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    Method for repairing an apertured gas turbine component
    3.
    发明公开
    Method for repairing an apertured gas turbine component 有权
    修复有孔燃气轮机部件的方法

    公开(公告)号：EP1286020A3

    公开(公告)日：2003-12-17

    申请号：EP02254349.0

    申请日：2002-06-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Ducotey, Howard S. Jr. ,  Zuber, Robert J. ,  Draghi, Peter J.

    IPC: F01D5/00 ,  C23C4/02 ,  C23C4/18 ,  B23P6/00

    CPC classification number: B23P6/002 ,  B23H9/10 ,  B23H9/14 ,  B23P2700/06 ,  C23C4/02 ,  C23C4/18 ,  C23C28/32 ,  C23C28/345 ,  C23C28/3455 ,  F01D5/005 ,  F05D2230/12 ,  F05D2230/90 ,  F05D2250/232 ,  F05D2260/202 ,  Y10T29/49318 ,  Y10T29/49339 ,  Y10T29/49341 ,  Y10T29/49721 ,  Y10T29/49726 ,  Y10T29/4973 ,  Y10T29/49746

    Abstract: A method is disclosed for repairing defects in a gas turbine component 10 that comprises a substrate 58 and an existing coating 44 on the substrate 58. The article 10 includes cooling holes 18 having a predetermined air flow requirement and an outer shaped portion 52 and an inner metering portion 60. The method comprises removing the existing coating 44 and recoating the surface of the article with a nonoriginal coating. After the nonoriginal coating is applied onto the component, the cooling holes 18 that meet a predetermined inspection criteria are reworked to remove the excess nonoriginal coating deposited in the outer shaped portion 52 of the cooling holes 18. The reworking is done by receiving an electrode 52, having only a shaped portion with a preselected shape, in the outer shaped portion 50 of the cooling holes 18 thus restoring the cooling holes to the predetermined air flow requirement.

    Abstract translation: 公开了一种用于修复燃气涡轮机部件10中的缺陷的方法，该燃气涡轮机部件10包括衬底58和衬底58上的现有涂层44.制品10包括具有预定的空气流量要求的冷却孔18以及外部成形部分52和内部 计量部分60.该方法包括除去现有涂层44并用非原生涂层重新涂覆制品的表面。 在将非原生涂层涂覆到部件上之后，重新制造符合预定检验标准的冷却孔18以去除沉积在冷却孔18的外部成形部分52中的多余的非原生涂层。重新加工通过接收电极52 在冷却孔18的外部成形部分50中仅具有预定形状的成形部分，从而将冷却孔恢复到预定的气流要求。

    Method for removing a protective coating from a turbine blade airfoil in a repair process
    5.
    发明公开
    Method for removing a protective coating from a turbine blade airfoil in a repair process 有权
    在einem Reparaturverfahren的Verfahren zum Entfernen einer Schutzschicht derTurbinenschaufelblätter

    公开(公告)号：EP2128307A1

    公开(公告)日：2009-12-02

    申请号：EP09250999.1

    申请日：2009-03-31

    Applicant: United Technologies Corporation

    Inventor： Valez, Ramon M. ,  Draghi, Peter J. ,  Everett, Clyde R.

    IPC: C23F1/16 ,  C23F1/26 ,  C23F1/44 ,  B23P6/00 ,  F01D25/00

    CPC classification number: C23F1/44 ,  C23F1/16 ,  C23F1/26 ,  F01D5/005 ,  F05D2230/40 ,  F05D2300/132

    Abstract: A method for a repair process includes the steps of subjecting a substrate coated with at least one protective metallic coating to a nitric acid solution (12) and then subjecting the substrate with the at least one protective metallic coating to a hydrochloric acid solution (14) to remove the at least one protective metallic coating from the substrate. The substrate includes about 5 wt% - 15wt% chromium, about 2 wt% - 8wt% cobalt, about 2 wt% - 6wt% tungsten, about 0.5 wt% - 2.5wt% titanium, about 8 wt% - 16wt% tantalum, about 2 wt% - 8wt% aluminum, hafnium in an amount no greater than 1wt%, and a remainder of nickel.

    Abstract translation: 修复方法的方法包括以下步骤：将涂覆有至少一层保护性金属涂层的基材经受硝酸溶液（12），然后使至少一种保护性金属涂层的基材经盐酸溶液（14） 以从衬底去除至少一个保护性金属涂层。 基体包括约5重量％-15重量％的铬，约2重量％-8重量％的钴，约2重量％-6重量％的钨，约0.5重量％-2.5重量％的钛，约8重量％-16重量％的钽，约 2重量％-8重量％的铝，不超过1重量％的铪，剩余的镍。

    Gas turbine engine component repair
    6.
    发明公开
    Gas turbine engine component repair 失效
    气体涡轮发动机部件维修

    公开(公告)号：EP0504095A3

    公开(公告)日：1992-10-28

    申请号：EP92630028.6

    申请日：1992-03-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Smolinski, John J. ,  Danielsen, John R. ,  Draghi, Peter J.

    IPC: C21D1/00 ,  B23P6/00 ,  B21D11/20 ,  F01D5/00

    CPC classification number: F01D5/005 ,  B23K26/0081 ,  B23K2201/005 ,  C21D1/00 ,  Y10T29/49318 ,  Y10T29/49336 ,  Y10T29/49728 ,  Y10T29/49746

    Abstract: A procedure is described for the repair of gas turbine engine turbine components which involves the repair of cracks and other defects and the replacement of worn or eroded material followed by the laser melting of a thin layer of metal on the surface of the component in those areas requiring reconfiguration to return to the original dimensions. The reconfiguration by laser melting is also useful for new articles which are out of tolerance, and generally for shaping objects from metal sheet or plate.

    Abstract translation: 描述了用于维修燃气涡轮发动机涡轮机部件的过程，其涉及修复裂纹和其他缺陷，以及更换磨损或侵蚀的材料，然后在这些区域的部件表面上激光熔化金属薄层 需要重新配置以恢复原始尺寸。 通过激光熔化的重新配置对于超出公差的新制品也是有用的，并且通常用于从金属板或板成型物体。

    Abrasive airfoil tip
    8.
    发明公开
    Abrasive airfoil tip 审中-公开
    研磨翼型尖端

    公开(公告)号：EP2540961A3

    公开(公告)日：2018-01-10

    申请号：EP12169876.5

    申请日：2012-05-29

    Applicant: United Technologies Corporation

    Inventor： Wrabel, Peter ,  Draghi, Peter J. ,  Gregg, Shawn J.

    IPC: F01D5/00 ,  F01D5/20 ,  F01D5/28 ,  F01D11/12

    Abstract: An airfoil (32) comprises a substrate (54), a residual abrasive coating (58) and a supplemental abrasive coating (62). The substrate extends along a tip section (51) of the airfoil, from a leading edge (48) to a trailing edge (50). The residual abrasive coating (58) comprises a two-phase abrasive and metal matrix material bonded to the substrate, on the tip section of the airfoil. The supplemental abrasive coating (62) comprises a two-phase abrasive and metal matrix material bonded to the residual abrasive coating and to the substrate adjacent the residual abrasive coating, on the tip section (51) of the airfoil. The supplemental abrasive coating restores the airfoil to a nominal tip height (57) in the tip section.

    Abstract translation: 翼型件（32）包括基底（54），残余研磨涂层（58）和补充研磨涂层（62）。 基板沿翼型的尖端部分（51）从前缘（48）延伸到后缘（50）。 残余研磨涂层（58）包括在翼型的尖端部分上结合到基底的两相磨料和金属基质材料。 补充磨料涂层（62）包括两相磨料和金属基体材料，所述两相磨料和金属基体材料在翼型的尖端部分（51）上结合到残余磨料涂层和靠近残余磨料涂层的基底。 补充磨料涂层将翼型恢复到尖端部分中的标称尖端高度（57）。

    Method for repairing an apertured gas turbine component
    9.
    发明公开
    Method for repairing an apertured gas turbine component 有权
    Verfahren zum Reparieren einesgelöchertenGasturbinenbauteils

    公开(公告)号：EP1286020A2

    公开(公告)日：2003-02-26

    申请号：EP02254349.0

    申请日：2002-06-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Ducotey, Howard S. Jr. ,  Zuber, Robert J. ,  Draghi, Peter J.

    IPC: F01D5/00 ,  C23C4/02 ,  C23C4/18

    CPC classification number: B23P6/002 ,  B23H9/10 ,  B23H9/14 ,  B23P2700/06 ,  C23C4/02 ,  C23C4/18 ,  C23C28/32 ,  C23C28/345 ,  C23C28/3455 ,  F01D5/005 ,  F05D2230/12 ,  F05D2230/90 ,  F05D2250/232 ,  F05D2260/202 ,  Y10T29/49318 ,  Y10T29/49339 ,  Y10T29/49341 ,  Y10T29/49721 ,  Y10T29/49726 ,  Y10T29/4973 ,  Y10T29/49746

    Abstract: A method is disclosed for repairing defects in a gas turbine component 10 that comprises a substrate 58 and an existing coating 44 on the substrate 58. The article 10 includes cooling holes 18 having a predetermined air flow requirement and an outer shaped portion 52 and an inner metering portion 60. The method comprises removing the existing coating 44 and recoating the surface of the article with a nonoriginal coating. After the nonoriginal coating is applied onto the component, the cooling holes 18 that meet a predetermined inspection criteria are reworked to remove the excess nonoriginal coating deposited in the outer shaped portion 52 of the cooling holes 18. The reworking is done by receiving an electrode 52, having only a shaped portion with a preselected shape, in the outer shaped portion 50 of the cooling holes 18 thus restoring the cooling holes to the predetermined air flow requirement.

    Abstract translation: 公开了一种用于修复燃气轮机部件10中的缺陷的方法，该方法包括基板58和基板58上的现有涂层44.该物品10包括具有预定空气流量要求的冷却孔18和外部成形部分52以及内部 计量部分60.该方法包括移除现有涂层44并用非原始涂层重新涂覆制品的表面。 在将非原始涂层施加到部件上之后，再次对符合预定检查标准的冷却孔18进行加工，以去除沉积在冷却孔18的外部形状部分52中的多余非原始涂层。通过接收电极52 在冷却孔18的外形部分50中仅具有预定形状的成形部分，从而将冷却孔恢复到预定的气流要求。

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