公开(公告)号：US6042879A

公开(公告)日：2000-03-28

申请号：US887506

申请日：1997-07-02

申请人： Peter J. Draghi ,  Brian J. Shurman ,  Dale A. Simard ,  Peter Wrabel

发明人： Peter J. Draghi ,  Brian J. Shurman ,  Dale A. Simard ,  Peter Wrabel

IPC分类号： C23C4/02 ,  C23C10/60 ,  C23C26/00 ,  B32B35/00

CPC分类号： C23C4/02 ,  C23C10/60 ,  C23C26/00 ,  B23P2700/06 ,  Y10T29/49318 ,  Y10T428/12361 ,  Y10T428/1275

摘要： A method for preparing a protectively coated, apertured article to be recoated reduces the likelihood that the apertures will become constricted as a consequence of subsequent recoating. The invention, described in the context of a gas turbine engine blade (12) having transpiration cooling passages (34), includes the step of diffusing an auxiliary coating (52) into an existing coating (28) and into the exposed substrate material (26) at the periphery of the passages to form a diffusion zone (54). The blade is then subjected to a stripping agent so that the diffusion zone (54) any undiffused existing coating, and any undiffused auxiliary coating are removed. The method causes a compensatory enlargement of the mouth (44) of each passage so that excess coating that accumulates in the passage mouths during subsequent recoating does not restrict the flow capacity of the passages.

摘要翻译： 用于制备待重涂的保护涂层的多孔制品的方法降低了由于随后的重新涂覆而使孔径变得收缩的可能性。 在具有蒸发冷却通道（34）的燃气涡轮发动机叶片（12）的上下文中描述的本发明包括将辅助涂层（52）扩散到现有涂层（28）中并进入暴露的基底材料（26）的步骤 ），以形成扩散区（54）。 然后对刀片进行剥离剂，使得扩散区（54）任何未扩散的现有涂层和任何未扩散的辅助涂层都被去除。 该方法引起每个通道的口（44）的补偿性扩大，使得在随后的重涂期间积聚在通道口中的过量涂层不会限制通道的流动能力。

公开(公告)号：US20120060370A1

公开(公告)日：2012-03-15

申请号：US13045907

申请日：2011-03-11

申请人： Peter E. Leibfried ,  John P. Arrigoni ,  Dale A. Simard ,  Philip J. Dunne ,  William G. Sorvillo, SR.

发明人： Peter E. Leibfried ,  John P. Arrigoni ,  Dale A. Simard ,  Philip J. Dunne ,  William G. Sorvillo, SR.

IPC分类号： B23P6/00

CPC分类号： F01D5/005 ,  B23P6/002 ,  Y10T29/49318 ,  Y10T29/49336 ,  Y10T29/49718 ,  Y10T29/49726 ,  Y10T29/49734

摘要： A method for repairing a defect in a component having a first major surface and a second major surface, a thickness defined between the major surfaces, and an edge adjoining both the major surfaces is characterized by forming a slot cut entirely through the thickness of the component between the first and second major surfaces, the slot extending inward from the edge of the component towards an interior of the component to a depth from the edge sufficient to remove at least a substantial part of the defect, the slot defining an open end at the edge of the component, a closed end within the component, a width, a radius formed by the closed end, and opposing chamfered edges at the open end.

摘要翻译： 一种用于修复具有第一主表面和第二主表面的部件中的缺陷的方法，在主表面之间限定的厚度和与两个主表面相邻的边缘的特征在于形成通过部件的厚度完全切割的狭槽 在所述第一和第二主表面之间，所述狭槽从所述部件的边缘朝向所述部件的内部向内延伸至距所述边缘的深度，足以移除所述缺陷的至少大部分，所述狭槽在所述第一和第二主表面 部件的边缘，部件内的封闭端，宽度，由封闭端形成的半径以及开口端的相对的倒角边缘。

公开(公告)号：US06171711B2

公开(公告)日：2001-01-09

申请号：US09412694

申请日：1999-10-05

申请人： Peter J. Draghi ,  Brian J. Shurman ,  Dale A. Simard ,  Peter Wrabel

发明人： Peter J. Draghi ,  Brian J. Shurman ,  Dale A. Simard ,  Peter Wrabel

IPC分类号： C23C1060

CPC分类号： C23C4/02 ,  B23P2700/06 ,  C23C10/60 ,  C23C26/00 ,  Y10T29/49318 ,  Y10T428/12361 ,  Y10T428/1275

摘要： A method for preparing a protectively coated, apertured article to be recoated reduces the likelihood that the apertures will become constricted as a consequence of subsequent recoating. The invention, described in the context of a gas turbine engine blade (12) having transpiration cooling passages (34), includes the step of diffusing an auxiliary coating (52) into an existing coating (28) and into the exposed substrate material (26) at the periphery of the passages to form a diffusion zone (54). The blade is then subjected to a stripping agent so that the diffusion zone (54) any undiffused existing coating, and any undiffused auxiliary coating are removed. The method causes a compensatory enlargement of the mouth (44) of each passage so that excess coating that accumulates in the passage mouths during subsequent recoating does not restrict the flow capacity of the passages.

摘要翻译： 用于制备待重涂的保护涂层的多孔制品的方法降低了由于随后的重新涂覆而使孔径变得收缩的可能性。 在具有蒸发冷却通道（34）的燃气涡轮发动机叶片（12）的上下文中描述的本发明包括将辅助涂层（52）扩散到现有涂层（28）中并进入暴露的基底材料（26）的步骤 ），以形成扩散区（54）。 然后对刀片进行剥离剂，使得扩散区（54）任何未扩散的现有涂层和任何未扩散的辅助涂层都被去除。 该方法引起每个通道的口（44）的补偿性扩大，使得在随后的重涂期间积聚在通道口中的过量涂层不会限制通道的流动能力。

公开(公告)号：US08205334B2

公开(公告)日：2012-06-26

申请号：US11273057

申请日：2005-11-14

申请人： Peter E. Leibfried ,  John P. Arrigoni ,  Dale A. Simard ,  Philip J. Dunne ,  William G. Sorvillo, Sr.

发明人： Peter E. Leibfried ,  John P. Arrigoni ,  Dale A. Simard ,  Philip J. Dunne ,  William G. Sorvillo, Sr.

IPC分类号： B23P6/00 ,  B23P19/04

CPC分类号： F01D5/005 ,  B23P6/002 ,  Y10T29/49318 ,  Y10T29/49336 ,  Y10T29/49718 ,  Y10T29/49726 ,  Y10T29/49734

摘要： A method for repairing a component having first and second major surfaces, a thickness between the major surfaces, and an edge, is characterized by utilizing a template to determine if the component is suitable for repair, and forming a slot cut entirely through the thickness of the component. The slot extends inward from the edge of the component, has an open end at the edge of the component, a closed end within the component, a width, a radius at the closed end, and chamfered edges at the open end. Forming the slot includes forming an initial cut with a first cutting surface from the edge of the component at least to the defect, finishing the initial cut to the width and the radius with a second cutting surface, resulting in a finished cut, and chamfering the edge of the finished cut with a third cutting surface.

摘要翻译： 用于修复具有第一和第二主表面的部件，主表面之间的厚度和边缘的方法的特征在于利用模板来确定部件是否适合于修复，并且形成完全切割通过 组件。 槽从部件的边缘向内延伸，在部件的边缘处具有开口端，部件内的封闭端，宽度，封闭端的半径和开口端的倒角边缘。 形成槽包括从部件的边缘至少到缺陷形成具有第一切割表面的初始切割，用第二切割表面将初始切割精加工成宽度和半径，从而完成切割，并将 用第三切割面切割成品的边缘。