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1. 发明申请

WO2014035516A3 GAS TURBINE ENGINE TURBINE VANE AIRFOIL PROFILE 审中-公开
标题翻译：燃气涡轮发动机涡轮叶片翼型轮廓
公开(公告)号：WO2014035516A3
公开(公告)日：2014-05-22
申请号：PCT/US2013044295
申请日：2013-06-05
申请人： UNITED TECHNOLOGIES CORP
发明人： SPANGLER BRANDON W , BERGMAN RUSSELL J
IPC分类号： F01D5/14 , F02C7/00
CPC分类号： F01D25/12 , F01D9/02 , F01D9/041 , F05D2240/81 , F05D2250/74 , F05D2260/202 , Y02T50/672 , Y02T50/673 , Y02T50/676
摘要： 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 inner and outer platforms respectively include inner and outer sets of film cooling holes. One of the inner and outer sets of film cooling holes are formed in substantial conformance with platform cooling hole locations described by one of the sets of Cartesian coordinates set forth in Tables 1 and 2. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate. The cooling holes with Cartesian coordinates in Tables 1 and 2 have a diametrical surface tolerance relative to the specified coordinates of 0.200 inches (5.08 mm).
摘要翻译：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连接的内部平台和外部平台。翼型包括由间隔开的压力侧和吸力侧连接的前缘和后缘以提供外部翼型表面。内部和外部平台分别包括内部和外部组膜冷却孔。内部和外部组膜冷却孔中的一个基本上与由表1和2中所述的笛卡尔坐标系中的一个描述的平台冷却孔位置一致地形成。笛卡尔坐标由轴向坐标，圆周坐标和相对于零坐标的径向坐标。表1和表2中具有笛卡尔坐标的冷却孔相对于0.200英寸（5.08毫米）的指定坐标具有直径表面公差。

2. 发明申请

WO2014035517A2 GAS TURBINE ENGINE TURBINE VANE PLATFORM CORE 审中-公开
标题翻译：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
申请人： UNITED TECHNOLOGIES CORP
发明人： BERGMAN RUSSELL J , BACH LEONARD A , SPANGLER BRANDON W
CPC分类号： 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
摘要： 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.
摘要翻译：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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