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。

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。

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。

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。

公开(公告)号：US20120148406A1

公开(公告)日：2012-06-14

申请号：US12966694

申请日：2010-12-13

申请人： Steve Halfmann ,  Daniel Cregg Crites ,  Malak Fouad Malak ,  Mark C. Morris ,  Ardeshir Riahi ,  Brandan Wakefield

发明人： Steve Halfmann ,  Daniel Cregg Crites ,  Malak Fouad Malak ,  Mark C. Morris ,  Ardeshir Riahi ,  Brandan Wakefield

IPC分类号： F01D5/08

CPC分类号： F01D5/085 ,  F01D5/088 ,  F01D5/3007 ,  F05D2240/81 ,  Y02T50/676

摘要： A turbine rotor disk is provided. The turbine rotor disk includes a hub, a ring attached to the hub, the ring including a plurality of posts extending radially outwardly and disposed around a circumference of the ring, each post including a first radially-extending face, a second radially-extending face, and a blade attachment surface extending axially between the first and second radially-extending faces, a main cooling air feed channel formed in each post and extending from the first radially-extending face toward the second radially-extending face, and a plurality of ancillary jet openings formed in each post and extending from the main cooling air feed channel to the blade attachment surface.

摘要翻译： 提供涡轮转子盘。 涡轮转子盘包括轮毂，附接到毂的环，环包括径向向外延伸并围绕环的圆周设置的多个柱，每个柱包括第一径向延伸面，第二径向延伸面 以及在第一和第二径向延伸面之间轴向延伸的刀片附接表面，形成在每个柱中并从第一径向延伸面朝向第二径向延伸面延伸的主冷却空气供给通道，以及多个辅助 在每个柱中形成并且从主冷却空气供给通道延伸到叶片附接表面的喷射开口。

公开(公告)号：US06554562B2

公开(公告)日：2003-04-29

申请号：US09882518

申请日：2001-06-15

申请人： Rodolphe Dudebout ,  Mark C. Morris ,  Douglas P. Freiberg ,  Craig W. McKeever ,  Richard J. Musiol ,  Ardeshir Riahi ,  William J. Howe

发明人： Rodolphe Dudebout ,  Mark C. Morris ,  Douglas P. Freiberg ,  Craig W. McKeever ,  Richard J. Musiol ,  Ardeshir Riahi ,  William J. Howe

IPC分类号： F01D904

CPC分类号： F01D5/142 ,  F01D9/04 ,  Y02T50/673

摘要： A method and apparatus to reduce the average and maximum temperatures to which the nozzles in the hot-section of gas-turbine engine are subjected is described. The method relates to the circumferential alignment of fuel nozzles and downstream turbine nozzles in a gas turbine engine. This situates the hot-streak emerging from each fuel nozzle in between the like-numbered turbine nozzle airfoils. The most severe operating condition for reducing the durability of nozzle airfoils is the one generating hot operating temperature conditions. By identifying the temperature profile passing through downstream nozzle airfoils, airfoils in static stages can be selectively spaced around the circumference of the ring attached to the casing of the gas turbine engine to avoid high temperature exposure to the airfoils. This method and apparatus mitigates the worst oxidation and thermo-mechanical fatigue damage in the airfoils by allowing the hot gas regions to pass through the path in between two adjacent airfoils.

摘要翻译： 描述了一种降低燃气涡轮发动机的热段中的喷嘴的平均温度和最高温度的方法和装置。 该方法涉及燃气涡轮发动机中的燃料喷嘴和下游涡轮喷嘴的圆周对准。 这使得从每个燃料喷嘴出现的热条之间位于相同数量的涡轮喷嘴翼型之间。 用于降低喷嘴翼型的耐用性的最严苛的操作条件是产生热操作温度条件的操作条件。 通过识别通过下游喷嘴翼型件的温度曲线，静态阶段的翼型件可以围绕附接到燃气涡轮发动机的壳体的环的圆周选择性间隔开，以避免高温暴露于翼型件。 该方法和装置通过允许热气体区域穿过两个相邻翼型之间的路径来减轻翼型件中最差的氧化和热机械疲劳损伤。

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。

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。

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。

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。