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    HARD PHASELESS METALLIC COATING FOR COMPRESSOR BLADE TIP
    171.
    发明申请
    HARD PHASELESS METALLIC COATING FOR COMPRESSOR BLADE TIP 审中-公开
    用于压缩机叶片的硬质非金属涂层

    公开(公告)号：US20160245110A1

    公开(公告)日：2016-08-25

    申请号：US14630958

    申请日：2015-02-25

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Christopher W. Strock ,  Changsheng Guo

    IPC: F01D11/12 ,  F01D25/24 ,  F04D29/32 ,  C22C27/06 ,  B23K31/02 ,  B22F3/105 ,  C22C27/04 ,  F01D5/28 ,  B23K26/34

    CPC classification number: F01D11/122 ,  B22F3/1055 ,  B23K26/34 ,  B23K31/02 ,  C22C27/04 ,  C22C27/06 ,  C23C30/00 ,  F01D5/288 ,  F04D29/324 ,  F05D2230/31 ,  F05D2240/307 ,  F05D2300/131 ,  F05D2300/506

    Abstract: A blade includes an airfoil having pressure and suction side walls extending in a spanwise direction from a blade root to a blade tip and a hard phaseless metallic coating located at the blade tip. An assembly includes a casing having an inner diameter surface, an abradable coating located on a portion of the inner diameter surface, a blade having a blade tip configured to rotate within the casing where the blade tip and the inner diameter surface of the casing form a seal, and a hard phaseless metallic coating located on the blade tip. A method of making a blade includes forming a blade having a tip and depositing a hard phaseless metallic coating on the blade tip.

    Abstract translation: 叶片包括具有从刀片根部到叶片尖端的翼展方向上延伸的压力和吸力侧壁的翼型件和位于叶片尖端处的硬质无量纲金属涂层。 一种组件包括具有内径表面的壳体，位于内径表面的一部分上的可磨损涂层，具有刀片尖端的刀片，刀片构造成在壳体内旋转，其中刀片尖端和壳体的内径表面形成 密封件和位于刀片尖端上的硬质无量纲金属涂层。 制造刀片的方法包括形成具有尖端的刀片，并在刀片尖端上沉积硬的无量纲金属涂层。

    Compressor Airfoil
    172.
    发明申请
    Compressor Airfoil 审中-公开
    压缩机翼型

    公开(公告)号：US20160238021A1

    公开(公告)日：2016-08-18

    申请号：US14623245

    申请日：2015-02-16

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： David Ulrich Furrer ,  Christopher W. Strock ,  Joseph G. Hillebrand ,  Matthew E. Bintz ,  Thomas D. Kasprow

    IPC: F04D29/32 ,  F04D29/02

    CPC classification number: F04D29/324 ,  F01D5/20 ,  F01D5/288 ,  F04D29/023 ,  F05D2230/90 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2240/307 ,  F05D2300/611 ,  Y02T50/672 ,  Y02T50/673

    Abstract: A compressor airfoil has a leading edge, a trailing edge, and a radially outboard edge connecting the leading edge and the trailing edge. The leading edge is formed according to a leading edge tip profile and the trailing edge is formed according to a trailing edge tip profile. The leading edge tip profile and/or trailing edge tip profile has a chamfer and/or a radius. In this manner, contact stress experienced by the compressor airfoil such as upon contact with a surrounding abradable seal are ameliorated. The leading edge tip profile and/or trailing edge tip profile are coated with an abrasive coating such as to enhance fitting of the abradable seal to the path of the compressor airfoil upon such contact.

    Abstract translation: 压缩机翼型件具有连接前缘和后缘的前缘，后缘和径向外侧边缘。 前缘是根据前缘尖端轮廓形成的，后缘根据后缘尖端轮廓形成。 前缘末端轮廓和/或后缘末端轮廓具有倒角和/或半径。 以这种方式，可以改善压缩机翼型的接触应力，例如与周围的可磨损密封件接触时的接触应力。 引导边缘末端轮廓和/或后缘末端轮廓涂覆有磨料涂层，以便在这种接触时增强可磨损密封件与压缩机翼型件的路径的配合。

    ABRASIVE BLADE TIP WITH IMPROVED WEAR AT HIGH INTERACTION RATE
    173.
    发明申请
    ABRASIVE BLADE TIP WITH IMPROVED WEAR AT HIGH INTERACTION RATE 审中-公开
    磨料刀片提高了高交织率的磨损

    公开(公告)号：US20160237832A1

    公开(公告)日：2016-08-18

    申请号：US14620310

    申请日：2015-02-12

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Christopher W. Strock

    IPC: F01D5/28 ,  F01D9/04 ,  B05D7/24

    Abstract: An abrasive blade tip coating comprising a blade tip having a top surface. A plurality of first grit particles are dispersed over the top surface of the blade tip. A plurality of second grit particles are closely packed between each of the plurality of first grit particles. The second grit particles having a nominal size smaller than the first grit particles. A matrix material is bonded to the top surface. The matrix material envelops the second grit particles. The matrix material is also bonded to and partially surrounds the first grit particles, wherein the first grit particles extend above the matrix material and the second grit particles relative to the top surface.

    Abstract translation: 一种研磨刀片涂层，其包括具有顶部表面的叶片尖端。 多个第一颗粒颗粒分散在叶片尖端的顶表面上。 在多个第一粒子之间，多个第二砂粒紧密堆积。 第二颗粒颗粒的标称尺寸小于第一颗粒颗粒。 基体材料结合到顶表面。 基质材料包围第二颗粒。 基质材料也结合并且部分地包围第一粒子颗粒，其中第一粒子颗粒相对于顶表面延伸到基体材料之上并且第二粒子颗粒延伸。

    Turbine Engine Component with Vibration Damping
    176.
    发明申请
    Turbine Engine Component with Vibration Damping 有权
    具有振动阻尼的涡轮发动机部件

    公开(公告)号：US20150361825A1

    公开(公告)日：2015-12-17

    申请号：US14763001

    申请日：2013-12-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Shahram Amini ,  Christopher W. Strock ,  Sergei F. Burlatsky ,  Dmitri Novikov

    IPC: F01D25/04 ,  F01D25/00 ,  F01D9/02

    CPC classification number: F01D25/04 ,  F01D5/16 ,  F01D5/282 ,  F01D5/288 ,  F01D9/02 ,  F01D25/005 ,  F05D2300/6032 ,  Y02T50/672 ,  Y10T156/10

    Abstract: A vibration resistant fan guide vane for a gas turbine engine is provided. The fan guide vane comprises a vibration damping component made of a MAXMET composite. The damping component may be a cover that covers some or all of the fan guide vane body. Alternatively, portions of the fan guide vane body or the entire vane body may be made from MAXMET composites. The disclosure makes use of the ultrahigh, fully reversible, non-linear elastic hysteresis behavior that MAXMET composites exhibit during cyclic elastic deformation in order to damp vibration.

    Abstract translation: 提供了一种用于燃气涡轮发动机的抗振动风扇导叶。 风扇导叶包括由MAXMET复合材料制成的减震部件。 阻尼部件可以是覆盖风扇导叶体的一些或全部的盖。 或者，风扇引导叶片体或整个叶片体的部分可以由MAXMET复合材料制成。 本公开使用MAXMET复合材料在循环弹性变形期间显示的超高度，完全可逆的非线性弹性滞后行为，以便减振。

    CUTTING BLADE TIPS
    177.
    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。

    Blade Rub Material
    179.
    发明申请
    Blade Rub Material 审中-公开
    刀片摩擦材料

    公开(公告)号：US20150337668A1

    公开(公告)日：2015-11-26

    申请号：US14761477

    申请日：2013-01-29

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Christopher W. Strock ,  Changsheng Guo

    IPC: F01D5/28 ,  C08L83/04 ,  C09D7/12 ,  C09D5/00 ,  C09D183/04

    CPC classification number: F01D5/28 ,  C08G77/24 ,  C08K7/22 ,  C08K7/28 ,  C08L2205/20 ,  C09D5/00 ,  C09D183/04 ,  F01D11/001 ,  F01D11/125 ,  F05D2300/437 ,  Y10T428/24008 ,  Y10T428/24628 ,  C08L83/04 ,  C08L83/08

    Abstract: One aspect of the disclosure involves a rub material comprising a polymeric matrix and polymer micro-balloon filler in the matrix. In one or more embodiments of any of the foregoing embodiments, the matrix comprises a silicone. In one or more embodiments of any of the foregoing embodiments, the rub material is at least I.0 mm thick. In one or more embodiments of any of the foregoing embodiments, the silicone is selected from the group consisting of dimethyl- and fluoro-silicone rubbers and their copolymers. In one or more embodiments of any of the foregoing embodiments, the micro-balloons at least locally have a concentration of 5-50% by volume.

    Abstract translation: 本公开的一个方面涉及在基质中包含聚合物基质和聚合物微球填料的擦擦材料。 在任何前述实施方案的一个或多个实施方案中，基质包含硅氧烷。 在任何前述实施例的一个或多个实施例中，摩擦材料至少为1.0mm厚。 在任何前述实施方案的一个或多个实施方案中，硅氧烷选自二甲基和氟硅橡胶及其共聚物。 在任何前述实施方案的一个或多个实施方案中，微球至少局部地具有5-50体积％的浓度。

    Abrasive Tip Blade Manufacture Methods
    180.
    发明申请
    Abrasive Tip Blade Manufacture Methods 有权
    磨料刀片制造方法

    公开(公告)号：US20150275679A1

    公开(公告)日：2015-10-01

    申请号：US14636676

    申请日：2015-03-03

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Christopher W. Strock

    IPC: F01D5/28 ,  B05D3/00 ,  B05D1/02

    CPC classification number: F01D5/288 ,  B05D1/02 ,  B05D3/007 ,  C23C4/06 ,  C23C4/08 ,  C23C24/06 ,  C23C28/044 ,  F01D11/122

    Abstract: A method is disclosed for manufacturing a blade tip coating. The blade tip coating (152) comprising an abrasive (156) and a matrix (154). The method comprises forming a mixture comprising the abrasive, a precursor of the matrix, and an additional particulate (158). The mixture is pressed, the additional particulate acting as a stop to limit thickness reduction of the mixture.

    Abstract translation: 公开了一种制造叶片尖端涂层的方法。 刀片涂层（152）包括磨料（156）和基质（154）。 该方法包括形成包含研磨剂，基质的前体和另外的颗粒（158）的混合物。 混合物被压制，另外的颗粒作为停止以限制混合物的厚度减小。

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