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1.发明授权Method for making a repaired turbine engine stationary vane assembly and repaired assembly 有权修理涡轮发动机静叶片组件和维修组件的方法公开(公告)号：US07172389B2
公开(公告)日：2007-02-06
申请号：US10989791
申请日：2004-11-16
申请人： Michael Philip Hagle , Timothy Lee Siebert , Jeffrey John Reverman , Dana Leigh Ferguson , Gregory Matthew Ford
发明人： Michael Philip Hagle , Timothy Lee Siebert , Jeffrey John Reverman , Dana Leigh Ferguson , Gregory Matthew Ford
IPC分类号： F01D9/00
CPC分类号： F01D9/02 , B23K1/0018 , B23K9/0026 , B23K15/0006 , B23K2101/001 , B23P6/005 , F01D5/005 , F01D5/34 , Y10T29/49323
摘要： A method is provided for making a repaired turbine engine stationary vane assembly including at least one airfoil bonded between spaced apart first and second platforms. The method comprises providing a first vane assembly member including at least a portion of the first platform, the airfoil, and a first segment of the second platform bonded with the airfoil. Also provided is a second vane assembly member including a second segment of the second platform with a recess of a shape and size sufficient to receive the first segment of the second platform. The first segment is placed in the recess after which the first and second segments are bonded, for example by brazing or welding. Provided is a more structurally sound repaired turbine engine stationary vane assembly including the first and second vane assembly members bonded together.
摘要翻译： 提供了一种用于制造修理的涡轮发动机静止叶片组件的方法，其包括结合在间隔开的第一和第二平台之间的至少一个翼型件。 该方法包括提供包括第一平台，翼型件的至少一部分和与翼型件粘合的第二平台的第一段的第一叶片组件。 还提供了一种第二叶片组件，其包括具有足以容纳第二平台的第一段的形状和尺寸的凹槽的第二平台的第二段。 第一段被放置在凹部中，之后第一和第二段结合，例如通过钎焊或焊接。 提供了一种更结构上更好的修理的涡轮发动机静止叶片组件，其包括结合在一起的第一和第二叶片组件构件。
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2.发明申请公开(公告)号：US20070147991A1
公开(公告)日：2007-06-28
申请号：US11315553
申请日：2005-12-22
IPC分类号： F01D1/02
CPC分类号： F01D5/005 , B23P6/002 , F01D9/02 , F05D2230/232 , F05D2230/237 , F05D2230/80 , Y10T29/49318 , Y10T29/49718
摘要： A repaired turbine engine stationary vane assembly, including at least one airfoil bonded between inner and outer bands, is provided by a method of providing first and second vane assembly members bonded at respective circumferential edges, for example by brazing or welding. The first vane assembly member includes the outer band, the airfoil, an inner flange, and a first segment of the inner band with a first edge, spaced from the flange and extending between and through inner band circumferential edge portions. The second vane assembly member includes a second segment of the inner band including a second edge of shape and size matched with the first edge and extending through the inner band circumferential edge portions.
摘要翻译： 通过提供通过例如通过钎焊或焊接在相应的周向边缘处接合的第一和第二叶片组件构件的方法来提供修复的涡轮发动机静止叶片组件，其包括结合在内带和外带之间的至少一个翼型件。 第一叶片组件构件包括外带，翼型件，内凸缘和内带的第一段，其具有第一边缘，与凸缘间隔开并且在内带圆周边缘部分之间并且穿过内带圆周边缘部分。 第二叶片组件构件包括内带的第二段，包括与第一边缘匹配的形状和尺寸的第二边缘并延伸穿过内带圆周边缘部分。
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3.发明授权公开(公告)号：US07434313B2
公开(公告)日：2008-10-14
申请号：US11315553
申请日：2005-12-22
CPC分类号： F01D5/005 , B23P6/002 , F01D9/02 , F05D2230/232 , F05D2230/237 , F05D2230/80 , Y10T29/49318 , Y10T29/49718
摘要： A repaired turbine engine stationary vane assembly, including at least one airfoil bonded between inner and outer bands, is provided by a method of providing first and second vane assembly members bonded at respective circumferential edges, for example by brazing or welding. The first vane assembly member includes the outer band, the airfoil, an inner flange, and a first segment of the inner band with a first edge, spaced from the flange and extending between and through inner band circumferential edge portions. The second vane assembly member includes a second segment of the inner band including a second edge of shape and size matched with the first edge and extending through the inner band circumferential edge portions.
摘要翻译： 通过提供通过例如通过钎焊或焊接在相应的周向边缘处接合的第一和第二叶片组件构件的方法来提供包括在内带和外带之间结合的至少一个翼型件的修理的涡轮发动机静止叶片组件。 第一叶片组件构件包括外带，翼型件，内凸缘和内带的第一段，其具有第一边缘，与凸缘间隔开并且在内带圆周边缘部分之间并且穿过内带圆周边缘部分。 第二叶片组件构件包括内带的第二段，包括与第一边缘匹配的形状和尺寸的第二边缘并延伸穿过内带圆周边缘部分。
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