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1. 发明专利

JP2010059968A Turbine airfoil clocking 审中-公开
标题翻译：涡轮空气流通
公开(公告)号：JP2010059968A
公开(公告)日：2010-03-18
申请号：JP2009196263
申请日：2009-08-27
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： NING WEI , FRIEDMAN MICHAEL E , RYMAN JOHN F
IPC分类号： F04D29/38 , F01D5/14
CPC分类号： F01D5/142 , F01D9/041 , F04D19/02 , F04D29/666 , Y02T50/673
摘要： PROBLEM TO BE SOLVED: To provide an efficient rotary airfoil-row machine in positioning airfoils in one row to airfoils in neighboring or nearby rows.
SOLUTION: In a compressor of a turbine engine, an assembly of airfoils 130 comprises: an intermediate airfoil row 136; a first upstream airfoil row 134; and a first downstream airfoil row 138. Both sides of the intermediate airfoil row 136 are adjacent to the first upstream airfoil row 134 and the first downstream airfoil row 138, respectively. The first upstream airfoil row 134 and the first downstream airfoil row 138 each comprises a row of rotor blades, which rotate at substantially the same speed during operation. The intermediate airfoil row 136 comprises a row of stator blades, which remains substantially stationary during operation. At least 90% of the airfoils 130 of the first upstream airfoil row 134, and at least 90% of the airfoils 130 of the first downstream airfoil row 134 has a clocking relationship of 25-75% pitch.
COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供一种有效的旋转翼型排列机，将机翼定位在一排中，以便在相邻或相邻行中的翼型件。解决方案：在涡轮发动机的压缩机中，翼型件130的组件包括：中间翼片排136; 第一上游翼型排134; 和第一下游翼型排138.中间翼型件排136的两侧分别与第一上游翼型件排134和第一下游翼型件排138相邻。第一上游翼型排134和第一下游翼型排138各自包括一排转子叶片，其在操作期间以基本上相同的速度旋转。中间翼片排136包括一排定子叶片，其在操作期间保持基本上静止。第一上游翼型件排134的翼型件130的至少90％以及第一下游翼型件排134的至少90％的翼型件130具有25-75％间距的时钟关系。版权所有（C）2010，JPO＆INPIT

2. 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

3. 发明专利

JP2010156339A Clocking of turbine aerofoil 有权
标题翻译：涡轮AEROFOIL的闭锁
公开(公告)号：JP2010156339A
公开(公告)日：2010-07-15
申请号：JP2009296946
申请日：2009-12-28
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： NING WEI , FRIEDMAN MICHAEL E , RYMAN JOHN F
IPC分类号： F01D5/14 , F01D9/02 , F04D19/02 , F04D29/64 , F04D29/66
CPC分类号： F01D5/142 , Y02T50/673
摘要： PROBLEM TO BE SOLVED: To position one line of aerofoils with respect to a position of aerofoils of adjacent or near line. SOLUTION: A target aerofoil 130 line shares borders, on both sides, with the first upstream aerofoil 130 line and the first downstream aerofoil 130 line, the first upstream aerofoil 130 line and the first downstream aerofoil 130 line include the substantially same number of similar aerofoils 130, and one of a moving blade line and a stationary blade line, and the target aerofoil 130 line includes the other line. Circumferential positions of the aerofoils 130 in the first upstream aerofoil 130 line and the aerofoils 130 in the first downstream aerofoil 130 line are specified to make at least 90% of the aerofoils 130 in the first upstream aerofoil 130 line and at least 90% of the aerofoils 130 in the first downstream aerofoil 130 line satisfy the clocking relation of 25-75% pitch. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：相对于相邻或近线的翼型的位置来定位一条翼状翼。解决方案：目标机翼130线在两侧与第一上游翼型130线和第一下游翼型130线共享边界，第一上游翼型130线和第一下游翼型130线包括基本上相同的数字类似的机翼130，以及活动叶片线和固定叶片线之一，并且目标翼型130线包括另一条线。指定第一上游翼型130线中的机翼130和第一下游翼型130线中的机翼130在第一上游翼型130线中的至少90％的翼状空间130的圆周位置和至少90％的翼型130 第一下游翼型130线中的机翼130满足25-75％间距的时钟关系。版权所有（C）2010，JPO＆INPIT

4. 发明专利

JP2010059967A Method for clocking turbine airfoils 有权
标题翻译：用于定时关闭涡轮机空气的方法
公开(公告)号：JP2010059967A
公开(公告)日：2010-03-18
申请号：JP2009196261
申请日：2009-08-27
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： NING WEI , FRIEDMAN MICHAEL E , RYMAN JOHN F
IPC分类号： F01D5/14 , F04D29/38
CPC分类号： F01D5/142 , F05D2230/60 , F05D2250/312 , Y02T50/673
摘要： PROBLEM TO BE SOLVED: To provide efficient turbine airfoils by positioning airfoils in one row to airfoils in neighboring or nearby rows. SOLUTION: In the method of operating a turbine engine, the turbine engine includes a successively axially stacked first airfoil row 134 of airfoils 130 in one of a compressor and a turbine, a second airfoil row 136, and a third airfoil row 138. The first airfoil row 134 and the third airfoil row 138 comprise one of a row of rotor blades and a row of stator blades, and the second airfoil row 136 comprises the other of a row of rotor blades and a row of stator blades. In this method, a portion of the airfoils 130 of the first airfoil row 134 and a portion of the airfoils 130 of the third airfoil row 138 are configured such that a portion of the airfoils 130 of the first airfoil row 134 and a portion of the airfoils 130 of the third airfoil row 138 include a clocking relationship of 25-75% pitch. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：通过将翼型件一排地定位在相邻或邻近行中的翼型件来提供有效的涡轮机翼型件。解决方案：在操作涡轮发动机的方法中，涡轮发动机包括在压缩机和涡轮之一中的机翼130的连续轴向堆叠的第一翼型排134，第二翼型排136和第三翼型排138 第一翼型排134和第三翼型排138包括一排转子叶片和一排定子叶片中的一个，第二翼型排136包括一排转子叶片和一排定子叶片中的另一个。在该方法中，第一翼型排134的翼型件130的一部分和第三翼型件列138的翼型件130的一部分被构造成使得第一翼型件排134的翼型件130的一部分和第三翼型排138的翼型件130包括25-75％间距的时钟关系。版权所有（C）2010，JPO＆INPIT

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