知搜-全球专利检索

  1. Login
  2. Sign Up

Search Results

24 records (took 0.021 seconds)

    Method determining hole completion
    1.
    发明授权
    Method determining hole completion 有权
    方法确定孔完成

    公开(公告)号：US09468991B2

    公开(公告)日：2016-10-18

    申请号：US14164539

    申请日：2014-01-27

    Applicant: General Electric Company

    Inventor： Shamgar Elijah McDowell ,  Zhaoli Hu ,  Abe Denis Darling ,  Douglas Anthony Serieno

    IPC: B23K26/00 ,  B23K26/04 ,  B23K26/03 ,  B23K26/38 ,  B23K26/16 ,  B23K26/40

    CPC classification number: B23K26/03 ,  B23K26/032 ,  B23K26/0622 ,  B23K26/146 ,  B23K26/16 ,  B23K26/388 ,  B23K26/389 ,  B23K26/40 ,  B23K2101/001 ,  B23K2101/34 ,  B23K2103/08 ,  B23K2103/50

    Abstract: The present disclosure provides a method for determining a hole completing in laser drilling of a hole in a near wall of an airfoil. The method includes drilling a hole in the near wall of the airfoil using a laser drill. The laser drill may move in a pattern relative to the airfoil. The method also includes determining when the drilling of the hole is complete based on a calculated time duration between successive breakthroughs of a laser from the laser drill through the near wall of the airfoil, or based on a calculated time duration since the latest breakthrough of the laser from the laser drill through the near wall of the airfoil.

    Abstract translation: 本公开提供了一种用于确定在翼型件的近壁中的孔的激光钻孔中完成孔的方法。 该方法包括使用激光钻孔在翼型件的近壁处钻孔。 激光钻可以以相对于翼型的图案移动。 该方法还包括基于来自激光钻头的激光在机翼的近壁之间的连续穿透之间的计算的持续时间来确定孔的钻孔何时完成，或者基于从最近的突破之后计算的持续时间 来自激光钻头的激光穿过机翼的近壁。

    SYSTEM AND METHOD FOR FORMING PASSAGES IN AN AIRFOIL
    3.
    发明申请
    SYSTEM AND METHOD FOR FORMING PASSAGES IN AN AIRFOIL 审中-公开
    在航空器中形成通道的系统和方法

    公开(公告)号：US20160214208A1

    公开(公告)日：2016-07-28

    申请号：US14602324

    申请日：2015-01-22

    Applicant: General Electric Company

    Inventor： Zhaoli Hu ,  Abe Denis Darling ,  Shamgar Elijah McDowell ,  Douglas Anthony Serieno

    IPC: B23K26/146 ,  B23K26/38 ,  F01D5/18

    CPC classification number: B23K26/146 ,  B23K26/38 ,  B23K2101/001 ,  B23P2700/06 ,  F01D5/187 ,  F05D2230/13 ,  F05D2260/20 ,  F05D2260/202

    Abstract: A system for forming a passage in an airfoil includes a liquid-jet guided laser that generates a laser beam confined within a fluid column, and a purge medium supply that is fluidly coupled to an aperture of the airfoil. A purge medium flows from the purge medium supply in a flow direction that is substantially parallel to an inner surface of the inner cavity. A controller is configured to direct the liquid-jet guided laser to cut a first passage through the outer surface. A centerline of the passage forms an acute angle with respect to the purge medium flow direction. The first passage is formed at a first radial position that is radially distal to the aperture. A method for forming passages in an airfoil using the system described herein is also disclosed.

    Abstract translation: 用于在翼型件中形成通道的系统包括产生限制在流体柱内的激光束的液体喷射引导激光器和流体地联接到翼型孔的吹扫介质供应。 吹扫介质从基本上平行于内腔的内表面的流动方向从吹扫介质供给流动。 控制器构造成引导液体喷射引导激光器切割穿过外表面的第一通道。 通道的中心线相对于吹扫介质流动方向形成锐角。 第一通道形成在径向远离孔的第一径向位置处。 还公开了使用本文所述的系统在翼型件中形成通道的方法。

    METHOD AND SYSTEM FOR CONFINED LASER DRILLING
    4.
    发明申请
    METHOD AND SYSTEM FOR CONFINED LASER DRILLING 审中-公开
    用于确定激光钻孔的方法和系统

    公开(公告)号：US20160199942A1

    公开(公告)日：2016-07-14

    申请号：US14592232

    申请日：2015-01-08

    Applicant: General Electric Company

    Inventor： Zhaoli Hu ,  Abe Denis Darling ,  Shamgar Elijah McDowell ,  Douglas Anthony Serieno

    IPC: B23K26/38 ,  F01D5/18 ,  B23K26/03

    CPC classification number: B23K26/032 ,  B23K26/146 ,  B23K26/389 ,  F01D5/186 ,  F05D2230/13 ,  F05D2260/202

    Abstract: A method for drilling a hole in a component is provided. The method includes directing a confined laser beam of a confined laser drill towards a near wall of the component and sensing a first characteristic of light from the hole in the near wall of the component with a first sensor positioned outside the component. The method also includes sensing a second characteristic of light from the hole in the near wall the component with a second sensor. The second characteristic of light is different from the first characteristic of light. Additionally, the method includes determining a hole progress based on the sensed first characteristic of light and the sensed second characteristic of light.

    Abstract translation: 提供了一种用于在组件中钻孔的方法。 该方法包括将受限激光钻的受限激光束引向部件的近壁，并且利用位于部件外部的第一传感器感测来自组件的近壁中的孔的光的第一特性。 该方法还包括利用第二传感器感测来自近壁中的孔的光的第二特性。 光的第二特性与光的第一特性不同。 另外，该方法包括基于感测的光的第一特性和感测到的光的第二特性来确定孔进展。

    SYSTEM AND METHOD FOR FORMING A COOLING HOLE IN AN AIRFOIL
    5.
    发明申请
    SYSTEM AND METHOD FOR FORMING A COOLING HOLE IN AN AIRFOIL 有权
    在空气中形成冷却孔的系统和方法

    公开(公告)号：US20160138405A1

    公开(公告)日：2016-05-19

    申请号：US14546357

    申请日：2014-11-18

    Applicant: General Electric Company

    Inventor： Zhaoli Hu ,  Abe Denis Darling ,  Shamgar Elijah McDowell ,  Douglas Anthony Serieno

    IPC: F01D5/18 ,  B23K26/384

    CPC classification number: B23K26/389 ,  B23K26/142 ,  B23K2101/001 ,  F05D2230/13

    Abstract: A system for forming a cooling hole in an airfoil includes a liquid-jet guided laser. The liquid-jet guided laser generates a laser beam confined within a fluid column. The fluid column/laser beam is directed at an outer surface of the airfoil. The system also includes a purge medium supply that is fluidly coupled to an aperture of the airfoil. The purge medium supply provides a purge medium into an inner cavity of the airfoil. The purge medium flow is oriented to flow in a flow direction that is substantially parallel to an inner surface of the cavity. A cooling hole is formed in the airfoil and extends through the outer surface and penetrates the inner surface of the cavity. A centerline of the cooling hole forms an acute angle with respect to the purge medium flow direction. The system described herein provides a method for manufacturing an airfoil.

    Abstract translation: 用于在翼型件中形成冷却孔的系统包括液体喷射引导激光器。 液体喷射引导激光器产生限制在流体柱内的激光束。 流体柱/激光束指向翼型件的外表面。 该系统还包括流体耦合到翼型的孔的清洗介质供应。 吹扫介质供应器将吹扫介质提供到翼型件的内腔中。 吹扫介质流被定向成在基本上平行于空腔的内表面的流动方向上流动。 在翼型件中形成冷却孔，并且延伸穿过外表面并穿过腔体的内表面。 冷却孔的中心线相对于吹扫介质流动方向形成锐角。 本文所述的系统提供了一种制造翼型的方法。

    METHOD AND SYSTEM FOR CONFINED LASER DRILLING
    9.
    发明申请
    METHOD AND SYSTEM FOR CONFINED LASER DRILLING 审中-公开
    用于确定激光钻孔的方法和系统

    公开(公告)号：US20160199945A1

    公开(公告)日：2016-07-14

    申请号：US14592217

    申请日：2015-01-08

    Applicant: General Electric Company

    Inventor： Shamgar Elijah McDowell ,  Zhaoli Hu ,  Abe Denis Darling ,  Douglas Anthony Serieno

    IPC: B23K26/70 ,  F01D5/18 ,  B23K26/402 ,  B23K26/382 ,  B23K26/03

    CPC classification number: B23K26/705 ,  B23K26/03 ,  B23K26/032 ,  B23K26/0622 ,  B23K26/146 ,  B23K26/382 ,  B23K26/389 ,  B23K26/40 ,  B23K26/402 ,  B23K2101/001 ,  B23K2103/172 ,  B23K2103/26 ,  F01D5/18 ,  F01D5/186 ,  F05D2230/13 ,  F05D2260/202 ,  Y02T50/675

    Abstract: A method for drilling a hole in a component is provided. The method includes directing a confined laser beam of the confined laser drill towards a near wall of the component and sensing a characteristic of light directed along a beam axis of the confined laser beam away from the component with a sensor. The method also includes determining one or more operational conditions based on the characteristic of the light sensed with the sensor. The one or more operational conditions includes at least one of a depth of the hole being drilled by the confined laser drill and a material into which the confined laser beam of the confined laser drill is being directed. Such a method may allow for more appropriate control of the confined laser drill.

    Abstract translation: 提供了一种用于在组件中钻孔的方法。 该方法包括将限制的激光钻孔的受限制的激光束引导到部件的近壁，并且感测沿着受限的激光束的光束轴指向远离部件的传感器的特性。 该方法还包括基于用传感器感测的光的特性确定一个或多个操作条件。 所述一个或多个操作条件包括被限制的激光钻孔钻出的孔的深度中的至少一个以及限制激光钻的受限激光束被引导到的材料中的至少一个。 这种方法可以允许对受限激光钻头进行更合适的控制。

    METHOD FOR DRILLING A HOLE IN AN AIRFOIL
    10.
    发明申请
    METHOD FOR DRILLING A HOLE IN AN AIRFOIL 有权
    用于钻探空气中的孔的方法

    公开(公告)号：US20150209899A1

    公开(公告)日：2015-07-30

    申请号：US14164506

    申请日：2014-01-27

    Applicant: General Electric Company

    Inventor： Zhaoli Hu ,  Abe Denis Darling ,  Shamgar Elijah McDowell ,  Douglas Anthony Serieno

    IPC: B23K26/03 ,  B23K26/38 ,  B23K26/14 ,  B23K26/00

    CPC classification number: B23K26/03 ,  B23K26/0006 ,  B23K26/146 ,  B23K26/388 ,  B23K26/389 ,  B23K2101/001 ,  B23K2103/172

    Abstract: A method for manufacturing an airfoil is provided, the method including drilling a hole in a near wall of the airfoil using a laser drill and activating a back strike protection in a cavity of the airfoil. The method additionally includes detecting a breakthrough of a laser from the laser drill through the near wall of the airfoil and subsequently initiating a drilling subroutine, with the drilling subroutine including a continued operation of the laser drill. Such a method may provide for an improved hole, such as a cooling passage, in the airfoil.

    Abstract translation: 提供了一种用于制造翼型的方法，所述方法包括使用激光钻孔在所述翼型件的近壁处钻孔，并且激活所述翼型件的空腔中的反击保护。 该方法还包括检测来自激光钻孔机的激光穿过翼型件的近壁的突破，并随后启动钻孔子程序，其中钻孔子程序包括激光钻孔机的连续操作。 这种方法可以在翼型件中提供改进的孔，例如冷却通道。

Patent Agency Ranking