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    GAS TURBINE ENGINE TURBINE VANE PLATFORM CORE
    1.
    发明申请
    GAS TURBINE ENGINE TURBINE VANE PLATFORM CORE 审中-公开
    气体涡轮发动机涡轮叶片平台核心

    公开(公告)号：WO2014035517A2

    公开(公告)日：2014-03-06

    申请号：PCT/US2013044419

    申请日：2013-06-06

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BERGMAN RUSSELL J ,  BACH LEONARD A ,  SPANGLER BRANDON W

    CPC classification number: F01D9/02 ,  B22C9/04 ,  B22C9/10 ,  F01D5/187 ,  F01D9/041 ,  F01D25/12 ,  F05D2230/21 ,  F05D2230/211 ,  F05D2240/81 ,  F05D2250/185 ,  F05D2260/2214 ,  Y02T50/672 ,  Y02T50/676

    Abstract: A turbine vane for a gas turbine engine includes inner and outer platforms joined by a radially extending airfoil. The airfoil includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. The airfoil includes an airfoil cooling passage. A platform cooling passage is arranged within at least one of the inner and outer platforms. The platform cooling passage includes multiple cooling regions with one of the cooling regions arranged beneath the airfoil cooling passage.

    Abstract translation: 用于燃气涡轮发动机的涡轮叶片包括通过径向延伸的翼型件连接的内平台和外平台。 翼型件包括通过间隔开的压力和吸力侧连接的前缘和后缘，以提供外部翼面表面。 翼型件包括翼型件冷却通道。 平台冷却通道布置在内平台和外平台中的至少一个中。 平台冷却通道包括多个冷却区域，其中一个冷却区域布置在翼型冷却通道下方。

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