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    7FAstage 1 abradable coatings and method for making same
    1.
    发明申请
    7FAstage 1 abradable coatings and method for making same 审中-公开
    7FAstage 1耐磨涂料及其制备方法

    公开(公告)号：US20050003172A1

    公开(公告)日：2005-01-06

    申请号：US10895886

    申请日：2004-07-22

    申请人： James Wheeler ,  Farshad Ghasripoor ,  Chek Beng Ng ,  Raymond Chupp ,  Donald Baldwin ,  Yuk-Chiu Lau ,  Tara McGovern

    发明人： James Wheeler ,  Farshad Ghasripoor ,  Chek Beng Ng ,  Raymond Chupp ,  Donald Baldwin ,  Yuk-Chiu Lau ,  Tara McGovern

    IPC分类号： C23C4/00 ,  B05D3/02 ,  B32B3/00

    CPC分类号： F01D11/122 ,  C23C4/01 ,  C23C4/02 ,  C23C4/04 ,  C23C4/11 ,  C23C4/134 ,  C23C4/18 ,  C23C4/185 ,  F05D2230/312 ,  F05D2250/183 ,  F05D2300/15 ,  Y10T428/12611 ,  Y10T428/24802 ,  Y10T428/24926

    摘要： A method of applying a profiled abradable coating onto a substrate in which an abradable ceramic coating composition is applied to a metal substrate using one or more coating application techniques to produce a defined ceramic pattern without requiring a separate web or grid to be brazed onto the substrate. The invention is particularly designed to withstand the higher operating temperatures encountered with the stage 1 section of 7FA+e gas turbines to allow for increased coating life without significant deterioration in structural or functional integrity. Typically, the grid pattern coating begins approximately 0.431″ after the leading edge of the shroud, and ends approximately 1.60″ before the trailing edge of the shroud. In the case of diamond-shaped patterns, the grid pattern will be about 0.28″ long and 0.28″ wide, with an overall thickness of about 0.46.″ The coatings thus provide the required levels of abradability and leakage performance and may be applied as a chevron or diamond pattern with the shape oriented such that the diagonals run perpendicular and parallel to the sides of the shroud.

    摘要翻译： 将成型的可磨损涂层施加到基底上，其中使用一种或多种涂覆施加技术将可磨损的陶瓷涂层组合物施加到金属基底上以产生限定的陶瓷图案，而不需要将单独的腹板或网格钎焊到基底上 。 本发明特别设计用于承受7FA + e燃气轮机的阶段1部分遇到的更高的工作温度，以允许更长的涂层寿命，而结构或功能完整性没有显着恶化。 通常，网格图案涂层在护罩的前缘大约0.431“开始，并且在护罩的后缘之前大约为1.60”。 在菱形图案的情况下，网格图案将为约0.28“长和0.28”宽，总厚度约为0.46“。因此，涂层提供所需的耐磨性和泄漏性能水平，并且可能 应用为人字形或菱形图案，其形状定向成使得对角线垂直并平行于护罩的侧面延伸。

    PATTERN FOR THE SURFACE OF A TURBINE SHROUD
    2.
    发明申请
    PATTERN FOR THE SURFACE OF A TURBINE SHROUD 有权
    涡轮机表面图案

    公开(公告)号：US20060110247A1

    公开(公告)日：2006-05-25

    申请号：US10907972

    申请日：2005-04-22

    申请人： Warren Nelson ,  Brian Arness ,  Paul Marks ,  Raymond Chupp ,  Tara McGovern

    发明人： Warren Nelson ,  Brian Arness ,  Paul Marks ,  Raymond Chupp ,  Tara McGovern

    IPC分类号： F01D5/20

    CPC分类号： F01D11/12 ,  F01D11/122

    摘要： An article of manufacture pattern for improving aerodynamic performance of a turbine including an abradable material capable of abradable contact. The abradable material is disposed in a pattern. The pattern includes a first plurality of ridges disposed at a base surface of the turbine. Each ridge of the first plurality of ridges has a first sidewall and a second sidewall having a first end and a second end. The first ends of the first and second sidewalls extend from the base surface. The first and second sidewalls slope toward each other with substantially equal but opposite slopes until meeting at the second ends of respective first and second sidewalls defining a centerline and a top portion of the ridge.

    摘要翻译： 一种用于改善涡轮机的空气动力性能的制造模式的制品，其包括能够耐磨的接触的耐磨材料。 耐磨材料以图案设置。 该图案包括设置在涡轮机的基面处的第一多个脊。 第一多个脊中的每个脊具有第一侧壁和具有第一端和第二端的第二侧壁。 第一和第二侧壁的第一端从基面延伸。 第一和第二侧壁彼此相对倾斜，具有基本上相等但相反的斜面，直到在相应的第一和第二侧壁的第二端处共同限定脊的中心线和顶部。

    Pattern for the surface of a turbine shroud
    3.
    发明申请
    Pattern for the surface of a turbine shroud 有权

    公开(公告)号：US20060110248A1

    公开(公告)日：2006-05-25

    申请号：US10996878

    申请日：2004-11-24

    申请人： Warren Nelson ,  Brian Arness ,  Paul Marks ,  Raymond Chupp ,  Tara McGovern

    发明人： Warren Nelson ,  Brian Arness ,  Paul Marks ,  Raymond Chupp ,  Tara McGovern

    IPC分类号： F01D5/20

    CPC分类号： F01D11/12 ,  F01D11/122

    摘要： A pattern for improving aerodynamic performance of a turbine includes a material disposed in a pattern at a base surface of a turbine shroud such that the material is capable of abradable contact with a tip portion of a turbine bucket. The pattern includes a first plurality of ridges disposed at the base surface such that a first portion of the first plurality of ridges corresponding to a back portion of the turbine bucket is oriented at a first angle with respect to an axis of rotation of the turbine bucket. Each ridge of the first plurality of ridges has a first sidewall and a second sidewall having a first end and a second end. The first ends of the first and second sidewalls extend from the base surface. The first and second sidewalls slope toward each other with substantially equal but opposite slopes until meeting at the second ends of respective first and second sidewalls defining a centerline and a top portion of the ridge.

    Cooling Circuit for Enhancing Turbine Performance
    5.
    发明申请
    Cooling Circuit for Enhancing Turbine Performance 审中-公开
    用于提高涡轮机性能的冷却回路

    公开(公告)号：US20090074589A1

    公开(公告)日：2009-03-19

    申请号：US11856945

    申请日：2007-09-18

    申请人： Biao Fang ,  Christopher Edward Wolfe ,  Omprakash Samudrala ,  Matthew Scott Kight ,  Jeffrey John Butkiewicz ,  Tara McGovern

    发明人： Biao Fang ,  Christopher Edward Wolfe ,  Omprakash Samudrala ,  Matthew Scott Kight ,  Jeffrey John Butkiewicz ,  Tara McGovern

    IPC分类号： F01D5/08

    CPC分类号： F02C7/12 ,  F01D25/12

    摘要： In a gas turbine having a compressor discharge casing, a cooling circuit diverts compressor discharge air toward a high pressure packing (HPP) circuit. The cooling circuit includes an inlet pipe that receives compressor discharge air. One or several cooled cooling air pipes are in fluid communication with the inlet pipe via a pipe manifold, which distributes the discharge air across the cooled cooling air pipes. A seal is disposed upstream of an entrance to the HPP circuit to limit flow into the HPP circuit, and a second seal is disposed downstream of the HPP circuit at turbine wheelspace to limit ingestion and thus the purge flow air required. The circuit serves to reduce required purge flow in the HPP circuit so that an amount of compressor discharge air can be put back to the main flow path, thereby improving turbine performance.

    摘要翻译： 在具有压缩机排放壳体的燃气轮机中，冷却回路将压缩机排出的空气转向高压包装（HPP）回路。 冷却回路包括接收压缩机排出空气的入口管。 一个或几个冷却的冷却空气管通过管道歧管与入口管流体连通，管道歧管将排放空气分配在冷却的冷却空气管道上。 密封件设置在HPP回路入口的上游，以限制流入HPP回路的第二密封件，并且在涡轮机轮距处设置在HPP回路下游的第二密封件，以限制摄入量，从而限制吸入流量所需的空气流量。 该电路用于减少HPP电路中所需的清洗流量，使得压缩机排出空气的量可以放回到主流路，从而提高涡轮机性能。