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1. 发明专利

JP2005054804A Perimeter-cooled turbine bucket airfoil cooling hole location, style and configuration 有权
标题翻译：涡轮冷却涡轮机气缸空气冷却孔位置，样式和配置
公开(公告)号：JP2005054804A
公开(公告)日：2005-03-03
申请号：JP2004230070
申请日：2004-08-06
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： CLEVELAND PETER GAINES , BEDDARD THOMAS BRADLEY
IPC分类号： F01D5/18 , F01D5/20
CPC分类号： F01D5/20 , F01D5/141 , F01D5/187 , F05D2260/22141 , Y10S416/02
摘要： PROBLEM TO BE SOLVED: To provide an aerofoil part for a first-stage bucket having the optimum number, position, form, and size of cooling holes disposed at the periphery to send cooling medium.
SOLUTION: The turbine stage one bucket has the aerofoil part having a plurality of cooling holes penetrating the aerofoil part from 0% span to 100% span for sending cooling air to the tip of the aerofoil part to flow into a high-temperature gas passage. X- and Y-coordinate values are given in table I, locating the holes relative to the airfoil profile at aerofoil profile sections of 5%, 50%, and 90% span. The table I also gives diameter of the holes. The cooling holes can thus be optimized to the aerofoil part of the turbine bucket. The cooling holes are also located in relation to the profile of the bucket aerofoil part given by the X-. Y-, and Z-coordinate values of table II. The two coordinate systems have the same origin.
COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：要解决的问题：为具有设置在周边的冷却孔的最佳数量，位置，形式和尺寸的第一级桶提供机翼部件以发送冷却介质。解决方案：涡轮级一桶具有机翼部分，其具有从0％跨度穿透机翼部分到100％跨度的多个冷却孔，用于将冷却空气发送到机翼部分的尖端以流入高温气体通道。 X和Y坐标值在表I中给出，在5％，50％和90％跨度的翼型剖面上将孔相对于翼型轮廓定位。桌子我也给出了孔的直径。因此，冷却孔可以优化到涡轮机桶的机翼部分。冷却孔也相对于X轴给出的铲斗机翼部分的轮廓而定位。 Y和Z坐标值。两个坐标系具有相同的起点。版权所有（C）2005，JPO＆NCIPI

2. 发明专利

JP2005030403A Airfoil shape for turbine bucket 审中-公开
标题翻译：涡轮机的气翼形状
公开(公告)号：JP2005030403A
公开(公告)日：2005-02-03
申请号：JP2004202671
申请日：2004-07-09
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： CLEVELAND PETER GAINES , BEDDARD THOMAS BRADLEY , SPARKS SCOTT MATTHEW , WEBER JOSEPH ANTHONY , FEHLBERG JAMES BERNARD
IPC分类号： F01D5/14 , F01D5/18
CPC分类号： F01D5/141 , F01D5/187 , F05D2250/70 , F05D2260/202 , Y02T50/673 , Y02T50/676 , Y10S416/02
摘要： PROBLEM TO BE SOLVED: To provide an airfoil profile of a first-stage turbine bucket.
SOLUTION: The first-stage turbine bucket 16 has an airfoil profile substantially according to the Cartesian coordinate values of X, Y and Z described in table I. In the table I, the X and Y values are expressed by inch, and the Z value a dimensionless value ranging from 0.05 span to 0.95 span converted to Z distance expressed by inch by multiplication of the Z value by the height of the airfoil part expressed by inch. When the X and Y are connected by a smooth continuous circular arc, it is a distance forming an airfoil profile section 40 in each distance Z. The X, Y and Z distances can be enlarged and reduced taking the same constant or numerical value as a function to obtain the enlarged or reduced airfoil section for a bucket. The reference airfoil given by the X, Y and Z distances is within an envelope ±0.150 inch in the vertical direction to the surface of the airfoil.
COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：要解决的问题：提供第一级涡轮机叶片的翼型轮廓。
解决方案：第一级涡轮机桶16具有基本上根据表I中描述的X，Y和Z的笛卡尔坐标值的翼型轮廓。在表I中，X和Y值由英寸表示，并且通过将Z值乘以由英寸表示的翼型部分的高度，Z值是从0.05跨度到0.95跨度的无量纲值转换为由英寸表示的Z距离。当X和Y通过平滑的连续圆弧连接时，它是在每个距离Z内形成翼型轮廓部分40的距离.X，Y和Z的距离可以被放大和缩小，采用相同的恒定值或数值用于获得用于铲斗的扩大或减小的翼型部分。由X，Y和Z距离给出的参考翼型在与机翼表面垂直的方向上为±0.150英寸的包络内。版权所有（C）2005，JPO＆NCIPI

3. 发明专利

JP2006046347A Airfoil shape for compressor blade 审中-公开
标题翻译：压缩机叶片的气翼形状
公开(公告)号：JP2006046347A
公开(公告)日：2006-02-16
申请号：JP2005228126
申请日：2005-08-05
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： TOMBERG STEVEN ERIC , BEHARRYSINGH ROGER , DEJORIS TIMOTHY E , MILLER WILLIAM J , DEIVERNOIS PAUL , CHALUVADI VENKATA SIVA P , MISTREANU ADRIAN MICREA , DUTKA MICHAEL JAMES , RACE NATHAN S , BOYD JEFFERY , MCGOWAN CHRISTOPHER DAVID , CLEVELAND PETER GAINES , HARRELL JASON THOMAS , SCHOTT CARL G , STAMPFLI JOHN DAVID , DENMARK RONALD STUART , SCHIRLE STEVEN MARK , MICHENFELDER JENNIFER B , RYMAN JOHN F
IPC分类号： F04D29/38 , F01D5/14 , F04D29/32 , F04D29/54
CPC分类号： F01D5/141 , F05D2240/301 , Y10S416/02 , Y10S416/05
摘要： PROBLEM TO BE SOLVED: To provide an airfoil profile of an article of manufacture.
SOLUTION: The article of manufacture has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. The table selected from the group of tables consisting of TABLES 1S-16S, 1R-17R, and IGV. 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 are joined smoothly with one another to form a complete airfoil shape.
COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：提供制造品的翼型。
解决方案：制品具有基本上符合表中所列的X，Y和Z的笛卡尔坐标值的标称曲线。该表从由表1S-16S，1R-17R和IGV组成的表格中选择。其中X和Y是以英寸为单位的距离，当通过平滑连续的弧连接时，以每英寸为单位限定每个距离Z处的翼型轮廓部分。 Z距离处的轮廓部分彼此平滑地连接以形成完整的翼型形状。版权所有（C）2006，JPO＆NCIPI

4. 发明专利

JP2005036810A End edge profile of tip shroud of turbine bucket 审中-公开
标题翻译：涡轮机底盘边缘剖面图
公开(公告)号：JP2005036810A
公开(公告)日：2005-02-10
申请号：JP2004209304
申请日：2004-07-16
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： SNOOK DANIEL DAVID , CLEVELAND PETER GAINES
IPC分类号： F01D5/14 , F01D5/20 , F01D5/22
CPC分类号： F01D5/225 , F05D2250/70
摘要： PROBLEM TO BE SOLVED: To provide profiles of the front and the rear edges of a tip shroud supported by a blade profile part.
SOLUTION: A turbine bucket(24) contains a bucket blade profile part(36) having the tip shroud(40), and the tip shroud(40) has the front and the rear edges(46, 48). Then the profiles of the front and the rear edges are determined according to Cartesian coordinate values of X and Y at the points 12 to 20 and 1 to 11 described in Table 1 respectively. The values of X and Y are distances indicated by the inch, forming the profiles of the front and the rear edges of the tip shroud when the points 12 to 20 and 1 to 11 are connected by a smooth continuous arc. A profile of the blade profile part at a 95% span is determined by Cartesian coordinate values of X, Y and Z described in Table 2 which has the same X and Y origin points along an origin point of Table 1 and the Z axis. The front and the rear edges outlined and adapted to the profile of the blade profile part of the tip shroud produce optimum mass distribution of the tip shroud which maximizes the life of a creep.
COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：要解决的问题：提供由叶片轮廓部分支撑的尖端护罩的前边缘和后边缘的轮廓。解决方案：涡轮机叶片（24）包含具有尖端护罩（40）的铲斗叶片轮廓部分（36），并且尖端护罩（40）具有前边缘和后边缘（46,48）。然后根据表1中所示的点12至20和1至11，根据X和Y的笛卡尔坐标值确定前边缘和后边缘的轮廓。 X和Y的值是由英寸表示的距离，当点12至20和1至11通过平滑的连续弧连接时，形成尖端护罩的前边缘和后边缘的轮廓。在95％跨度处的叶片轮廓部分的轮廓由表2中描述的X，Y和Z的笛卡尔坐标值确定，其具有沿着表1的原点和Z轴具有相同的X和Y原点。前缘和后缘被勾勒并适应于尖端护罩的叶片轮廓部分的轮廓，产生最大化蠕变寿命的尖端罩的最佳质量分布。版权所有（C）2005，JPO＆NCIPI

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