HYBRID AIRFOIL FOR A GAS TURBINE ENGINE
    3.
    发明申请
    HYBRID AIRFOIL FOR A GAS TURBINE ENGINE 审中-公开
    燃气涡轮发动机的混合式机翼

    公开(公告)号:WO2014011242A2

    公开(公告)日:2014-01-16

    申请号:PCT/US2013/032918

    申请日:2013-03-19

    Abstract: A hybrid airfoil for a gas turbine engine according to an exemplary embodiment of this disclosure can include a leading edge portion, a trailing edge portion, and an intermediate portion between the leading edge portion and the trailing edge portion. The leading edge portion can be made of a first material, the trailing edge portion can be made of a second material, and the intermediate portion can be made of a third material. At least two of the first material, the second material and the third material are different materials.

    Abstract translation: 根据本公开的示例性实施例的用于燃气涡轮发动机的混合翼型可以包括前缘部分,后缘部分以及在前缘部分和后缘部分之间的中间部分 。 前缘部分可以由第一材料制成,后缘部分可以由第二材料制成,并且中间部分可以由第三材料制成。 第一种材料,第二种材料和第三种材料中的至少两种是不同的材料。

    MULTI-DENSITY, MULTI-PROPERTY TURBINE COMPONENT
    4.
    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

    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。

    VORTEX GENERATORS FOR IMPROVED FILM EFFECTIVENESS
    6.
    发明申请
    VORTEX GENERATORS FOR IMPROVED FILM EFFECTIVENESS 审中-公开
    涡旋发生器提高电影效率

    公开(公告)号:WO2014021981A3

    公开(公告)日:2014-02-06

    申请号:PCT/US2013/043830

    申请日:2013-06-03

    Abstract: An airfoil includes a suction surface, a pressure surface, a first showerhead cooling hole and a second showerhead cooling hole. The suction surface and the pressure surface both extend axially between a leading edge and a trailing edge, as well as radially from a root section to a tip section. The first showerhead cooling hole and the second showerhead cooling hole both extend into pressure surface near the leading edge. The first showerhead cooling hole and the second showerhead cooling hole are angled in opposing directions.

    Abstract translation: 翼型件包括吸力表面,压力表面,第一喷淋头冷却孔和第二喷淋头冷却孔。 吸力表面和压力表面均在前缘和后缘之间以及从根部径向地延伸到尖端部分。 第一喷头冷却孔和第二喷头冷却孔均延伸到靠近前缘的压力表面中。 第一个喷头冷却孔和第二个喷头冷却孔的方向相反。

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