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    Turbine blade assemblies and methods of manufacturing the same
    3.
    发明授权
    Turbine blade assemblies and methods of manufacturing the same 有权
    涡轮叶片组件及其制造方法

    公开(公告)号：US08292587B2

    公开(公告)日：2012-10-23

    申请号：US12338746

    申请日：2008-12-18

    申请人： Kin Poon ,  Rajiv Rana ,  Bob Mitlin ,  Ardeshir Riahi ,  David Chou ,  Steve Halfmann ,  Frank Mignano

    发明人： Kin Poon ,  Rajiv Rana ,  Bob Mitlin ,  Ardeshir Riahi ,  David Chou ,  Steve Halfmann ,  Frank Mignano

    IPC分类号： F01D11/00

    CPC分类号： F01D5/187 ,  F01D5/225 ,  F05D2230/60 ,  F05D2240/81 ,  Y02T50/676

    摘要： A turbine blade assembly includes an airfoil, a platform, and a first cover plate. A center flow path extends through the platform in communication with an internal cooling circuit of the airfoil, which extends from a first side of the platform. A second side of the platform is located opposite the platform from the first side. An edge of the platform extends between the first and second sides and, a first passage is formed between the first and second sides and includes a first inlet and a first outlet. The first passage extends from the center flow path toward the platform edge, and a first groove is formed on the second side of the platform and extends from the first outlet of the first passage toward the edge of the platform. The first cover plate is disposed over the second side of the platform covering the first groove.

    摘要翻译： 涡轮叶片组件包括翼型件，平台和第一盖板。 中心流动路径延伸穿过与从平台的第一侧延伸的翼型件的内部冷却回路连通的平台。 平台的第二侧与第一侧相对的平台。 平台的边缘在第一和第二侧面之间延伸，并且第一通道形成在第一和第二侧之间，并且包括第一入口和第一出口。 第一通道从中心流动路径延伸到平台边缘，并且第一凹槽形成在平台的第二侧上，并且从第一通道的第一出口朝向平台的边缘延伸。 第一盖板设置在覆盖第一凹槽的平台的第二侧上。

    Air cooled turbine blades and methods of manufacturing
    4.
    发明授权
    Air cooled turbine blades and methods of manufacturing 有权
    风冷式涡轮叶片及其制造方法

    公开(公告)号：US08292581B2

    公开(公告)日：2012-10-23

    申请号：US11971459

    申请日：2008-01-09

    申请人： Kin C. Poon ,  Malak F. Malak ,  Rajiv Rana ,  Ardeshir Riahi ,  David H. Chou

    发明人： Kin C. Poon ,  Malak F. Malak ,  Rajiv Rana ,  Ardeshir Riahi ,  David H. Chou

    IPC分类号： F01D5/08

    CPC分类号： F01D5/187 ,  B22C9/10 ,  B22C9/103 ,  B22D25/00 ,  F01D5/081 ,  F01D5/087 ,  F01D5/20 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/676 ,  Y10T29/49341

    摘要： An air-cooled turbine blade and methods of manufacturing the blade are provided. The blade includes a suction side flow circuit formed within its interior and defined at least by an interior surface of a convex suction side wall, a pressure side flow circuit formed within the blade interior and defined at least by an interior surface of a concave pressure side wall, and a center flow circuit including a first section and a second section, the first section disposed between the suction side flow circuit and the pressure side flow circuit, and the second section in flow communication with the first section and a plurality of openings of a leading edge wall and defined at least partially by an interior surface of the leading edge wall.

    摘要翻译： 提供一种风冷式涡轮叶片及其制造方法。 叶片包括形成在其内部并且至少由凸起的吸入侧壁的内表面限定的吸入侧流动回路，压力侧流动回路形成在叶片内部并且至少由凹入压力侧的内表面限定 壁和包括第一部分和第二部分的中心流动回路，第一部分设置在吸力侧流动回路和压力侧流动回路之间，第二部分与第一部分流动连通，并且多个开口 前缘壁并且至少部分地由前缘壁的内表面限定。

    AIR COOLED TURBINE BLADES AND METHODS OF MANUFACTURING
    5.
    发明申请
    AIR COOLED TURBINE BLADES AND METHODS OF MANUFACTURING 有权
    空气冷却涡轮叶片及其制造方法

    公开(公告)号：US20090175733A1

    公开(公告)日：2009-07-09

    申请号：US11971459

    申请日：2008-01-09

    申请人： Kin C. Poon ,  Malak F. Malak ,  Rajiv Rana ,  Ardeshir Riahi ,  David H. Chou

    发明人： Kin C. Poon ,  Malak F. Malak ,  Rajiv Rana ,  Ardeshir Riahi ,  David H. Chou

    IPC分类号： F01D5/18 ,  B23P15/02

    CPC分类号： F01D5/187 ,  B22C9/10 ,  B22C9/103 ,  B22D25/00 ,  F01D5/081 ,  F01D5/087 ,  F01D5/20 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/676 ,  Y10T29/49341

    摘要： An air-cooled turbine blade and methods of manufacturing the blade are provided. The blade includes a suction side flow circuit formed within its interior and defined at least by an interior surface of a convex suction side wall, a pressure side flow circuit formed within the blade interior and defined at least by an interior surface of a concave pressure side wall, and a center flow circuit including a first section and a second section, the first section disposed between the suction side flow circuit and the pressure side flow circuit, and the second section in flow communication with the first section and a plurality of openings of a leading edge wall and defined at least partially by an interior surface of the leading edge wall.

    摘要翻译： 提供一种风冷式涡轮叶片及其制造方法。 叶片包括形成在其内部并且至少由凸起的吸入侧壁的内表面限定的吸入侧流动回路，压力侧流动回路形成在叶片内部并且至少由凹入压力侧的内表面限定 壁和包括第一部分和第二部分的中心流动回路，第一部分设置在吸力侧流动回路和压力侧流动回路之间，第二部分与第一部分流动连通，并且多个开口 前缘壁并且至少部分地由前缘壁的内表面限定。

    TURBINE BLADE ASSEMBLIES AND METHODS OF MANUFACTURING THE SAME
    6.
    发明申请
    TURBINE BLADE ASSEMBLIES AND METHODS OF MANUFACTURING THE SAME 有权
    涡轮叶片组件及其制造方法

    公开(公告)号：US20100158700A1

    公开(公告)日：2010-06-24

    申请号：US12338746

    申请日：2008-12-18

    申请人： Kin Poon ,  Rajiv Rana ,  Bob Mitlin ,  Ardeshir Riahi ,  David Chou ,  Steve Halfmann ,  Frank Mignano

    发明人： Kin Poon ,  Rajiv Rana ,  Bob Mitlin ,  Ardeshir Riahi ,  David Chou ,  Steve Halfmann ,  Frank Mignano

    IPC分类号： F01D5/18 ,  B22D19/08

    CPC分类号： F01D5/187 ,  F01D5/225 ,  F05D2230/60 ,  F05D2240/81 ,  Y02T50/676

    摘要： A turbine blade assembly includes an airfoil, a platform, and a first cover plate. A center flow path extends through the platform in communication with an internal cooling circuit of the airfoil, which extends from a first side of the platform. A second side of the platform is located opposite the platform from the first side. An edge of the platform extends between the first and second sides and, a first passage is formed between the first and second sides and includes a first inlet and a first outlet. The first passage extends from the center flow path toward the platform edge, and a first groove is formed on the second side of the platform and extends from the first outlet of the first passage toward the edge of the platform. The first cover plate is disposed over the second side of the platform covering the first groove.

    摘要翻译： 涡轮叶片组件包括翼型件，平台和第一盖板。 中心流动路径延伸穿过与从平台的第一侧延伸的翼型件的内部冷却回路连通的平台。 平台的第二侧与第一侧相对的平台。 平台的边缘在第一和第二侧面之间延伸，并且第一通道形成在第一和第二侧之间，并且包括第一入口和第一出口。 第一通道从中心流动路径延伸到平台边缘，并且第一凹槽形成在平台的第二侧上，并且从第一通道的第一出口朝向平台的边缘延伸。 第一盖板设置在覆盖第一凹槽的平台的第二侧上。

    Turbine rotor cooling flow system
    7.
    发明授权
    Turbine rotor cooling flow system 有权
    涡轮转子冷却流系统

    公开(公告)号：US08277169B2

    公开(公告)日：2012-10-02

    申请号：US11155399

    申请日：2005-06-16

    申请人： Ardeshir Riahi ,  Frederick G. Borns ,  Vivek Agarwal

    发明人： Ardeshir Riahi ,  Frederick G. Borns ,  Vivek Agarwal

    IPC分类号： F01D5/08

    CPC分类号： F01D5/081 ,  Y02T50/676

    摘要： Disclosed herein is an apparatus comprising a disk coverplate for a turbine rotor, the disk coverplate comprising a plurality of cooling holes, wherein the distance between the centers of any two adjacent cooling holes is greater than twice the average diameter of the two adjacent cooling holes. A method to control turbine cooling air flow is also disclosed.

    摘要翻译： 本文公开了一种包括用于涡轮转子的盘盖板的装置，盘盖板包括多个冷却孔，其中任何两个相邻冷却孔的中心之间的距离大于两个相邻冷却孔的平均直径的两倍。 还公开了一种控制涡轮机冷却空气流动的方法。

    Turbine rotor cooling flow system
    8.
    发明申请
    Turbine rotor cooling flow system 有权
    涡轮转子冷却流系统

    公开(公告)号：US20060285968A1

    公开(公告)日：2006-12-21

    申请号：US11155399

    申请日：2005-06-16

    申请人： Ardeshir Riahi ,  Frederick Borns ,  Vivek Agarwal

    发明人： Ardeshir Riahi ,  Frederick Borns ,  Vivek Agarwal

    IPC分类号： F03B11/00

    CPC分类号： F01D5/081 ,  Y02T50/676

    摘要： Disclosed herein is an apparatus comprising a disk coverplate for a turbine rotor, the disk coverplate comprising a plurality of cooling holes, wherein the distance between the centers of any two adjacent cooling holes is greater than twice the average diameter of the two adjacent cooling holes. A method to control turbine cooling air flow is also disclosed.

    摘要翻译： 本文公开了一种包括用于涡轮转子的盘盖板的装置，盘盖板包括多个冷却孔，其中任何两个相邻冷却孔的中心之间的距离大于两个相邻冷却孔的平均直径的两倍。 还公开了一种控制涡轮机冷却空气流动的方法。

    Turbine blades and methods of manufacturing
    9.
    发明授权
    Turbine blades and methods of manufacturing 有权
    涡轮叶片及制造方法

    公开(公告)号：US08206108B2

    公开(公告)日：2012-06-26

    申请号：US11953489

    申请日：2007-12-10

    申请人： Ardeshir Riahi ,  Kin Poon ,  David Chou ,  Malak F. Malak

    发明人： Ardeshir Riahi ,  Kin Poon ,  David Chou ,  Malak F. Malak

    IPC分类号： F01D5/18

    CPC分类号： F01D5/147 ,  F01D5/18 ,  F01D5/20 ,  F05D2230/10 ,  F05D2230/211 ,  F05D2240/307 ,  Y02T50/676

    摘要： A turbine blade includes a convex suction side wall, a concave pressure side wall, a tip wall, an internal cooling circuit, and a plurality of tip edge channels. The tip wall is recessed from a first tip edge of the suction side wall and a second tip edge of the concave pressure side wall to define a suction side wall tip section and a pressure side wall tip section, and the suction side wall tip section is shorter than the pressure side wall tip section. The internal cooling circuit is formed at least partially between the convex suction side wall, the concave pressure side wall, and the tip wall. The plurality of tip edge channels formed through the first tip edge of the convex suction side wall extend to the internal cooling circuit. Methods of manufacturing turbine blades are also provided.

    摘要翻译： 涡轮叶片包括凸吸入侧壁，凹压侧壁，尖端壁，内部冷却回路和多个尖端边缘通道。 顶壁从吸力侧壁的第一顶端边缘和凹压侧壁的第二顶端边缘凹入，以限定吸入侧壁顶端部分和压力侧壁顶端部分，并且吸力侧壁顶端部分是 比压力侧壁末端部分短。 内部冷却回路至少部分形成在凸吸入侧壁，凹压侧壁与顶壁之间。 通过凸形吸入侧壁的第一顶端边缘形成的多个尖端边缘通道延伸到内部冷却回路。 还提供制造涡轮叶片的方法。

    Gas turbine engine including airfoils having an improved airfoil film cooling configuration and method therefor
    10.
    发明申请
    Gas turbine engine including airfoils having an improved airfoil film cooling configuration and method therefor 失效
    包括具有改进的翼型薄膜冷却配置的翼型件的燃气涡轮发动机及其方法

    公开(公告)号：US20050163609A1

    公开(公告)日：2005-07-28

    申请号：US10766231

    申请日：2004-01-27

    申请人： Ardeshir Riahi ,  Robert McDonald ,  Frederick Borns

    发明人： Ardeshir Riahi ,  Robert McDonald ,  Frederick Borns

    IPC分类号： F01D5/18 ,  F01D5/14

    CPC分类号： F01D5/186 ,  F05D2250/28 ,  F05D2260/202 ,  Y02T50/67 ,  Y02T50/676 ,  Y10T29/49341 ,  Y10T29/49995

    摘要： An airfoil for a gas turbine engine blade includes a plurality of film cooling holes extending through its outer surface. The film cooling holes are formed by defining at least a first datum structure and a second datum structure, and then forming each film cooling hole at a location on the airfoil outer surface relative to the first and second datum structures. As a result, each film cooling hole has a centerline extending therethrough that forms a compound angle with respect to a tangent to the outer surface, and the distance between the centerlines of each film cooling hole is at least a predetermined minimum distance.

    摘要翻译： 用于燃气涡轮发动机叶片的翼型件包括延伸穿过其外表面的多个薄膜冷却孔。 通过限定至少第一基准结构和第二基准结构形成薄膜冷却孔，然后在翼型件外表面上相对于第一和第二基准结构的位置处形成每个薄膜冷却孔。 结果，每个薄膜冷却孔具有穿过其延伸的中心线，其相对于外表面的切线形成复合角度，并且每个薄膜冷却孔的中心线之间的距离至少为预定的最小距离。