公开(公告)号：US06478535B1

公开(公告)日：2002-11-12

申请号：US09848844

申请日：2001-05-04

申请人： Vincent Chung ,  Milton Ortiz ,  Kin Poon

发明人： Vincent Chung ,  Milton Ortiz ,  Kin Poon

IPC分类号： F01D518

CPC分类号： F01D5/187 ,  F05D2260/202 ,  Y02T50/67 ,  Y02T50/672 ,  Y02T50/676

摘要： A thin wall cooling system has multiple in-wall channels traversing a thin wall structure such as the wall of a gas turbine engine blade or vane. The blade has a hollow interior that may be divided into multiple cavities. Coolant is introduced into an entry opening of each in-wall channel and then discharged through exit openings into the vane cavities. The coolant then exits the cavities by through wall channels to discharge the coolant to form a cool air film on the external surface of the blade. This combination allows improved cooling control for structures that experience an elevated temperature environment, as for example, the flow of hot gas across the exterior surface of a gas turbine engine blade.

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：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。

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：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：US20050235651A1

公开(公告)日：2005-10-27

申请号：US10830265

申请日：2004-04-21

申请人： Mark Morris ,  Alan Tiltman ,  Kin Poon ,  Bradley Volkmann

发明人： Mark Morris ,  Alan Tiltman ,  Kin Poon ,  Bradley Volkmann

IPC分类号： F01D25/12 ,  F01D25/18 ,  F02C7/06 ,  F02C7/28

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：US08880105B2

公开(公告)日：2014-11-04

申请号：US13339777

申请日：2011-12-29

申请人： James Aweya ,  Nayef Alsindi ,  Kin Poon

发明人： James Aweya ,  Nayef Alsindi ,  Kin Poon

IPC分类号： H04W24/00

CPC分类号： G01S5/0252

摘要： This invention relates to methods and devices for entropy-based location fingerprinting, in particular for use over wireless local-area networks (WLANs). The invention has particular application in localization for indoor environments. In embodiments of the invention, an entropy-based fingerprint is determined at a number of predetermined locations within the desired area of localization during an off-line phase and subsequently used in an on-line mode to determine the location of a receiver. In particular embodiments, the fingerprint is a vector of entropy estimates of the channel transfer function (CTF) between a mobile terminal and all access points within coverage. The invention seeks to provide a fingerprinting localization solution that has a simplicity of structure, leading to advantages in storage and pattern recognition requirements, and robustness by proving a unique measure of information that is related to the channel experienced at the location of the mobile terminal.

摘要翻译： 本发明涉及用于基于熵的位置指纹的方法和装置，特别是用于无线局域网（WLAN）上。 本发明在室内环境的定位中具有特别的应用。 在本发明的实施例中，在离线阶段期间，在所需的定位区域内的多个预定位置处确定基于熵的指纹，并随后以在线模式使用以确定接收机的位置。 在特定实施例中，指纹是移动终端与覆盖范围内的所有接入点之间的信道传递函数（CTF）的熵估计的向量。 本发明寻求提供一种指纹定位解决方案，其具有简单的结构，通过证明与在移动终端的位置处经历的信道相关的信息的独特测量，可以获得存储和模式识别要求的优势以及鲁棒性。

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。