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    AIRFOIL WITH VARIABLE TRIP STRIP HEIGHT
    1.
    发明申请
    AIRFOIL WITH VARIABLE TRIP STRIP HEIGHT 审中-公开
    带可变行程杆高度的AIRFOIL

    公开(公告)号：WO2014105236A2

    公开(公告)日：2014-07-03

    申请号：PCT/US2013/061857

    申请日：2013-09-26

    Applicant: UNITED TECHNOLOGIES CORPORATION ,  RILEY, Sarah ,  BOEKE, Mark A. ,  DEGRAY, Jeffrey J. ,  GREGG, Shawn J.

    Inventor： RILEY, Sarah ,  BOEKE, Mark A. ,  DEGRAY, Jeffrey J. ,  GREGG, Shawn J.

    CPC classification number: F01D25/12 ,  F01D5/187 ,  F01D9/02 ,  F05D2240/12 ,  F05D2240/126 ,  F05D2240/127 ,  F05D2240/81 ,  F05D2250/183 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/672 ,  Y02T50/676

    Abstract: An airfoil component for a gas turbine engine includes an airfoil extending from a platform. At least one of the airfoil and the platform includes a cooling passage defined by a surface. A chevron-shaped trip strip extends from the surface into the cooling passage at a trip strip height along a length. The trip strip height varies along the length. A turbine vane for a gas turbine engine includes inner and outer platforms. A cooling passage is provided in the inner platform. The cooling passage is provided by first and second radially extending legs spaced circumferentially apart from one another and joined to one another by a circumferential passage. A pair of airfoils extend radially from the same inner platform. A trip strip extends from the surface into the circumferential passage at a trip strip height along a length. The trip strip height varying along the length.

    Abstract translation: 用于燃气涡轮发动机的翼型件组件包括从平台延伸的翼型件。 翼型件和平台中的至少一个包括由表面限定的冷却通道。 人字形跳闸条从表面延伸到沿着长度的跳闸条高度处的冷却通路。 跳闸条高度沿长度变化。 用于燃气涡轮发动机的涡轮叶片包括内部和外部平台。 内部平台上设有冷却通道。 冷却通道由第一和第二径向延伸的腿部提供，所述第一和第二径向延伸的腿部彼此周向间隔开并且通过周向通道彼此连接。 一对翼型从相同的内部平台径向延伸。 跳闸条从表面沿着长度以跳闸条高度从表面延伸到圆周通道中。 跳闸高度沿长度变化。

    TAPERED THERMAL COATING FOR AIRFOIL
    4.
    发明申请
    TAPERED THERMAL COATING FOR AIRFOIL 审中-公开
    用于气流的热转印热涂层

    公开(公告)号：WO2013172903A2

    公开(公告)日：2013-11-21

    申请号：PCT/US2013/027232

    申请日：2013-02-22

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： LEVINE, Jeffrey R. ,  GREGG, Shawn J.

    IPC: F01D5/28 ,  F01D5/14 ,  F02C7/00 ,  F02K3/00

    CPC classification number: F01D5/188 ,  Y02T50/676

    Abstract: An airfoil comprises pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section, the root section and the tip section defining a span therebetween. A thermal coating extends from the root section of the airfoil toward the tip section of the airfoil. A relative coating thickness of the thermal coating decreases by at least thirty percent at full span in the tip section, as compared to minimum span in the root section.

    Abstract translation: 翼型件包括从前缘到后缘轴向延伸的压力和抽吸表面，并且从根部到尖端部分径向地延伸，根部和末端部分限定了它们之间的跨度。 热涂层从翼型的根部朝向翼型的末端部分延伸。 与根部中的最小跨度相比，热涂层的相对涂层厚度在末端部分的全跨度处降低至少30％。

    MULTI-DENSITY, MULTI-PROPERTY TURBINE COMPONENT
    5.
    发明申请
    MULTI-DENSITY, MULTI-PROPERTY TURBINE COMPONENT 审中-公开
    多重密度，多属性涡轮机组件

    公开(公告)号：WO2015053946A1

    公开(公告)日：2015-04-16

    申请号：PCT/US2014/057358

    申请日：2014-09-25

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： GREGG, Shawn J. ,  STAROSELSKY, Alexander ,  SRINIVASAN, Gajawalli V.

    IPC: B22F3/105 ,  B22F3/11 ,  F01D5/28

    CPC classification number: B23K26/342 ,  B22F3/1055 ,  B22F3/11 ,  B22F5/04 ,  B22F2207/13 ,  B22F2207/17 ,  B23K26/0006 ,  B23K26/12 ,  B23K26/144 ,  B23K2203/02 ,  B23K2203/08 ,  B23K2203/14 ,  B33Y10/00 ,  B33Y80/00 ,  F01D5/18 ,  F01D5/28 ,  Y02P10/295

    Abstract: A method of forming a metal component having different regions containing different grain sizes and porosities is by additive manufacturing. The method includes spreading a layer of starting powder on a temperature controlled moveable platform in a heated chamber with atmosphere and temperature control. Selected areas of the powder are melted and solidified with a computer controlled focused energy beam. The cooled platform is then indexed down and the process repeated. The grain size of the melted and solidified region can be controlled by the cooling rate during solidification which, in turn is controlled by the temperature of the chamber and the temperature of the cooled moveable platform.

    Abstract translation: 通过添加制造，形成具有不同粒径和孔隙率不同区域的金属成分的方法。 该方法包括在加热室中的温度控制的可移动平台上涂覆起始粉末层，其中大气和温度控制。 粉末的选定区域用计算机控制的聚焦能量束熔化和固化。 然后冷却的平台被索引并重复该过程。 熔化和固化区域的晶粒尺寸可以通过凝固过程中的冷却速度进行控制，而冷却速度又由室内的温度和冷却的可移动平台的温度控制。

    GAS TURBINE ENGINE ASYMMETRIC NOZZLE GUIDE VANES
    6.
    发明申请
    GAS TURBINE ENGINE ASYMMETRIC NOZZLE GUIDE VANES 审中-公开
    气体涡轮发动机不对称喷嘴导向槽

    公开(公告)号：WO2014099077A2

    公开(公告)日：2014-06-26

    申请号：PCT/US2013/061704

    申请日：2013-09-25

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： GREGG, Shawn J. ,  OTERO, Edwin

    CPC classification number: F02C3/14 ,  F23R3/28 ,  F23R3/50 ,  F23R2900/00014

    Abstract: A gas turbine engine includes a multiple of Nozzle Guide Vanes (NGVs) arranged asymmetrically and a multiple of NGVs clocked with respect to the multiple of fuel nozzles around a 360 degree circumference.

    Abstract translation: 燃气涡轮发动机包括多个非对称布置的喷嘴导向叶片（NGV），并且相对于围绕360度圆周的多个燃料喷嘴计时的多个NGV。

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