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公开(公告)号：US08142138B2
公开(公告)日：2012-03-27
申请号：US12434277
申请日：2009-05-01
申请人： Sanjeev Heda , Robert W. Coign , Kevin L. Bruce
发明人： Sanjeev Heda , Robert W. Coign , Kevin L. Bruce
IPC分类号： F01D25/12
CPC分类号： F01D25/12 , F01D11/24 , Y02T50/675
摘要： In one embodiment, a turbine system may include a turbine casing, a shroud block coupled to the turbine casing, a fluid passage in the shroud block; and a pin configured to interface with the fluid passage. The pin may include a hollow shaft; a rod inserted into the hollow shaft; and a valve disposed on a distal end of the rod, wherein the valve is configured to open and close the fluid passage when the rod is actuated remotely through the hollow shaft.
摘要翻译： 在一个实施例中，涡轮机系统可以包括涡轮机壳体，联接到涡轮机壳体的护罩块，护罩块中的流体通道; 以及被配置为与流体通道相接合的销。 销可包括中空轴; 插入中空轴的杆; 以及设置在所述杆的远端上的阀，其中所述阀构造成当所述杆远离所述中空轴致动时，所述阀被打开和关闭所述流体通道。
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公开(公告)号：US20130084160A1
公开(公告)日：2013-04-04
申请号：US13249554
申请日：2011-09-30
CPC分类号： F01D11/24 , F05D2240/11 , F05D2250/183 , F05D2260/201
摘要： The present application provides a turbine shroud impingement system. The turbine shroud impingement system may include a turbine shroud segment, an impingement box positioned within the turbine shroud segment, a feed tube in communication with the impingement box, and a bellows positioned about the feed tube.
摘要翻译： 本申请提供了一种涡轮机罩冲击系统。 涡轮机罩冲击系统可以包括涡轮机护罩段，位于涡轮机护罩区段内的冲击箱，与冲击箱连通的进料管和围绕进料管定位的波纹管。
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公开(公告)号：US20130052024A1
公开(公告)日：2013-02-28
申请号：US13216297
申请日：2011-08-24
申请人： Thomas J. Brunt , Robert W. Coign
发明人： Thomas J. Brunt , Robert W. Coign
IPC分类号： F01D5/30
CPC分类号： F01D9/041 , F05D2260/30
摘要： The present application provides a turbine nozzle vane retention system. The turbine nozzle vane retention system may include a number of nozzles with a platform, a slot extending into the platform, and a pin extending between the slot of a first nozzle and the slot of a second nozzle,
摘要翻译： 本申请提供了一种涡轮喷嘴叶片保持系统。 涡轮喷嘴叶片保持系统可以包括具有平台的多个喷嘴，延伸到平台中的狭槽以及在第一喷嘴的狭槽和第二喷嘴的狭槽之间延伸的销，
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公开(公告)号：US20100278631A1
公开(公告)日：2010-11-04
申请号：US12434277
申请日：2009-05-01
申请人： Sanjeev Heda , Robert W. Coign , Kevin L. Bruce
发明人： Sanjeev Heda , Robert W. Coign , Kevin L. Bruce
IPC分类号： F01D25/12
CPC分类号： F01D25/12 , F01D11/24 , Y02T50/675
摘要： In one embodiment, a turbine system may include a turbine casing, a shroud block coupled to the turbine casing, a fluid passage in the shroud block; and a pin configured to interface with the fluid passage. The pin may include a hollow shaft; a rod inserted into the hollow shaft; and a valve disposed on a distal end of the rod, wherein the valve is configured to open and close the fluid passage when the rod is actuated remotely through the hollow shaft.
摘要翻译： 在一个实施例中，涡轮机系统可以包括涡轮机壳体，联接到涡轮机壳体的护罩块，护罩块中的流体通道; 以及被配置为与流体通道相接合的销。 销可包括中空轴; 插入中空轴的杆; 以及设置在所述杆的远端上的阀，其中所述阀构造成当所述杆远离所述中空轴致动时，所述阀被打开和关闭所述流体通道。
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公开(公告)号：US06994520B2
公开(公告)日：2006-02-07
申请号：US10853240
申请日：2004-05-26
IPC分类号： F01D9/06
CPC分类号： F01D5/141 , B22C9/10 , F01D5/18 , F05D2230/21 , F05D2230/211
摘要： First stage nozzle airfoils have internal core profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein X, Y and Z values are in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define internal core profile sections at each radial distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete internal core profile. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled-up or scaled-down internal core profile. The nominal internal core profile given by the X, Y and Z distances lies within an envelope of ±0.030 inches in directions normal to any internal core surface location.
摘要翻译： 第一级喷嘴翼型件具有基本上根据表I中列出的X，Y和Z的笛卡尔坐标值的内部芯轮廓，其中X，Y和Z值为英寸。 X和Y值是当通过光滑连续的弧连接时在每个径向距离Z处限定内部芯轮廓部分的距离。每个距离Z处的轮廓部分彼此平滑地连接以形成完整的内部芯轮廓。 X，Y和Z距离可以是可扩展的，作为相同常数或数字的函数，以提供按比例放大或缩小的内核配置文件。 由X，Y和Z距离给出的标称内部芯轮廓在垂直于任何内部芯部表面位置的方向上在±0.030英寸的包络内。
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