01D5/186 ,  F01D5/288 ,  F05D2230/13 ,  F05D2260/607 ,  Y10T29/49318 ,  Y10T29/49339 ,  Y10T428/12361 ,  Y10T428/24273 ,  Y10T428/249953

    摘要： A process of removing deposits from through-holes in a component, such as metallic bond coat and ceramic materials from cooling holes in an air-cooled gas turbine engine. The process is particularly effective in removing a TBC material deposited in a cooling hole of a component as a result of depositing a coating of the TBC material on a surface of the component, in which the deposit is removed from the cooling hole without damaging the cooling hole or the TBC coating surrounding the cooling hole on the coated surface of the component. A preferred feature is that the cooling hole, including the entrance to the hole at a surface of the component opposite the coated surface and the coating surrounding the exit of the hole at the coated surface, exhibits improved surface characteristics that increase the discharge coefficient of the cooling hole, as evidenced by an increase in the effective area of the cooling hole.

    摘要翻译： 从空气冷却燃气涡轮发动机的冷却孔中除去金属结合层和陶瓷材料等成分的通孔的沉积物的工序。 该方法特别有效地除去沉积在部件的冷却孔中的TBC材料，这是因为在组件的表面上沉积TBC材料的涂层，其中沉积物从冷却孔移除而不损坏冷却 孔或TBC涂层，围绕组件的涂覆表面上的冷却孔。 一个优选的特征是，包括在与涂覆表面相对的部件的表面处的孔的入口和围绕涂覆表面的孔的出口的涂层的冷却孔表现出改进的表面特性，其增加了 如冷却孔的有效面积的增加所证明的。

    Method of adjusting gas turbine component cooling air flow
    10.
    发明授权
    Method of adjusting gas turbine component cooling air flow 失效
    调整燃气轮机部件冷却风量的方法

    公开(公告)号：US06408610B1

    公开(公告)日：2002-06-25

    申请号：US09618571

    申请日：2000-07-18

    申请人： James M. Caldwell ,  Gilbert Farmer ,  Karl S. Fessenden ,  Xuenan Wang ,  Jerald M. Kauffman

    发明人： James M. Caldwell ,  Gilbert Farmer ,  Karl S. Fessenden ,  Xuenan Wang ,  Jerald M. Kauffman

    IPC分类号： F02C712

    CPC分类号： F01D5/186 ,  B23P2700/06 ,  C23C14/046 ,  F01D5/18 ,  F01D5/288 ,  Y10T29/4932

    摘要： A method of adjusting airflow through a plurality of cooling holes by depositing a thermal barrier coating on an exterior surface and/or an interior surface of the component by a physical vapor deposition process. The cooling holes are not masked. Thus, a portion of the thermal barrier coating partially obstructs airflow through the cooling holes and reduces airflow through the cooling holes. A predetermined pressure drop is developed across the cooling holes and airflow through the cooling holes is measured. The measured airflow is compared to a preselected range of desired cooling hole airflows and the steps of depositing the thermal barrier coating, developing the predetermined pressure drop, calculating airflow and comparing the measured airflow to the preselected range are repeated until the measured airflow is within the preselected range of desired cooling hole airflows.

    摘要翻译： 通过物理气相沉积工艺在组件的外表面和/或内表面上沉积热障涂层，来调节通过多个冷却孔的气流的方法。 冷却孔未被遮蔽。 因此，热障涂层的一部分部分阻碍通过冷却孔的空气流并且减少通过冷却孔的气流。 在冷却孔之间产生预定的压降，并测量通过冷却孔的气流。 将测量的气流与期望的冷却孔气流的预选范围进行比较，并重复沉积热障涂层，显影预定压降，计算气流并将测量的气流与预选范围进行比较的步骤，直到所测量的气流在 所需冷却孔气流的预选范围。