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1. 发明授权

US08880105B2 Method and system for localization 有权
标题翻译：本地化方法和系统
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。

2. 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。

3. 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。

4. 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。

5. 发明申请

US20130172020A1 METHOD AND SYSTEM FOR LOCALIZATION 有权
标题翻译：用于本地化的方法和系统
公开(公告)号：US20130172020A1
公开(公告)日：2013-07-04
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 , H04W4/04
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。

6. 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。

7. 发明授权

US07625178B2 High effectiveness cooled turbine blade 失效
标题翻译：高效冷却涡轮叶片
公开(公告)号：US07625178B2
公开(公告)日：2009-12-01
申请号：US11513759
申请日：2006-08-30
申请人： Mark C. Morris , George W. Wolfmeyer , Luis A. Tapia , Vivek Agarwal , Kin Poon , Jason C. Smoke , William C. Baker , Henry M. Armstrong
发明人： Mark C. Morris , George W. Wolfmeyer , Luis A. Tapia , Vivek Agarwal , Kin Poon , Jason C. Smoke , William C. Baker , Henry M. Armstrong
IPC分类号： F01D5/08
CPC分类号： F01D5/187 , B22C7/02 , B22C9/04 , B22C9/10 , F05D2230/211 , F05D2260/202 , F05D2260/2212 , F05D2260/22141 , Y02T50/676 , Y10T29/49336 , Y10T29/49339 , Y10T29/49341
摘要： An air-cooled turbine blade is provided having an airfoil shape defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root and a tip, the walls and the tip each including an interior surface that defines an interior with the root, the trailing edge including a plurality of slots formed thereon. The blade includes a suction side flow circuit formed therein comprising a forward and an aft flow circuit. The blade also includes a tip flow circuit extending along the tip interior surface to at least one of the trailing edge slots and including a first and a second opening, the first opening in flow communication with the suction side forward flow circuit outlet, and the second opening in flow communication with a cross-over hole of the suction side aft flow circuit. Methods of manufacturing the blade are also provided.
摘要翻译：本发明提供一种风冷式涡轮机叶片，其具有由凸形的吸入侧壁，凹入压力侧壁，前缘，后缘，根部和尖端形成的翼面形状，所述壁和端部各自包括内表面其限定具有根部的内部，所述后缘包括形成在其上的多个狭槽。叶片包括形成在其中的吸入侧流动回路，包括前进和后部流动回路。叶片还包括尖端流动回路，其沿着尖端内表面延伸到至少一个后缘槽，并且包括第一和第二开口，第一开口与吸力侧向前流动回路出口流动连通，打开与吸入侧后流道的交叉孔流动连通。还提供了制造叶片的方法。

8. 发明申请

US20080056908A1 High effectiveness cooled turbine blade 失效
标题翻译：高效冷却涡轮叶片
公开(公告)号：US20080056908A1
公开(公告)日：2008-03-06
申请号：US11513759
申请日：2006-08-30
申请人： Mark C. Morris , George W. Wolfmeyer , Luis A. Tapia , Vivek Agarwal , Kin Poon , Jason C. Smoke , William C. Baker , Henry M. Armstrong
发明人： Mark C. Morris , George W. Wolfmeyer , Luis A. Tapia , Vivek Agarwal , Kin Poon , Jason C. Smoke , William C. Baker , Henry M. Armstrong
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , B22C7/02 , B22C9/04 , B22C9/10 , F05D2230/211 , F05D2260/202 , F05D2260/2212 , F05D2260/22141 , Y02T50/676 , Y10T29/49336 , Y10T29/49339 , Y10T29/49341
摘要： An air-cooled turbine blade is provided having an airfoil shape defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root and a tip, the walls and the tip each including an interior surface that defines an interior with the root, the trailing edge including a plurality of slots formed thereon. The blade includes a suction side flow circuit formed therein comprising a forward and an aft flow circuit. The blade also includes a tip flow circuit extending along the tip interior surface to at least one of the trailing edge slots and including a first and a second opening, the first opening in flow communication with the suction side forward flow circuit outlet, and the second opening in flow communication with a cross-over hole of the suction side aft flow circuit. Methods of manufacturing the blade are also provided.
摘要翻译：本发明提供一种风冷式涡轮机叶片，其具有由凸形的吸入侧壁，凹入压力侧壁，前缘，后缘，根部和尖端形成的翼面形状，所述壁和端部各自包括内表面其限定具有根部的内部，所述后缘包括形成在其上的多个狭槽。叶片包括形成在其中的吸入侧流动回路，包括前进和后部流动回路。叶片还包括尖端流动回路，其沿着尖端内表面延伸到至少一个后缘槽，并且包括第一和第二开口，第一开口与吸力侧向前流动回路出口流动连通，打开与吸入侧后流道的交叉孔流动连通。还提供了制造叶片的方法。

9. 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。

10. 发明申请

US20050235651A1 Gas turbine engine including a low pressure sump seal buffer source and thermally isolated sump 失效
标题翻译：燃气涡轮发动机包括低压油底壳密封缓冲源和热隔离油底壳
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。

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