公开(公告)号：EP1952932A3

公开(公告)日：2010-05-26

申请号：EP08100850.0

申请日：2008-01-24

申请人： GENERAL ELECTRIC COMPANY

发明人： Qi, Huan ,  Singh, Prabhjot ,  Azer, Magdi Naim

IPC分类号： B23K26/34 ,  B23K101/00

CPC分类号： F01D5/005 ,  B22F3/1055 ,  B22F5/04 ,  B23K26/342 ,  B23K35/0244 ,  B23K35/3033 ,  B23K35/3046 ,  B23K35/3053 ,  B23K35/325 ,  B23K2101/001 ,  B23P6/007 ,  C23C24/106 ,  F01D5/02 ,  F01D5/147 ,  F04D29/388 ,  F05D2220/30 ,  F05D2230/31 ,  F05D2230/80 ,  Y02P10/295

摘要： A method is disclosed for laser cladding a substrate 3, comprising providing the substrate 3; depositing a first determined variable bead width of a material along a toolpath upon the substrate; depositing a second adjacent determined variable bead width of a material along the toolpath which overlaps the first determined variable bead width of deposited material 7; continuing to deposit a plurality of overlapping predetermined adjacent variable bead widths of a material until a first material layer is complete; forming a second material layer by depositing a plurality of overlapping predetermined variable bead widths of a material on top of the first material layer; and continuing to deposit material layers on top of deposited material layers until the cladding is complete; wherein the variable bead width of the deposited material is controlled by a computer having a plurality of input parameters to maintain an approximately constant percent of bead width overlap.

公开(公告)号：EP2366476B1

公开(公告)日：2014-07-02

申请号：EP10156136.3

申请日：2010-03-10

申请人： General Electric Company

发明人： Qi, Huan ,  Singh, Prabhjot ,  Desander, Donald Brett ,  Azer, Magdi Naim ,  Tewari, Sudhir Kumar ,  Gledhill, Mark Douglas ,  Sabato, Joseph Giancarlo ,  Rockstroh, Todd Jay

IPC分类号： B22F3/105 ,  B22F7/06

CPC分类号： B22F3/1055 ,  B22C9/04 ,  B22F7/062 ,  B22F2007/068 ,  Y02P10/292 ,  Y02P10/295

摘要： A method for making a turbine airfoil (18) includes providing a mold core (40) and an outer shell (42) which cooperatively define a cavity in the shape of a hollow airfoil (18) having an outer wall, a root, and a tip. A tip portion of the core (40) extends completely through the portion of the cavity defining the tip of the airfoil (18). The core (40) is restrained to prevent movement between the core (40) and outer shell (42). Molten metal is introduced into the cavity and solidified to form an airfoil (18) having at least one outer wall which defines an open tip and a hollow interior. A metallic tip cap is formed on the outer wall which substantially closes off the open tip. The tip cap may be formed by packing the airfoil (18) with metallic powder; and laser sintering the exposed powder so as to form a tip cap which is metallurgically bonded to the outer wall.

公开(公告)号：EP1952932B1

公开(公告)日：2019-04-24

申请号：EP08100850.0

申请日：2008-01-24

申请人： GENERAL ELECTRIC COMPANY

发明人： Qi, Huan ,  Singh, Prabhjot ,  Azer, Magdi Naim

IPC分类号： B22F3/105 ,  B22F5/04 ,  B23K35/30 ,  B23K35/32 ,  B23P6/00 ,  B23K35/02 ,  B23K26/342 ,  B23K101/00 ,  C23C24/10

公开(公告)号：EP2366476A1

公开(公告)日：2011-09-21

申请号：EP10156136.3

申请日：2010-03-10

申请人： General Electric Company

发明人： Qi, Huan ,  Singh, Prabhjot ,  Desander, Donald Brett ,  Azer, Magdi Naim ,  Tewari, Sudhir Kumar ,  Gledhill, Mark Douglas ,  Sabato, Joseph Giancarlo ,  Rockstroh, Todd Jay

IPC分类号： B22F3/105 ,  B22F7/06

CPC分类号： B22F3/1055 ,  B22C9/04 ,  B22F7/062 ,  B22F2007/068 ,  Y02P10/292 ,  Y02P10/295

摘要： A method for making a turbine airfoil (18) includes providing a mold core (40) and an outer shell (42) which cooperatively define a cavity in the shape of a hollow airfoil (18) having an outer wall, a root, and a tip. A tip portion of the core (40) extends completely through the portion of the cavity defining the tip of the airfoil (18). The core (40) is restrained to prevent movement between the core (40) and outer shell (42). Molten metal is introduced into the cavity and solidified to form an airfoil (18) having at least one outer wall which defines an open tip and a hollow interior. A metallic tip cap is formed on the outer wall which substantially closes off the open tip. The tip cap may be formed by packing the airfoil (18) with metallic powder; and laser sintering the exposed powder so as to form a tip cap which is metallurgically bonded to the outer wall.

摘要翻译： 一种用于制造涡轮机翼（18）的方法包括提供模芯（40）和外壳（42），所述模芯和外壳（42）协同地限定了具有外壁，根部和中空翼型件 小费。 芯部（40）的尖端部分完全延伸穿过限定翼型件（18）尖端的空腔部分。 芯（40）被限制以防止芯（40）和外壳（42）之间的移动。 将熔融金属引入空腔中并固化以形成具有至少一个限定开口尖端和中空内部的外壁的翼型件（18）。 金属顶盖形成在外壁上，基本封闭开口尖端。 顶盖可以通过用金属粉末包装机翼（18）而形成; 并激光烧结暴露的粉末，以形成冶金结合到外壁的尖端盖。