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：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。

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。

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。

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。

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。

公开(公告)号：US20110299972A1

公开(公告)日：2011-12-08

申请号：US12794433

申请日：2010-06-04

申请人： Mark C. Morris ,  Alexander MirzaMoghadam ,  Khosro Molla Hosseini ,  Kin Poon ,  Jeff Howe ,  Alan G. Tiltman

发明人： Mark C. Morris ,  Alexander MirzaMoghadam ,  Khosro Molla Hosseini ,  Kin Poon ,  Jeff Howe ,  Alan G. Tiltman

IPC分类号： F01D1/00

CPC分类号： F01D3/025

摘要： An impeller or axial stage compressor disk backface shroud for use with a gas turbine engine is disclosed. The backface shroud includes, but is not limited to, a substantially funnel shaped body having a surface. The substantially funnel shaped body is configured to be statically mounted to the gas turbine engine substantially coaxially with the impeller or axial stage compressor disk. The surface and a backface of the impeller or axial stage compressor disk form a cavity that guides an airflow portion to a turbine when the substantially funnel shaped body is mounted coaxially with the impeller or axial stage compressor disk and axially spaced apart therefrom. The airflow portion has a tangential velocity and a recessed groove in the surface of the backface shroud is oriented generally transversely to the tangential velocity to at least partially interfere with the airflow portion, thus affecting static pressure in the cavity.

摘要翻译： 公开了一种用于燃气涡轮发动机的叶轮或轴向级压缩机盘背面罩。 背面护罩包括但不限于具有表面的大致漏斗形的主体。 基本上漏斗形的主体构造成与叶轮或轴向级压缩机盘基本上同轴地静态地安装到燃气涡轮发动机。 当基本上漏斗形的主体与叶轮或轴向级压缩机盘同轴地安装并且与其轴向间隔开时，叶轮或轴向级压缩机盘的表面和背面形成空腔，该空腔将气流部分引导到涡轮机。 气流部分具有切向速度，并且背面护罩的表面中的凹槽通常横向于切向速度定向，以至少部分地干扰气流部分，从而影响空腔中的静压力。

公开(公告)号：US07093418B2

公开(公告)日：2006-08-22

申请号：US10830265

申请日：2004-04-21

申请人： Mark C. Morris ,  Alan G. Tiltman ,  Kin Poon ,  Bradley A. Volkmann

发明人： Mark C. Morris ,  Alan G. Tiltman ,  Kin Poon ,  Bradley A. Volkmann

IPC分类号： F02C7/28 ,  F02C7/06 ,  F02G3/00

CPC分类号： F01D25/125 ,  F01D25/18 ,  F02C7/28 ,  F05D2240/50 ,  F05D2260/231 ,  Y02T50/675

摘要： A gas turbine engine is configured to use relatively cool, low pressure air discharged from a low pressure compressor to supply buffer air to lubrication sump seals. The engine is further configured such that the lubrication sump is thermally layered by isolating relatively hot, high pressure compressor air from the sump by utilizing a warm vent mixing cavity, which is located radially between of the hot high pressure compressor air and the cool buffer air, which is located in a buffer cavity between the vent cavity and the sump.

摘要翻译： 燃气涡轮发动机被配置为使用从低压压缩机排放的相对冷却的低压空气将缓冲空气供应到润滑油底壳密封件。 发动机进一步构造成使得通过利用位于热高压压缩机空气和冷却缓冲空气之间的温热排气混合空腔来分离相对较热的高压压缩机空气，从而将润滑油池分层 ，其位于通气腔和贮槽之间的缓冲腔中。

公开(公告)号：US08801364B2

公开(公告)日：2014-08-12

申请号：US12794433

申请日：2010-06-04

申请人： Mark C. Morris ,  Alexander MirzaMoghadam ,  Khosro Molla Hosseini ,  Kin Poon ,  Jeff Howe ,  Alan G. Tiltman

发明人： Mark C. Morris ,  Alexander MirzaMoghadam ,  Khosro Molla Hosseini ,  Kin Poon ,  Jeff Howe ,  Alan G. Tiltman

IPC分类号： F01D3/00

CPC分类号： F01D3/025

摘要： An impeller or axial stage compressor disk backface shroud for use with a gas turbine engine is disclosed. The backface shroud includes, but is not limited to, a substantially funnel shaped body having a surface. The substantially funnel shaped body is configured to be statically mounted to the gas turbine engine substantially coaxially with the impeller or axial stage compressor disk. The surface and a backface of the impeller or axial stage compressor disk form a cavity that guides an airflow portion to a turbine when the substantially funnel shaped body is mounted coaxially with the impeller or axial stage compressor disk and axially spaced apart therefrom. The airflow portion has a tangential velocity and a recessed groove in the surface of the backface shroud is oriented generally transversely to the tangential velocity to at least partially interfere with the airflow portion, thus affecting static pressure in the cavity.

摘要翻译： 公开了一种用于燃气涡轮发动机的叶轮或轴向级压缩机盘背面罩。 背面护罩包括但不限于具有表面的大致漏斗形的主体。 基本上漏斗形的主体构造成与叶轮或轴向级压缩机盘基本上同轴地静态地安装到燃气涡轮发动机。 当基本上漏斗形的主体与叶轮或轴向级压缩机盘同轴地安装并且与其轴向间隔开时，叶轮或轴向级压缩机盘的表面和背面形成空腔，该空腔将气流部分引导到涡轮机。 气流部分具有切向速度，并且背面护罩的表面中的凹槽通常横向于切向速度定向，以至少部分地干扰气流部分，从而影响空腔中的静压力。