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1. 发明授权

US08814518B2 Apparatus and methods for cooling platform regions of turbine rotor blades 有权
标题翻译：涡轮转子叶片冷却平台区域的装置和方法
公开(公告)号：US08814518B2
公开(公告)日：2014-08-26
申请号：US12915477
申请日：2010-10-29
申请人： John Wesley Harris, Jr. , Craig Allen Bielek , Scott Edmond Ellis , Xiaoyong Fu
发明人： John Wesley Harris, Jr. , Craig Allen Bielek , Scott Edmond Ellis , Xiaoyong Fu
IPC分类号： F01D5/18
CPC分类号： F01D5/081 , F01D5/18 , F05D2240/81 , F05D2260/22141 , Y02T50/676
摘要： A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the rotor blade includes an interior cooling passage that extends from a connection at the root to the approximate radial height of the platform, wherein, the interior cooling passage comprises a high-pressure coolant region and a low-pressure coolant region, and wherein a pressure side of the platform comprises a topside extending circumferentially from the airfoil to a pressure side slashface. The platform cooling arrangement may include: a platform cavity formed within the pressure side of the platform, a high-pressure connector that connects the platform cavity to the high-pressure coolant region of the interior cooling passage; a low-pressure connector that connects the platform cavity to the low-pressure coolant region of the interior cooling passage; and a pin bank formed within the platform cavity that includes radial pins.
摘要翻译：涡轮转子叶片中的平台冷却装置，其具有在翼型件和根部之间的界面处的平台，其中所述转子叶片包括从根部的连接部延伸到所述平台的近似径向高度的内部冷却通道，内部冷却通道包括高压冷却剂区域和低压冷却剂区域，并且其中平台的压力侧包括从翼面周向延伸到压力侧斜面的顶侧。平台冷却装置可以包括：形成在平台的压力侧内的平台空腔，将平台空腔连接到内部冷却通道的高压冷却剂区域的高压连接器; 将平台腔连接到内部冷却通道的低压冷却剂区域的低压连接器; 以及形成在所述平台腔内的销排，所述销组包括径向销。

2. 发明申请

US20120156055A1 APPARATUS AND METHODS FOR COOLING PLATFORM REGIONS OF TURBINE ROTOR BLADES 有权
标题翻译：用于冷却涡轮转子叶片平台区域的装置和方法
公开(公告)号：US20120156055A1
公开(公告)日：2012-06-21
申请号：US12972835
申请日：2010-12-20
申请人： John Wesley Harris, JR. , Craig Allen Bielek , Scott Edmond Ellis , Daniel Alan Hynum , Melissa Ann Seely , Xiaoyong Fu
发明人： John Wesley Harris, JR. , Craig Allen Bielek , Scott Edmond Ellis , Daniel Alan Hynum , Melissa Ann Seely , Xiaoyong Fu
IPC分类号： F01D5/18 , B23P15/02
CPC分类号： F01D5/187 , F01D5/087 , F05D2240/81 , F05D2250/185 , Y02T50/671 , Y02T50/676 , Y10T29/49341
摘要： A configuration of cooling channels through the interior of a turbine rotor blade, the turbine rotor blade including a platform at an interface between an airfoil and a root. In one embodiment, the configuration of cooling channels includes: an interior cooling passage that is configured to extend from a connection with a coolant source in the root to the interior of the airfoil; a platform cooling channel that traverses at least a portion of the platform; a turndown extension that includes a first section, which comprises a connection with the platform cooling channel, and a second section, which comprises a radially oriented cooling channel; and a connector that extends from a connector opening formed through an outer face of the root to a connection with the interior cooling passage and, therebetween, bisects the second section of the turndown extension.
摘要翻译：通过涡轮转子叶片的内部的冷却通道的构造，涡轮转子叶片包括在翼型件和根部之间的界面处的平台。在一个实施例中，冷却通道的构造包括：内部冷却通道，其构造成从与根部中的冷却剂源的连接延伸到翼型件的内部; 平台冷却通道，其横穿所述平台的至少一部分; 包括与所述平台冷却通道的连接的第一部分和包括径向定向的冷却通道的第二部分的调节延伸部; 以及连接器，该连接器从形成为通过根部的外表面的连接器开口延伸到与内部冷却通道的连接，并且在两者之间平分调节延伸部分的第二部分。

3. 发明申请

US20120107134A1 APPARATUS AND METHODS FOR COOLING PLATFORM REGIONS OF TURBINE ROTOR BLADES 有权
标题翻译：用于冷却涡轮转子叶片平台区域的装置和方法
公开(公告)号：US20120107134A1
公开(公告)日：2012-05-03
申请号：US12915477
申请日：2010-10-29
申请人： John Wesley Harris, JR. , Craig Allen Bielek , Scott Edmond Ellis , Xiaoyong Fu
发明人： John Wesley Harris, JR. , Craig Allen Bielek , Scott Edmond Ellis , Xiaoyong Fu
IPC分类号： F01D5/18 , B23P15/02
CPC分类号： F01D5/081 , F01D5/18 , F05D2240/81 , F05D2260/22141 , Y02T50/676
摘要： A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the rotor blade includes an interior cooling passage that extends from a connection at the root to the approximate radial height of the platform, wherein, the interior cooling passage comprises a high-pressure coolant region and a low-pressure coolant region, and wherein a pressure side of the platform comprises a topside extending circumferentially from the airfoil to a pressure side slashface. The platform cooling arrangement may include: a platform cavity formed within the pressure side of the platform, a high-pressure connector that connects the platform cavity to the high-pressure coolant region of the interior cooling passage; a low-pressure connector that connects the platform cavity to the low-pressure coolant region of the interior cooling passage; and a pin bank formed within the platform cavity that includes radial pins.
摘要翻译：涡轮转子叶片中的平台冷却装置，其具有在翼型件和根部之间的界面处的平台，其中所述转子叶片包括从根部的连接部延伸到所述平台的近似径向高度的内部冷却通道，内部冷却通道包括高压冷却剂区域和低压冷却剂区域，并且其中平台的压力侧包括从翼面周向延伸到压力侧斜面的顶侧。平台冷却装置可以包括：形成在平台的压力侧内的平台空腔，将平台空腔连接到内部冷却通道的高压冷却剂区域的高压连接器; 将平台腔连接到内部冷却通道的低压冷却剂区域的低压连接器; 以及形成在所述平台腔内的销排，所述销组包括径向销。

4. 发明授权

US08636471B2 Apparatus and methods for cooling platform regions of turbine rotor blades 有权
标题翻译：涡轮转子叶片冷却平台区域的装置和方法
公开(公告)号：US08636471B2
公开(公告)日：2014-01-28
申请号：US12972835
申请日：2010-12-20
申请人： John Wesley Harris, Jr. , Craig Allen Bielek , Scott Edmond Ellis , Daniel Alan Hynum , Melissa Ann Seely , Xiaoyong Fu
发明人： John Wesley Harris, Jr. , Craig Allen Bielek , Scott Edmond Ellis , Daniel Alan Hynum , Melissa Ann Seely , Xiaoyong Fu
IPC分类号： F01D5/18 , F01D5/08
CPC分类号： F01D5/187 , F01D5/087 , F05D2240/81 , F05D2250/185 , Y02T50/671 , Y02T50/676 , Y10T29/49341
摘要： A configuration of cooling channels through the interior of a turbine rotor blade, the turbine rotor blade including a platform at an interface between an airfoil and a root. In one embodiment, the configuration of cooling channels includes: an interior cooling passage that is configured to extend from a connection with a coolant source in the root to the interior of the airfoil; a platform cooling channel that traverses at least a portion of the platform; a turndown extension that includes a first section, which comprises a connection with the platform cooling channel, and a second section, which comprises a radially oriented cooling channel; and a connector that extends from a connector opening formed through an outer face of the root to a connection with the interior cooling passage and, therebetween, bisects the second section of the turndown extension.
摘要翻译：通过涡轮转子叶片的内部的冷却通道的构造，涡轮转子叶片包括在翼型件和根部之间的界面处的平台。在一个实施例中，冷却通道的构造包括：内部冷却通道，其构造成从与根部中的冷却剂源的连接延伸到翼型件的内部; 平台冷却通道，其横穿所述平台的至少一部分; 包括与所述平台冷却通道的连接的第一部分和包括径向定向的冷却通道的第二部分的调节延伸部; 以及连接器，该连接器从形成为通过根部的外表面的连接器开口延伸到与内部冷却通道的连接，并且在两者之间平分调节延伸部分的第二部分。

5. 发明授权

US08944774B2 Gas turbine nozzle with a flow fence 有权
标题翻译：燃气轮机喷嘴带有流动围栏
公开(公告)号：US08944774B2
公开(公告)日：2015-02-03
申请号：US13342256
申请日：2012-01-03
申请人： Craig Allen Bielek
发明人： Craig Allen Bielek
IPC分类号： F01D9/02 , F04D29/38 , F01D5/14
CPC分类号： F01D5/145 , F01D5/141 , F01D5/20
摘要： The present application provides a turbine nozzle. The turbine nozzle may include an airfoil with a leading edge and a trailing edge and a flow fence extending from the leading edge to the trailing edge.
摘要翻译：本申请提供了一种涡轮喷嘴。涡轮喷嘴可以包括具有前缘和后缘的翼型和从前缘延伸到后缘的流动挡板。

6. 发明申请

US20130039771A1 TURBOMACHINE COMPONENT HAVING AN AIRFOIL CORE SHAPE 有权
标题翻译：涡轮机组件具有气垫芯形状
公开(公告)号：US20130039771A1
公开(公告)日：2013-02-14
申请号：US13206016
申请日：2011-08-09
申请人： Benjamin Michael Check , Craig Allen Bielek , Hal Feaster Pollard , Sivaraman Vedhagiri
发明人： Benjamin Michael Check , Craig Allen Bielek , Hal Feaster Pollard , Sivaraman Vedhagiri
IPC分类号： F01D5/14
CPC分类号： F01D9/041 , F01D5/141 , F05D2240/12 , F05D2250/74
摘要： A turbomachine component includes a turbine stator nozzle member having an airfoil core shape. The airfoil core shape includes a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil core shape.
摘要翻译：涡轮机组件包括具有翼型件形状的涡轮机定子喷嘴构件。翼型芯的形状包括基本上根据表1所示的X，Y和Z的笛卡尔坐标值的公称轮廓，并且其中X和Y是以平滑连续的弧连接时定义翼型轮廓部分的英寸距离在每个距离Z英寸处，Z距离处的轮廓部分彼此平滑地连接以形成完整的翼型芯形状。

7. 发明授权

US06736599B1 First stage turbine nozzle airfoil 有权
标题翻译：第一级涡轮喷嘴翼型
公开(公告)号：US06736599B1
公开(公告)日：2004-05-18
申请号：US10249870
申请日：2003-05-14
申请人： Curtis John Jacks , Craig Allen Bielek , Robert Walter Coign , Randall Gill
发明人： Curtis John Jacks , Craig Allen Bielek , Robert Walter Coign , Randall Gill
IPC分类号： F01D904
CPC分类号： F01D9/02 , F01D5/141 , F05D2200/10 , F05D2240/128 , F05D2240/301 , F05D2250/70
摘要： The first stage nozzles have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table 1. The X and Y values are in inches and the Z value is non-dimensional along the nozzle-stacking axis coincident with a turbine radius and convertible to a Z distance in inches from the turbine axis by multiplying the Z value by the height of the airfoil and adding the root radius to the result. The X and Y distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of ±0.160 inches.
摘要翻译：第一级喷嘴具有基本上符合表1所示的X，Y和Z的笛卡尔坐标值的翼型轮廓.X和Y值以英寸为单位，并且Z值沿着与a的一致的喷嘴 - 堆叠轴线是无量纲的涡轮机半径，并通过将Z值乘以翼型的高度并将根半径添加到结果中，将其与涡轮机轴的英寸距离Z转换成Z距离。 X和Y距离可以是可缩放的，作为相同常数或数字的函数，以提供用于喷嘴的放大或缩小的翼型部分。由X，Y和Z距离给出的额定翼型在±0.160英寸的范围内。

8. 发明授权

US09255480B2 Turbine of a turbomachine 有权
标题翻译：涡轮机的涡轮机
公开(公告)号：US09255480B2
公开(公告)日：2016-02-09
申请号：US13284068
申请日：2011-10-28
申请人： Paul Kendall Smith , Gunnar Leif Siden , Craig Allen Bielek , Thomas William Vandeputte
发明人： Paul Kendall Smith , Gunnar Leif Siden , Craig Allen Bielek , Thomas William Vandeputte
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2240/125 , F05D2240/307
摘要： A turbine of a turbomachine is provided and includes opposing endwalls defining a pathway for a fluid flow and a plurality of interleaved blade stages and nozzle stages arranged axially along the pathway. The plurality of the blade stages includes a last blade stage at a downstream end of the pathway and a next-to-last blade stage upstream from the last blade stage. The plurality of the nozzle stages includes a last nozzle stage between the last blade stage and the next-to-last blade stage and a next-to-last nozzle stage upstream from the next-to-last blade stage. At least one of the next-to-last blade stage and the next-to-last nozzle stage includes aerodynamic elements configured to interact with the fluid flow and to define a throat distribution producing a tip strong pressure profile in the fluid flow.
摘要翻译：提供涡轮机的涡轮机并且包括限定用于流体流动的路径的相对的端壁以及沿着该路径轴向设置的多个交错的叶片级和喷嘴级。多个叶片级在通路的下游端包括最后的叶片级，并且在最后叶片级的上游包括一个最后叶片级。多个喷嘴级包括在最后的叶片级和下一个到最后的叶片级之间的最后一个喷嘴级，以及从下一个到最后的叶片级上游的最后一个喷嘴级。下一个到最后的叶片级和下一个到最后的喷嘴级中的至少一个包括配置成与流体流相互作用并且限定喉部分布的气动元件，其产生流体流中的尖端强压力分布。

9. 发明授权

US08807950B2 Turbine nozzle airfoil profile 有权
标题翻译：涡轮喷嘴翼型
公开(公告)号：US08807950B2
公开(公告)日：2014-08-19
申请号：US13304728
申请日：2011-11-28
申请人： Craig Allen Bielek , Veeraporn Kullatham , Mary Holloway
发明人： Craig Allen Bielek , Veeraporn Kullatham , Mary Holloway
IPC分类号： F01D5/14
CPC分类号： F01D5/142 , F05D2250/74
摘要： The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.
摘要翻译：本申请提供了一种包括翼型形状的涡轮喷嘴。翼型可以具有基本上根据表1所示的X，Y和Z的笛卡尔坐标值的标称轮廓.X，Y和Z的笛卡尔坐标值是0％至100％的无量纲值可转换为通过将X，Y和Z的笛卡尔坐标值乘以翼型件的高度（英寸），以英寸为单位的尺寸距离。 X和Y值是以英寸为单位的距离，当通过平滑连续的弧连接时，在每个距离Z处限定翼型轮廓部分.Z距离处的翼型轮廓部分可以彼此平滑地连接以形成完整的翼型形状。

10. 发明授权

US08714931B2 Turbine bucket airfoil profile 有权
标题翻译：涡轮斗翼型材
公开(公告)号：US08714931B2
公开(公告)日：2014-05-06
申请号：US13304729
申请日：2011-11-28
申请人： Craig Allen Bielek , Vineet Ghate , Matthew Piersall , Jonathan Reed
发明人： Craig Allen Bielek , Vineet Ghate , Matthew Piersall , Jonathan Reed
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2250/74
摘要： The present application provides a turbine bucket including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.
摘要翻译：本申请提供了一种包括翼型形状的涡轮机桶。翼型可以具有基本上根据表1所示的X，Y和Z的笛卡尔坐标值的标称轮廓.X，Y和Z的笛卡尔坐标值是0％至100％的无量纲值可转换为通过将X，Y和Z的笛卡尔坐标值乘以翼型件的高度（英寸），以英寸为单位的尺寸距离。 X和Y值是以英寸为单位的距离，当通过平滑连续的弧连接时，在每个距离Z处限定翼型轮廓部分.Z距离处的翼型轮廓部分可以彼此平滑地连接以形成完整的翼型形状。

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