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    Rotary probe for cleaning an internal cavity
    13.
    发明公开
    Rotary probe for cleaning an internal cavity 有权
    旋转探针未工艺腔体的纯化

    公开(公告)号：EP1577027A1

    公开(公告)日：2005-09-21

    申请号：EP05251600.2

    申请日：2005-03-16

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Velez, Ramon M., Jr. ,  Draghi, Peter J.

    IPC: B08B9/00 ,  B08B9/087 ,  F01D25/00

    CPC classification number: B08B9/00 ,  B08B1/04 ,  B08B9/087

    Abstract: Foreign material is dislodged from a hard to reach region of an object by passing a rigid (24) elongated tubular guide in close proximity to the hard to reach region. The upper tip of the guide is bent so that it can be directed at the hard to reach region and a wire (32) is passed through the guide into the hard to reach region. The lower portion of the wire that extends outwardly from the bottom of the guide and the wire is rotated at a speed sufficient to dislodge unwanted foreign material from the hard to reach region.

    Apparatus and method for cleaning airfoil internal cavities
    14.
    发明公开
    Apparatus and method for cleaning airfoil internal cavities 有权
    Vorrichtung und Verfahren zur Reinigung vonHohlräumenvon Turbinenschaufeln

    公开(公告)号：EP1410853A1

    公开(公告)日：2004-04-21

    申请号：EP03256489.0

    申请日：2003-10-15

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Velez, Jr., Ramon M. ,  Draghi, Peter J.

    IPC: B08B9/032 ,  F01D25/00 ,  F01D5/00

    CPC classification number: B08B9/00 ,  B08B9/0323 ,  B08B9/0325

    Abstract: The present invention discloses a method and a device 20 for cleaning internal passageways 40,50 within a component, such as a component to be used in an engine. The device 20 includes a first probe 22 having a longitudinal axis 32 and at least one nozzle 34 oriented at an angle, preferably perpendicular, to the longitudinal axis 32. In a preferred embodiment, the first probe 22 has two nozzles 34,34', both oriented perpendicular to the longitudinal axis 32, and offset 180 degrees from each other. The device further includes a second probe 24 having a longitudinal axis 44 and a nozzle 48 in a tip end 46, which nozzle 48 is oriented along the longitudinal axis 44. Preferably, the first and second probes 22,24 are connected to a common manifold 26.

    Abstract translation: 具有纵向轴线和喷嘴的清洁流体分配探针（22）延伸到发动机部件（42）内的内部空腔（40）中。 喷嘴相对于探针的纵向轴线以预定的角度定向。 还包括用于发动机部件内腔清洁方法的独立权利要求。

    Method for repairing turbine engine components
    15.
    发明公开
    Method for repairing turbine engine components 有权
    InstandsetzungsverfahrenfürTurbinenmotorenteilen

    公开(公告)号：EP1354977A2

    公开(公告)日：2003-10-22

    申请号：EP03251391.3

    申请日：2003-03-07

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Bose, Sudhangshu ,  Cetel, Alan D. ,  Draghi, Peter J. ,  Pietruska, Norman

    IPC: C23C4/02 ,  F01D5/00

    CPC classification number: C23G1/20 ,  B23P6/007 ,  C23C10/02 ,  Y10T29/49318 ,  Y10T29/49336 ,  Y10T29/49726 ,  Y10T29/49737 ,  Y10T29/49746

    Abstract: The present invention relates to a method for repairing turbine engine components, such as vanes and blades, which have airfoils. The method broadly comprises removing oxidation debris from portions of the component by blending areas exhibiting thermal barrier coating spall and/or oxidation damage, removing a ceramic insulating layer from the component, and blending surfaces of the component where nicks, dents, and/or cracks are located. If the component has a depleted aluminum zone, the depleted zone is either removed or replenished. Further, a tip portion of the component, if damaged, is restored and tip abrasives are applied to restore the component's cutting ability. Thereafter, a ceramic coating is applied to the component.

    Abstract translation: 本发明涉及一种用于修理具有翼型的涡轮发动机部件（例如叶片和叶片）的方法。 该方法广泛地包括通过混合显示出热障涂层剥落和/或氧化损伤的区域来除去部件的部分的氧化碎屑，从该组件中除去陶瓷绝缘层，以及将部件的表面与缺口，凹痕和/或裂纹 位于。 如果组件具有耗尽的铝区，则耗尽的区域被去除或补充。 此外，如果损坏的部件的尖端部分被恢复，并且施加尖端磨料以恢复部件的切割能力。 此后，将陶瓷涂层施加到部件上。

    Abrasive airfoil tip
    17.
    发明公开
    Abrasive airfoil tip 审中-公开
    Schleifschaufelspitze

    公开(公告)号：EP2540961A2

    公开(公告)日：2013-01-02

    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: 机翼（32）包括基底（54），残留磨料涂层（58）和辅助磨料涂层（62）。 衬底沿着翼型件的前端部分（51）从前缘（48）延伸到后缘（50）。 剩余磨料涂层（58）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（62）包括在翼型的末端部分（51）上结合到残余磨料涂层和邻近残留研磨涂层的基底上的两相磨料和金属基质材料。 补充磨料涂层将翼型件恢复到尖端部分中的公称顶端高度（57）。

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