专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US6165345A Electrochemical stripping of turbine blades 有权
标题翻译：涡轮叶片的电化学剥离
公开(公告)号：US6165345A
公开(公告)日：2000-12-26
申请号：US231057
申请日：1999-01-14
申请人： Kevin Updegrove , Frank Goodwater , William Fay
发明人： Kevin Updegrove , Frank Goodwater , William Fay
IPC分类号： F01D5/28 , C25F5/00 , C25F7/00 , F02C7/00
CPC分类号： C25F5/00
摘要： A process is provided to strip a metallic coating from a turbine blade comprising attaching the blade to a positive lead from a power supply, submersing a portion of the blade with a metallic coating to be stripped into a bath of acidic electro stripping solution, said bath containing a negative lead from a power supply attached to a conductive grid; and providing a current to the blade in the bath for a period of time effective to remove the coating on the portion of the blade.
摘要翻译：提供了一种从涡轮机叶片剥离金属涂层的方法，包括将叶片从电源附接到正极，将一部分刀片浸入金属涂层中以汽提到酸性电剥离溶液浴中，所述浴包含连接到导电电网的电源的负极; 并在电镀槽中向刀片提供电流一段时间以有效地去除刀片部分上的涂层。

2. 发明授权

US5800695A Plating turbine engine components 失效
标题翻译：电镀涡轮发动机部件
公开(公告)号：US5800695A
公开(公告)日：1998-09-01
申请号：US733028
申请日：1996-10-16
申请人： David Kang , Kevin Updegrove , Frank Goodwater
发明人： David Kang , Kevin Updegrove , Frank Goodwater
IPC分类号： C23C18/31 , C25D5/02 , C25D7/04 , B05D1/32
CPC分类号： C25D5/022 , B23P2700/06
摘要： A process is provided for plating a coating onto a gas turbine engine component without detrimentally effecting air flow through cooling holes by injecting a maskant into the cooling passage to fill the cooling holes with the maskant, plating the external surface of the component with a coating, then removing the maskant from the component.
摘要翻译：提供了一种用于将涂层电镀到燃气涡轮发动机部件上的过程，而不会通过将掩蔽剂注入到冷却通道中而不利地影响通过冷却孔的空气流动，以用掩蔽剂填充冷却孔，用涂层镀覆该部件的外表面，然后从组件中除去掩蔽剂。

3. 发明授权

US06173491B1 Method for replacing a turbine vane airfoil 有权
标题翻译：更换涡轮叶片翼型的方法
公开(公告)号：US06173491B1
公开(公告)日：2001-01-16
申请号：US09373277
申请日：1999-08-12
申请人： Frank Goodwater , David Kang
发明人： Frank Goodwater , David Kang
IPC分类号： B23P1500
CPC分类号： B23P6/002 , F01D5/005 , F01D9/041 , Y10T29/49318
摘要： A method for refurbishing turbine engine vanes in which the airfoils are removed and replaced. The original configuration of the vanes can be modified from a single casting or welded pair to a multi-piece component assembly comprising individual airfoil segments attached to the inner and outer platforms. The component assembly allows replacement of airfoils and/or platforms with improved castings in the form of improved alloys, improved physical geometry, or both. Modifications can be made in the vane class area without the need to modify the airfoil contour by brazing or other contour alteration processes. According to the method, the platforms are separated from the airfoils, the openings in the platforms are sealed, new airfoil sockets are cut into the platforms, and the vane is reassembled.
摘要翻译：一种用于翻新涡轮机叶片的方法，其中翼型件被移除和更换。叶片的原始构造可以从单个铸造或焊接对修改为包括附接到内部和外部平台的各个翼型段的多件式部件组件。组件组件允许以改进的合金，改进的物理几何形状或两者的形式更换具有改进的铸件的翼型件和/或平台。可以在叶片类区域进行修改，而不需要通过钎焊或其他轮廓改变过程来修改翼型轮廓。根据该方法，平台与翼型件分离，平台中的开口被密封，将新的翼型插座切成平台，并且叶片被重新组装。

4. 发明授权

US6154959A Laser cladding a turbine engine vane platform 失效
标题翻译：激光熔覆涡轮发动机叶片平台
公开(公告)号：US6154959A
公开(公告)日：2000-12-05
申请号：US375124
申请日：1999-08-16
申请人： Frank Goodwater , David Kang
发明人： Frank Goodwater , David Kang
IPC分类号： B23P9/00 , B23K26/00 , B23K26/34 , B23K101/34 , B23K103/16 , B23P6/00 , C22C19/00 , F01D5/00 , F01D5/28 , F02C7/00 , B23P15/00
CPC分类号： B23P6/002 , B23K26/32 , B23K26/342 , B23K35/001 , B23K35/3033 , B23K35/3046 , F01D5/005 , F01D5/288 , B23K2203/18 , B23K2203/26 , B23P2700/06 , F05D2240/80 , Y02T50/673 , Y10T29/49318 , Y10T29/49336
摘要： A method of refurbishing turbine engine vanes in which an alloy blend of a cobalt based superalloy and a nickel based superalloy corresponding to the base material of the turbine vane cobalt platform and the base nickel material of the replacement turbine vane airfoils is laser clad to the gaspath surfaces of the turbine vane platform. Laser cladding with the alloy blend allows the use of replacement airfoils with improved castings in the form of improved nickel based superalloys, and allows a coating to be uniformly applied to the gaspath surfaces of the vane. According to the method, the platforms are separated from the airfoils and laser clad with a blend of cobalt based superalloy and nickel based superalloy. The vane is then reassembled using the laser clad platform and at least one replacement airfoil.
摘要翻译：一种翻新涡轮发动机叶片的方法，其中对应于涡轮机叶片钴平台的基础材料的钴基超级合金和镍基超级合金的合金共混物和替换的涡轮叶片翼型件的基底镍材料被激光包覆到气路涡轮叶片平台的表面。使用合金混合物的激光熔覆允许以改进的镍基超级合金的形式使用具有改进的铸件的替换翼型，并且允许将涂层均匀地施加到叶片的气路面。根据该方法，将平台与翼型件分离，并用钴基超级合金和镍基超级合金的共混物激光包覆。然后使用激光包层平台和至少一个替换翼型将叶片重新组装。

5. 发明授权

US5554837A Interactive laser welding at elevated temperatures of superalloy articles 失效
标题翻译：超高温合金制品在高温下的交互式激光焊接
公开(公告)号：US5554837A
公开(公告)日：1996-09-10
申请号：US116670
申请日：1993-09-03
申请人： Frank Goodwater , Lang D. Huynh , David S. Kang , Hon Li , James M. Lizotte , Brian G. Doyle
发明人： Frank Goodwater , Lang D. Huynh , David S. Kang , Hon Li , James M. Lizotte , Brian G. Doyle
IPC分类号： F01D5/28 , B23K26/00 , B23K26/12 , B23K26/20 , B23K26/32 , B23K26/34 , B23K26/42 , C21D9/00 , C21D9/50 , C22C19/00 , F02C7/00 , B23K26/08
CPC分类号： B23K26/034 , B23K26/123 , B23K26/32 , B23K26/60 , B23K2201/001 , B23K2203/26 , F05B2220/302
摘要： A process and apparatus is provided for laser welding a nickel and/or cobalt based superalloy article comprising: preheating the entire weld area and adjacent region to a ductile temperature with an induction heat coil and maintaining such temperature during welding and solidification of the weld; and welding the preheated article utilizing a laser with a powder alloy feed with a control means controlling the laser, power feed and motion system on which the article is fixtured, wherein the control means includes a vision system which digitizes the weld area providing a path for the laser welding to follow.
摘要翻译：提供一种用于激光焊接镍和/或钴基超级合金制品的方法和装置，包括：用焊接热线圈将整个焊接区域和相邻区域预热到延性温度，并在焊接和凝固期间保持这种温度; 以及使用具有粉末合金进料的激光焊接所述预热制品，所述控制装置控制所述制品固定在其上的所述激光，供电和运动系统，其中所述控制装置包括将所述焊接区域数字化的视觉系统，激光焊接跟随。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式