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    CUTTING BLADE TIPS
    6.
    发明申请
    CUTTING BLADE TIPS 有权
    切割刀片提示

    公开(公告)号：US20150354373A1

    公开(公告)日：2015-12-10

    申请号：US14725052

    申请日：2015-05-29

    Applicant: United Technologies Corporation

    Inventor： Changsheng Guo ,  Christopher W. Strock

    IPC: F01D5/20 ,  F01D11/12

    CPC classification number: F01D5/20 ,  F01D11/122 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/25 ,  F05D2230/90 ,  F05D2300/2112 ,  F05D2300/22 ,  F05D2300/2282 ,  F05D2300/2284 ,  F05D2300/30 ,  F05D2300/506 ,  Y10T29/49337

    Abstract: A blade includes a blade body extending from a blade root to an opposed blade tip surface along a longitudinal axis. The blade body defines a pressure side and a suction side. The blade body includes a cutting edge defined where the tip surface of the blade body meets the pressure side of the blade body. The cutting edge is configured to abrade a seal section of an engine case. A method for manufacturing a blade includes forming an airfoil with a root and an opposed tip surface along a longitudinal axis, wherein the airfoil defines a pressure side and a suction side. The method also includes forming a cutting edge where the tip surface of the airfoil meets the pressure side of the airfoil.

    Abstract translation: 叶片包括沿着纵向轴线从叶片根部延伸到相对的叶片尖端表面的叶片体。 叶片本体限定了压力侧和吸力侧。 叶片主体包括限定在叶片主体的尖端表面与叶片本体的压力侧相遇的切割边缘。 切削刃构造成磨损发动机壳体的密封部分。 一种叶片的制造方法，其特征在于，沿纵轴形成具有根部和相对的前端面的翼型，其特征在于，所述翼型部形成有压力侧和吸力侧。 该方法还包括形成切削刃，其中翼型件的顶端表面与翼型件的压力侧相遇。

    Coating for cooling air holes
    7.
    发明授权
    Coating for cooling air holes 有权

    公开(公告)号：US08962066B2

    公开(公告)日：2015-02-24

    申请号：US13487290

    申请日：2012-06-04

    Applicant: Steven W. Burd

    Inventor： Steven W. Burd

    IPC: B05D7/22

    CPC classification number: B05D5/005 ,  F01D5/005 ,  F01D5/186 ,  F01D5/288 ,  F05D2230/80 ,  F05D2230/90 ,  F05D2250/52 ,  F05D2300/2282 ,  Y10T428/24273

    Abstract: A method of repairing a component removes a prior coating from an underlying metal substrate. Small cooling air holes extend through the substrate and the coating that is to be removed. A new coating layer is placed on the metal substrate, and over the existing cooling air holes. The location of the cooling air holes is identified by inspecting the coated component for the location of indicators of the coating passing over the cooling air holes. The identified location of the indicators is used to control a cutting tool to remove any new coating from the cooling air holes. The basic method may also benefit new manufacture.

    COATING WITH ABRADABILITY PROPORTIONAL TO INTERACTION RATE
    8.
    发明申请
    COATING WITH ABRADABILITY PROPORTIONAL TO INTERACTION RATE 审中-公开
    涂层具有可交互性的比例

    公开(公告)号：US20120189434A1

    公开(公告)日：2012-07-26

    申请号：US13013949

    申请日：2011-01-26

    Applicant: Christopher W. Strock ,  Matthew E. Bintz

    Inventor： Christopher W. Strock ,  Matthew E. Bintz

    IPC: F01D5/20 ,  F16J15/16

    CPC classification number: F01D11/122 ,  C23C28/022 ,  C23C28/027 ,  F01D5/284 ,  F01D5/288 ,  F05D2250/132 ,  F05D2300/2106 ,  F05D2300/211 ,  F05D2300/2282 ,  Y02T50/67 ,  Y02T50/673

    Abstract: A seal in a gas turbine engine component between an airfoil with a radial outward end and a seal member adjacent it coated with an abrasive layer having a ceramic component in a matrix of a metal alloy with hexagonal BN. The ceramic component is selected from silica, quartz, alumina, zirconia and mixtures thereof and the metal is selected from nickel, cobalt, copper and iron. The ceramic ranges from about 1% to about 10% and the amount of nickel, cobalt, copper or iron will range from about 30% to about 60% by volume, and the balance is hBN.

    Abstract translation: 在具有径向向外端的翼型和邻近的翼形件之间的燃气涡轮发动机部件中的密封件涂覆有具有在具有六边形BN的金属合金的基体中的陶瓷部件的研磨层。 陶瓷组分选自二氧化硅，石英，氧化铝，氧化锆及其混合物，金属选自镍，钴，铜和铁。 陶瓷的范围为约1％至约10％，镍，钴，铜或铁的量为约30体积％至约60体积％，余量为hBN。

    COMPONENT HAVING AN ABRASIVE LAYER AND A METHOD OF APPLYING AN ABRASIVE LAYER ON A COMPONENT
    9.
    发明申请
    COMPONENT HAVING AN ABRASIVE LAYER AND A METHOD OF APPLYING AN ABRASIVE LAYER ON A COMPONENT 审中-公开
    具有磨耗层的组件和在组件上施加磨蚀层的方法

    公开(公告)号：US20100150730A1

    公开(公告)日：2010-06-17

    申请号：US12613906

    申请日：2009-11-06

    Applicant: Christopher Sellars ,  Matthew Hancock

    Inventor： Christopher Sellars ,  Matthew Hancock

    IPC: F01D5/28 ,  B05D5/02 ,  C23C4/10 ,  C25D7/00 ,  C25D3/00 ,  B23P15/02

    CPC classification number: F01D11/122 ,  F05D2300/2261 ,  F05D2300/2282 ,  Y10T29/49336 ,  Y10T428/24421

    Abstract: The tips of gas turbine engine turbine rotor blades are provided with an abrasive layer and the abrasive layer comprises chromised silicon carbide grit protruding from a layer of material. In particular the abrasive layer comprises a mixture of cubic boron nitride grit and chromised silicon carbide grit and the cubic boron nitride grit and the chromised silicon carbide grit protruding from the layer of material. The cubic boron nitride grit has a greater dimension than the chromised silicon carbide grit. The cubic boron nitride grit cuts the majority of a track in an abradable structure and then the chromised silicon carbide grit provides any additional cutting of the abradable structure.

    Abstract translation: 燃气涡轮发动机涡轮转子叶片的尖端设置有研磨层，研磨层包括从一层材料突出的镀铬碳化硅砂粒。 特别地，研磨层包括立方氮化硼砂粒和铬化碳化硅砂粒和立方氮化硼砂粒和从材料层突出的镀铬碳化硅砂粒的混合物。 立方氮化硼砂粒的尺寸大于铬化碳化硅砂粒的尺寸。 立方氮化硼砂粒切割可磨损结构中的大部分轨道，然后镀铬碳化硅砂粒提供可磨损结构的任何额外切割。

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