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1.发明公开Method of repairing shrouded turbine blades with cracks in the vicinity of the outer shroud notch 有权修复在所述外壳的外切口的附近涂覆有裂纹的涡轮叶片的方法，
公开(公告)号：EP1892374A2
公开(公告)日：2008-02-27
申请号：EP07253059.5
申请日：2007-08-03
CPC分类号： F01D5/005 , B23K2201/001 , B23P6/002 , F01D25/285 , F05D2230/232 , F05D2230/80 , Y10T29/49318 , Y10T29/4932 , Y10T29/49336 , Y10T29/49718 , Y10T29/49732 , Y10T29/49734
摘要： A method of repairing a damaged notch fillet radius (20) of a turbine blade shroud (12) includes a replacement notch fillet radius (20) and a hardface nugget (30). The damaged notch fillet radius (20) is blended out and a hardface structure (22) positioned proximate the damaged notch fillet radius (20) is removed. A replacement notch fillet (20) radius is formed with weld filler and the hardface nugget (30) is welded to at least a portion of the replacement notch fillet radius (20).
摘要翻译： 修复涡轮机叶片护罩（12）的受损切口圆角半径（20）的方法，包括：替换切口圆角半径（20）和一个硬质面块（30）。 损坏的切口圆角半径（20）共混并定位成邻近一个硬质表面结构（22）的损坏的切口圆角半径（20）被去除。 的替换切口圆角（20）的半径形成有焊接填充和硬质面块（30）被焊接到所述替换切口圆角半径（20）的至少一部分。
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公开(公告)号：EP1978346B1
公开(公告)日：2011-09-28
申请号：EP08251292.2
申请日：2008-04-02
CPC分类号： G01N21/8803 , G01N1/32
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公开(公告)号：EP1995346A3
公开(公告)日：2010-07-14
申请号：EP08251806.9
申请日：2008-05-23
CPC分类号： B23P6/007 , C23C10/02 , C23C10/04 , C23C10/60 , C23C28/021 , C23C28/023 , C23C28/028 , C23C30/00 , F01D5/005 , F01D5/288 , F05D2230/30 , F05D2230/90 , Y10T29/49318 , Y10T428/12493 , Y10T428/12944
摘要： A method of repairing a component of a gas turbine engine that includes a metallic substrate (24), an existing coating, and a diffusion layer formed in the metallic substrate adjacent to the coating. The method includes removing at least a portion of the existing aluminide coating, removing material forming the diffusion layer, applying a new metallic layer (32) to the metallic substrate, and applying a new aluminide coating (28B) over the new metallic layer to form a new diffusion layer (30B) in the new metallic layer. The new metallic layer is a substantially homogeneous material that is substantially similar in chemical composition to that of the metallic substrate, and the new metallic layer (32) forms a structural layer having a thickness selected to provide a specified contour to the component.
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4.发明公开Method for checking surface condition after cleaning process 有权Verfahren zurPrüfungdesOberflächenzustandsnach einem Reinigungsverfahren
公开(公告)号：EP1978346A1
公开(公告)日：2008-10-08
申请号：EP08251292.2
申请日：2008-04-02
CPC分类号： G01N21/8803 , G01N1/32
摘要： Methods for inspecting gas turbine component parts for possible distress after hydrogen fluoride cleaning are disclosed. The methods selectively remove a small amount of material for intergranular attack (IGA) analysis, determine corrosion in the component part, and restore the component part back to its original dimensions.
摘要翻译： 公开了在氟化氢清洗之后检查可能遇险的燃气轮机部件的方法。 该方法选择性地去除少量的晶间腐蚀（IGA）分析材料，确定部件中的腐蚀，并将部件恢复到其原始尺寸。
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5.发明授权Method of repairing shrouded turbine blades with cracks in the vicinity of the outer shroud notch 有权修复在所述外壳的外切口的附近涂覆有裂纹的涡轮叶片的方法，
公开(公告)号：EP1892374B1
公开(公告)日：2014-09-24
申请号：EP07253059.5
申请日：2007-08-03
CPC分类号： F01D5/005 , B23K2201/001 , B23P6/002 , F01D25/285 , F05D2230/232 , F05D2230/80 , Y10T29/49318 , Y10T29/4932 , Y10T29/49336 , Y10T29/49718 , Y10T29/49732 , Y10T29/49734
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6.发明公开Method of repairing shrouded turbine blades with cracks in the vicinity of the outer shroud notch 有权修复在所述外壳的外切口的附近涂覆有裂纹的涡轮叶片的方法，
公开(公告)号：EP1892374A3
公开(公告)日：2012-06-27
申请号：EP07253059.5
申请日：2007-08-03
CPC分类号： F01D5/005 , B23K2201/001 , B23P6/002 , F01D25/285 , F05D2230/232 , F05D2230/80 , Y10T29/49318 , Y10T29/4932 , Y10T29/49336 , Y10T29/49718 , Y10T29/49732 , Y10T29/49734
摘要： A method of repairing a damaged notch fillet radius (20) of a turbine blade shroud (12) includes a replacement notch fillet radius (20) and a hardface nugget (30). The damaged notch fillet radius (20) is blended out and a hardface structure (22) positioned proximate the damaged notch fillet radius (20) is removed. A replacement notch fillet (20) radius is formed with weld filler and the hardface nugget (30) is welded to at least a portion of the replacement notch fillet radius (20).
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7.发明公开Coated gas turbine engine component repair 审中-公开Wiederherstellung von beschichteten Gasturbinen Komponenten
公开(公告)号：EP1995346A2
公开(公告)日：2008-11-26
申请号：EP08251806.9
申请日：2008-05-23
CPC分类号： B23P6/007 , C23C10/02 , C23C10/04 , C23C10/60 , C23C28/021 , C23C28/023 , C23C28/028 , C23C30/00 , F01D5/005 , F01D5/288 , F05D2230/30 , F05D2230/90 , Y10T29/49318 , Y10T428/12493 , Y10T428/12944
摘要： A method of repairing a component of a gas turbine engine that includes a metallic substrate (24), an existing coating, and a diffusion layer formed in the metallic substrate adjacent to the coating. The method includes removing at least a portion of the existing aluminide coating, removing material forming the diffusion layer, applying a new metallic layer (32) to the metallic substrate, and applying a new aluminide coating (28B) over the new metallic layer to form a new diffusion layer (30B) in the new metallic layer. The new metallic layer is a substantially homogeneous material that is substantially similar in chemical composition to that of the metallic substrate, and the new metallic layer (32) forms a structural layer having a thickness selected to provide a specified contour to the component.
摘要翻译： 一种修复燃气涡轮发动机的部件的方法，其包括金属基板（24），现有的涂层和形成在与涂层相邻的金属基板中的扩散层。 该方法包括去除现有的铝化物涂层的至少一部分，去除形成扩散层的材料，向金属基底施加新的金属层（32），并在新的金属层上施加新的铝化物涂层（28B）以形成 新的金属层中的扩散层（30B）。 新的金属层是基本上均匀的材料，其化学组成基本上与金属基底相似，并且新的金属层（32）形成具有被选择为该部件提供特定轮廓的厚度的结构层。
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