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公开(公告)号：US4726101A
公开(公告)日：1988-02-23
申请号：US911681
申请日：1986-09-25
申请人： Peter J. Draghi , John P. Arrigoni
发明人： Peter J. Draghi , John P. Arrigoni
CPC分类号： B23P6/005 , B22F7/062 , B23K35/0244 , B23P6/007 , F01D5/005 , B23K35/0233 , Y10T29/49318 , Y10T29/49726 , Y10T29/49728 , Y10T29/4973 , Y10T29/49732 , Y10T29/49734 , Y10T29/49737 , Y10T29/49742 , Y10T29/4975 , Y10T403/479
摘要： A gas turbine vane (1) is subject to distortion and wear during operation or repair which results in an increase in the spacing between successive vanes (6 and 7) which define nozzle gas flow areas (8 and 9). During refurbishment, the nozzle spacing must be returned to the original dimension to insure optimum turbine performance. A build up of alloy in the wear area is accomplished by controllably applying layers of a tape (12) of uniform thickness to the vane. The tape includes a mixture of a binder and an alloy powder, which is compatible with the substrate alloy, with the mixture formed into a sheet of uniform thickness and having an adhesive backing. After applying the tape in layers to a desired thickness, the vane is heated to a temperature at which the binder and adhesive decompose and the alloy in the tape diffusion bonds with the substrate alloy. Utilization of this process reduces the cost of refurbishing used turbine vanes and avoids hot forming or bending processes which could damage the vanes.
摘要翻译： 燃气轮机叶片（1）在操作或修理期间经受变形和磨损，这导致限定喷嘴气体流动区域（8和9）的连续叶片（6和7）之间的间隔增加。 在翻新期间，喷嘴间距必须恢复到原始尺寸，以确保最佳涡轮机性能。 在磨损区域中合金的累积是通过可控地将均匀厚度的带（12）的层施加到叶片来实现的。 胶带包括与基材合金相容的粘合剂和合金粉末的混合物，混合物形成为均匀厚度的片材并具有粘合剂背衬。 在将带子施加到所需厚度之后，将叶片加热到粘合剂和粘合剂分解的温度，并且带中的合金扩散与基底合金结合。 该方法的利用降低了翻新二手涡轮叶片的成本，并避免了可能损坏叶片的热成型或弯曲过程。
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公开(公告)号：US6042879A
公开(公告)日：2000-03-28
申请号：US887506
申请日：1997-07-02
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。
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公开(公告)号：US5142778A
公开(公告)日：1992-09-01
申请号：US668580
申请日：1991-03-13
CPC分类号： F01D5/005 , B23K26/0081 , C21D1/00 , B23K2201/005 , Y10T29/49318 , Y10T29/49336 , Y10T29/49728 , Y10T29/49746
摘要： 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.
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公开(公告)号：US07032603B2
公开(公告)日：2006-04-25
申请号：US10893833
申请日：2004-07-19
IPC分类号： B08B9/00
CPC分类号： B08B9/00 , B08B9/0323 , B08B9/0325
摘要： The present invention relates to a method and a device for cleaning internal passageways within a component, such as a component to be used in an engine. The device for cleaning the internal passageway includes a first probe having a longitudinal axis and at least one nozzle oriented at an angle, preferably perpendicular, to the longitudinal axis. In a preferred embodiment, the first probe has two nozzles, both oriented perpendicular to the longitudinal axis, and offset 180 degrees from each other. The device further includes a second probe having a longitudinal axis and a nozzle in a tip end, which nozzle is oriented along the longitudinal axis. Preferably, the first and second probes are connected to a common manifold.
摘要翻译： 本发明涉及一种用于清洁部件内的内部通道的方法和装置，例如在发动机中使用的部件。 用于清洁内部通道的装置包括具有纵向轴线的第一探针和至少一个与纵向轴线成一定角度，优选垂直的喷嘴。 在优选实施例中，第一探针具有两个垂直于纵向轴线定向并且相互偏移180度的喷嘴。 该装置还包括具有纵向轴线的第二探针和在尖端中的喷嘴，该喷嘴沿着纵向轴线定向。 优选地，第一和第二探针连接到公共歧管。
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公开(公告)号：US06805140B2
公开(公告)日：2004-10-19
申请号：US10271681
申请日：2002-10-15
IPC分类号： B08B900
CPC分类号： B08B9/00 , B08B9/0323 , B08B9/0325
摘要： The present invention relates to a method and a device for cleaning internal passageways within a component, such as a component to be used in an engine. The device for cleaning the internal passageway includes a first probe having a longitudinal axis and at least one nozzle oriented at an angle, preferably perpendicular, to the longitudinal axis. In a preferred embodiment, the first probe has two nozzles, both oriented perpendicular to the longitudinal axis, and offset 180 degrees from each other. The device further includes a second probe having a longitudinal axis and a nozzle in a tip end, which nozzle is oriented along the longitudinal axis. Preferably, the first and second probes are connected to a common manifold.
摘要翻译： 本发明涉及一种用于清洁部件内的内部通道的方法和装置，例如在发动机中使用的部件。 用于清洁内部通道的装置包括具有纵向轴线的第一探针和至少一个与纵向轴线成一定角度，优选垂直的喷嘴。 在优选实施例中，第一探针具有两个垂直于纵向轴线定向并且相互偏移180度的喷嘴。 该装置还包括具有纵向轴线的第二探针和在尖端中的喷嘴，该喷嘴沿着纵向轴线定向。 优选地，第一和第二探针连接到公共歧管。
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公开(公告)号：US06171711B2
公开(公告)日：2001-01-09
申请号：US09412694
申请日：1999-10-05
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。
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公开(公告)号：US20130004328A1
公开(公告)日：2013-01-03
申请号：US13215897
申请日：2011-08-23
CPC分类号： F01D5/005 , F01D5/20 , F01D5/288 , F01D11/122 , F05D2230/31 , F05D2230/314 , F05D2230/80 , F05D2230/90 , Y02T50/672
摘要： An airfoil comprises a substrate, a residual abrasive coating and a supplemental abrasive coating. The substrate extends along a tip section of the airfoil, from a leading edge to a trailing edge. The residual abrasive coating comprises a two-phase abrasive and metal matrix material bonded to the substrate, on the tip section of the airfoil. The supplemental abrasive coating 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 of the airfoil. The supplemental abrasive coating restores the airfoil to a nominal tip height in the tip section.
摘要翻译： 翼型件包括基底，残留磨料涂层和辅助磨料涂层。 衬底沿着翼型的尖端部分从前缘延伸到后缘。 剩余的研磨涂层包括在翼型的末端部分上结合到基底的两相磨料和金属基质材料。 补充磨料涂层包括两个磨料和金属基质材料，其结合到残留的研磨剂涂层上，并且与邻近残留磨料涂层的基底在翼型的尖端部分上接合。 补充研磨涂层将翼型件恢复到尖端部分中的公称尖端高度。
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公开(公告)号：US07875200B2
公开(公告)日：2011-01-25
申请号：US12123504
申请日：2008-05-20
IPC分类号： B44C1/22
CPC分类号： C23F1/44 , C23F1/16 , C23F1/26 , F01D5/005 , F05D2230/40 , F05D2300/132
摘要： 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 and then subjecting the substrate with the at least one protective metallic coating to a hydrochloric acid solution to remove the at least one protective metallic coating from the substrate. The substrate includes about 5 wt %-15 wt % chromium, about 2 wt %-8 wt % cobalt, about 2 wt %-6 wt % tungsten, about 0.5 wt %-2.5 wt % titanium, about 8 wt %-16 wt % tantalum, about 2 wt %-8 wt % aluminum, hafnium in an amount no greater than 1 wt %, and a remainder of nickel.
摘要翻译： 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，然后用至少一种保护性金属涂层对基材进行盐酸溶液以除去至少一种 保护金属涂层从基材。 基材包括约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％ ％钽，约2重量％-8重量％的铝，不超过1重量％的铪，剩余的镍。
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公开(公告)号：US07204019B2
公开(公告)日：2007-04-17
申请号：US09935896
申请日：2001-08-23
CPC分类号： 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
摘要： A method for repairing defects in a gas turbine component that comprises a substrate and an existing coating on the substrate. The article includes cooling holes having a predetermined air flow requirement and an outer shaped portion and an inner metering portion. The method comprises removing the existing coating and recoating the surface of the article with a nonoriginal coating. After the nonoriginal coating is applied onto the component, the cooling holes that meet a predetermined inspection criteria are reworked to remove the excess nonoriginal coating deposited in the outer shaped portion of the cooling holes. The reworking is done by receiving an electrode, having only a shaped portion with a preselected shape, in the outer shaped portion of the cooling holes thus restoring the cooling holes to the predetermined air flow requirement.
摘要翻译： 一种用于修复燃气轮机部件中的缺陷的方法，所述方法包括基板和所述基板上的现有涂层。 该制品包括具有预定空气流量要求的冷却孔和外部形状部分和内部计量部分。 该方法包括用非原始涂层去除现有涂层并重新涂覆制品的表面。 在将非原始涂层施加到部件上之后，再次加工满足预定检查标准的冷却孔，以去除沉积在冷却孔外形部分中的多余非原始涂层。 通过在冷却孔的外形部分中容纳仅具有预定形状的成形部分的电极，从而将冷却孔恢复到预定的空气流量要求，从而进行返工。
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10.发明授权
公开(公告)号：US5293717A
公开(公告)日：1994-03-15
申请号：US920936
申请日：1992-07-28
IPC分类号： B24B5/01 , B24B49/02 , B24B51/00 , G05B19/401 , B24B49/00
CPC分类号： B24B5/01 , B24B49/02 , B24B51/00 , G05B19/401 , F05B2220/302 , Y02P90/265
摘要： A method for removing a predetermined amount of material from the inner surface of a circular article which deviates from a true circular configuration. The outer surface of the article is touch probed to determine its true location in space, and the data are stored in a computer memory. These data are then compared to engineering design data to establish the location of the surface to which material removal is desired. A control computer compares the measured data with the design data, and sends commands to the machine control system, causing the machine to remove the excess material down to the desired dimension. Any deviations from circular are compensated for by moving the article radially relative to the cutting tool as the article moves circumferentially relative to the cutting tool.
摘要翻译： 一种用于从圆形物品的内表面去除预定量的材料的方法，其偏离真正的圆形构造。 物品的外表面被触摸探测以确定其在空间中的真实位置，并且将数据存储在计算机存储器中。 然后将这些数据与工程设计数据进行比较，以建立需要去除材料的表面的位置。 控制计算机将测量数据与设计数据进行比较，并将命令发送到机器控制系统，使机器将多余的材料移除到所需尺寸。 当制品相对于切割工具周向移动时，通过相对于切割工具径向地移动物品来补偿任何与圆形的偏差。
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