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1. 发明授权

US08292587B2 Turbine blade assemblies and methods of manufacturing the same 有权
标题翻译：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。

2. 发明申请

US20100158700A1 TURBINE BLADE ASSEMBLIES AND METHODS OF MANUFACTURING THE SAME 有权
标题翻译：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。

3. 发明授权

US08297935B2 Turbine blades and methods of forming modified turbine blades and turbine rotors 失效
标题翻译：涡轮叶片和形成改进的涡轮叶片和涡轮转子的方法
公开(公告)号：US08297935B2
公开(公告)日：2012-10-30
申请号：US12273108
申请日：2008-11-18
申请人： Bob Mitlin , Mark C. Morris , Steve Halfmann , Ardeshir Riahi
发明人： Bob Mitlin , Mark C. Morris , Steve Halfmann , Ardeshir Riahi
IPC分类号： F01D5/14
CPC分类号： F01D5/30 , F01D5/141 , F01D5/143 , F01D5/18 , Y02T50/673 , Y10T29/49336 , Y10T29/49764
摘要： Turbine blades and methods of forming modified turbine blades and turbine rotors for use in an engine are provided. In an embodiment, by way of example only, a turbine blade includes a platform and an airfoil. The platform includes a surface configured to define a portion of a flowpath, and the surface includes an initial contour configured to plastically deform into an intended final contour after an initial exposure of the blade to an operation of the engine. The airfoil extends from the platform.
摘要翻译：提供涡轮叶片和形成用于发动机的改进的涡轮叶片和涡轮转子的方法。在一个实施例中，仅作为示例，涡轮机叶片包括平台和翼型件。平台包括被配置为限定流路的一部分的表面，并且该表面包括初始轮廓，该初始轮廓被配置为在叶片初始暴露于发动机的操作之后塑造变形成预定的最终轮廓。机翼从平台延伸。

4. 发明申请

US20100284819A1 TURBINE BLADES AND METHODS OF FORMING MODIFIED TURBINE BLADES AND TURBINE ROTORS 失效
标题翻译：涡轮叶片及形成改装式涡轮叶片及涡轮转子的方法
公开(公告)号：US20100284819A1
公开(公告)日：2010-11-11
申请号：US12273108
申请日：2008-11-18
申请人： Bob Mitlin , Mark C. Morris , Steve Halfmann , Ardeshir Riahi
发明人： Bob Mitlin , Mark C. Morris , Steve Halfmann , Ardeshir Riahi
IPC分类号： F01D5/14 , B23P15/02
CPC分类号： F01D5/30 , F01D5/141 , F01D5/143 , F01D5/18 , Y02T50/673 , Y10T29/49336 , Y10T29/49764
摘要： Turbine blades and methods of forming modified turbine blades and turbine rotors for use in an engine are provided. In an embodiment, by way of example only, a turbine blade includes a platform and an airfoil. The platform includes a surface configured to define a portion of a flowpath, and the surface includes an initial contour configured to plastically deform into an intended final contour after an initial exposure of the blade to an operation of the engine. The airfoil extends from the platform.
摘要翻译：提供涡轮叶片和形成用于发动机的改进的涡轮叶片和涡轮转子的方法。在一个实施例中，仅作为示例，涡轮机叶片包括平台和翼型件。平台包括被配置为限定流路的一部分的表面，并且该表面包括初始轮廓，该初始轮廓被配置为在叶片初始暴露于发动机的操作之后塑造变形成预定的最终轮廓。机翼从平台延伸。

5. 发明申请

US20130051974A1 GAS TURBINE ENGINES AND METHODS FOR COOLING COMPONENTS THEREOF WITH MID-IMPELLER BLEED COOLING AIR 审中-公开
标题翻译：气体涡轮发动机及其与中间桨叶冷却空气冷却组件的方法
公开(公告)号：US20130051974A1
公开(公告)日：2013-02-28
申请号：US13218224
申请日：2011-08-25
申请人： Kin Poon , Jeff Howe , Michael T. Todd Barton , Frank Mignano , Mahmoud Mansour , Nick Nolcheff , Scott Taylor , Steve Trzcinski , Ardeshir Riahi , Jeff Guymon , Alan Hemmingson , Alex Mirzamoghadam
发明人： Kin Poon , Jeff Howe , Michael T. Todd Barton , Frank Mignano , Mahmoud Mansour , Nick Nolcheff , Scott Taylor , Steve Trzcinski , Ardeshir Riahi , Jeff Guymon , Alan Hemmingson , Alex Mirzamoghadam
IPC分类号： F04D27/02 , F01D5/08
CPC分类号： F01D25/14 , F04D29/162 , F04D29/4206
摘要： Gas turbine engines and methods for cooling components thereof with mid-impeller bleed (MIB) cooling air having a pressure are provided. The gas turbine engine has a compressor comprising an impeller body and an impeller shroud at least partially surrounding the impeller body. The impeller shroud has a plurality of MIB openings disposed therein. At least one edge treatment is provided thereto. The edge treatment substantially preserves pressure of the cooling air during entrance into and discharge out of the MIB opening. The plurality of MIB openings may be extended MIB openings in a thickened impeller shroud. The centerline of the MIB openings may be oriented to be substantially aligned with an averaged local absolute flow velocity vector of the cooling air at the inlet section of the MIB opening in order to extract cooling air in a direction that has a vector component in a tangential, an axial, and a radial flow direction.
摘要翻译：提供了燃气涡轮发动机及其具有中间叶轮排出（MIB）冷却空气的组件的组件的压力。燃气涡轮发动机具有压缩机，该压缩机包括至少部分地围绕叶轮本体的叶轮本体和叶轮护罩。叶轮护罩具有设置在其中的多个MIB开口。向其提供至少一个边缘处理。边缘处理在进入和排出MIB开口时基本上保持冷却空气的压力。多个MIB开口可以在增厚的叶轮护罩中延伸MIB开口。 MIB开口的中心线可以被定向为与MIB开口的入口部分处的冷却空气的平均局部绝对流速矢量基本对齐，以便沿着具有向心分量的向量分量的方向提取冷却空气，轴向和径向流动方向。

6. 发明授权

US08206108B2 Turbine blades and methods of manufacturing 有权
标题翻译：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。

7. 发明申请

US20120070307A1 TURBINE BLADES, TURBINE ASSEMBLIES, AND METHODS OF MANUFACTURING TURBINE BLADES 有权
标题翻译：涡轮叶片，涡轮组件及制造涡轮叶片的方法
公开(公告)号：US20120070307A1
公开(公告)日：2012-03-22
申请号：US12888202
申请日：2010-09-22
申请人： Kin Poon , Malak Fouad Malak , Ardeshir Riahi , David Chou
发明人： Kin Poon , Malak Fouad Malak , Ardeshir Riahi , David Chou
IPC分类号： F01D5/18 , B22D27/02 , B23P15/02 , B22D25/02
CPC分类号： F01D5/20 , F01D5/187 , Y02T50/673 , Y02T50/676 , Y10T29/49341
摘要： A turbine blade includes a first side wall including a first tip edge, a second side wall opposite the first side wall and including a second tip edge, a tip wall between the first and second side walls, the tip wall recessed from the first tip edge of the first side wall and the second tip edge of the second side wall forming a coolant cavity, a tip recess cavity, a first parapet wall on the first side wall, and a second parapet wall on the second side wall, the coolant cavity defined by the tip wall, and the tip recess cavity defined by the tip wall, and the first and second parapet walls, a step formed between the first tip edge and the tip wall, a cooling hole through the first parapet wall, the step, and the tip wall, the cooling hole including an open and a closed channel section.
摘要翻译：涡轮叶片包括第一侧壁，其包括第一末端边缘，与第一侧壁相对的第二侧壁，并且包括第二末端边缘，位于第一和第二侧壁之间的末端壁，所述第一侧壁和所述第二侧壁的所述第二末端边缘形成冷却剂腔，所述顶部凹陷空腔，所述第一侧壁上的第一栏杆壁和所述第二侧壁上的第二护墙壁，所述冷却剂腔被限定由尖端壁和由尖端壁限定的尖端凹部空腔以及第一和第二护墙壁，在第一顶端边缘和尖端壁之间形成的台阶，穿过第一栏杆壁的冷却孔，台阶和尖端壁，冷却孔包括开放和封闭的通道部分。

8. 发明申请

US20090148305A1 TURBINE BLADES AND METHODS OF MANUFACTURING 有权
标题翻译：涡轮叶片及制造方法
公开(公告)号：US20090148305A1
公开(公告)日：2009-06-11
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，以限定吸力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。

9. 发明授权

US08777567B2 Turbine blades, turbine assemblies, and methods of manufacturing turbine blades 有权
标题翻译：涡轮叶片，涡轮组件以及制造涡轮叶片的方法
公开(公告)号：US08777567B2
公开(公告)日：2014-07-15
申请号：US12888202
申请日：2010-09-22
申请人： Kin Poon , Malak Fouad Malak , Ardeshir Riahi , David Chou
发明人： Kin Poon , Malak Fouad Malak , Ardeshir Riahi , David Chou
IPC分类号： F01D5/20 , F01D5/18
CPC分类号： F01D5/20 , F01D5/187 , Y02T50/673 , Y02T50/676 , Y10T29/49341
摘要： A turbine blade includes a first side wall including a first tip edge, a second side wall opposite the first side wall and including a second tip edge, a tip wall between the first and second side walls, the tip wall recessed from the first tip edge of the first side wall and the second tip edge of the second side wall forming a coolant cavity, a tip recess cavity, a first parapet wall on the first side wall, and a second parapet wall on the second side wall, the coolant cavity defined by the tip wall, and the tip recess cavity defined by the tip wall, and the first and second parapet walls, a step formed between the first tip edge and the tip wall, a cooling hole through the first parapet wall, the step, and the tip wall, the cooling hole including an open and a closed channel section.
摘要翻译：涡轮叶片包括第一侧壁，其包括第一末端边缘，与第一侧壁相对的第二侧壁，并且包括第二末端边缘，位于第一和第二侧壁之间的末端壁，所述第一侧壁和所述第二侧壁的所述第二末端边缘形成冷却剂腔，所述顶部凹陷空腔，所述第一侧壁上的第一栏杆壁和所述第二侧壁上的第二护墙壁，所述冷却剂腔被限定由尖端壁和由尖端壁限定的尖端凹部空腔以及第一和第二护墙壁，在第一顶端边缘和尖端壁之间形成的台阶，穿过第一栏杆壁的冷却孔，台阶和尖端壁，冷却孔包括开放和封闭的通道部分。

10. 发明授权

US08292581B2 Air cooled turbine blades and methods of manufacturing 有权
标题翻译：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。

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