利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

10 条记录 (耗时 0.028 秒)

    Air cooled turbine blades and methods of manufacturing
    3.
    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
    4.
    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
    5.
    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。

    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 assemblies with impingement cooling
    7.
    发明授权
    Turbine assemblies with impingement cooling 有权
    具有冲击冷却的涡轮机组件

    公开(公告)号：US08616832B2

    公开(公告)日：2013-12-31

    申请号：US12627609

    申请日：2009-11-30

    申请人： Jason Smoke ,  Bradley Reed Tucker ,  Bob Mitlin ,  Dan Crites ,  Rajiv Rana ,  Alexander MirzaMoghadam

    发明人： Jason Smoke ,  Bradley Reed Tucker ,  Bob Mitlin ,  Dan Crites ,  Rajiv Rana ,  Alexander MirzaMoghadam

    IPC分类号： F01D5/14

    CPC分类号： F01D5/087 ,  F01D5/187 ,  F05D2240/81 ,  F05D2260/201 ,  Y02T50/676

    摘要： A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path; a stator assembly with a stator vane extending into the mainstream gas flow; and a turbine rotor assembly upstream of the stator assembly and defining a turbine cavity with the stator assembly. The turbine rotor assembly includes a rotor disk having a forward side and an aft side, a rotor platform positioned on a periphery of the rotor disk, the rotor platform defining an aft flow discourager, a rotor blade mounted on the rotor platform extending into the mainstream gas flow, and an aft seal plate mounted on the aft side of the rotor disk. The aft seal plate has a radius such that the aft seal plate protects the rotor disk from hot gas ingestion.

    摘要翻译： 燃气涡轮发动机组件包括壳体，该壳体包括至少部分地限定主流热气体流动路径的环形管道壁; 具有延伸到主流气流中的定子叶片的定子组件; 以及在定子组件上游的涡轮转子组件，并且与定子组件限定涡轮机空腔。 涡轮转子组件包括具有前侧和后侧的转子盘，位于转子盘的周边上的转子平台，转子平台限定了后流动盘旋器，安装在转子平台上的转子叶片延伸到主流 气流和安装在转子盘的后侧的后密封板。 尾部密封板具有使得后部密封板保护转子盘免受热气体摄取的半径。

    TURBINE ASSEMBLIES WITH IMPINGEMENT COOLING
    8.
    发明申请
    TURBINE ASSEMBLIES WITH IMPINGEMENT COOLING 有权
    涡轮组件与冲击冷却

    公开(公告)号：US20110129342A1

    公开(公告)日：2011-06-02

    申请号：US12627609

    申请日：2009-11-30

    申请人： Jason Smoke ,  Bradley Reed Tucker ,  Bob Mitlin ,  Dan Crites ,  Rajiv Rana ,  Alexander MirzaMoghadam

    发明人： Jason Smoke ,  Bradley Reed Tucker ,  Bob Mitlin ,  Dan Crites ,  Rajiv Rana ,  Alexander MirzaMoghadam

    IPC分类号： F01D5/08

    CPC分类号： F01D5/087 ,  F01D5/187 ,  F05D2240/81 ,  F05D2260/201 ,  Y02T50/676

    摘要： A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path; a stator assembly with a stator vane extending into the mainstream gas flow; and a turbine rotor assembly upstream of the stator assembly and defining a turbine cavity with the stator assembly. The turbine rotor assembly includes a rotor disk having a forward side and an aft side, a rotor platform positioned on a periphery of the rotor disk, the rotor platform defining an aft flow discourager, a rotor blade mounted on the rotor platform extending into the mainstream gas flow, and an aft seal plate mounted on the aft side of the rotor disk. The aft seal plate has a radius such that the aft seal plate protects the rotor disk from hot gas ingestion.

    摘要翻译： 燃气涡轮发动机组件包括壳体，该壳体包括至少部分地限定主流热气体流动路径的环形管道壁; 具有延伸到主流气流中的定子叶片的定子组件; 以及在定子组件上游的涡轮转子组件，并且与定子组件限定涡轮机空腔。 涡轮转子组件包括具有前侧和后侧的转子盘，位于转子盘的周边上的转子平台，转子平台限定了后流动盘旋器，安装在转子平台上的转子叶片延伸到主流 气流和安装在转子盘的后侧的后密封板。 尾部密封板具有使得后部密封板保护转子盘免受热气体摄取的半径。