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    GAS TURBINE ENGINE TURBINE VANE AIRFOIL PROFILE
    1.
    发明申请
    GAS TURBINE ENGINE TURBINE VANE AIRFOIL PROFILE 审中-公开
    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

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SPANGLER BRANDON W ,  BERGMAN RUSSELL J

    IPC: F01D5/14 ,  F02C7/00

    CPC classification number: F01D25/12 ,  F01D9/02 ,  F01D9/041 ,  F05D2240/81 ,  F05D2250/74 ,  F05D2260/202 ,  Y02T50/672 ,  Y02T50/673 ,  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 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).

    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。

    GAS TURBINE ENGINE TURBINE VANE PLATFORM CORE
    2.
    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。

    COOLING SYSTEM FOR A TURBINE VANE
    3.
    发明专利
    COOLING SYSTEM FOR A TURBINE VANE 未知

    公开(公告)号：SG11201404364TA

    公开(公告)日：2014-10-30

    申请号：SG11201404364T

    申请日：2013-03-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： PAPPLE MICHAEL ,  ENNACER MOHAMMED ,  DABBS THURMAN CARLO ,  LUTJEN PAUL M ,  CAPRARIO JOSEPH T ,  BERGMAN RUSSELL J ,  GREGG SHAWN J

    IPC: F01D25/08 ,  F01D5/18 ,  F01D9/06 ,  F02C7/12

    Abstract: A cooling system for a gas turbine engine includes a first plenum, a first cooling flow passageway, and a second cooling flow passageway. The first cooling flow passageway is in fluid communication with the first plenum and with a first airfoil cooling channel within an airfoil of the stator vane. The first airfoil cooling channel is for cooling a leading edge of the airfoil. The second cooling flow passageway is in fluid communication with the first plenum and with a platform cooling channel within an outer diameter platform of the stator vane. The first cooling flow passageway and the second cooling flow passageway are disposed within a mounting hook. The first cooling flow passageway and the second cooling flow passageway are not in fluid communication with each other.

    COOLING SYSTEM FOR A TURBINE VANE
    4.
    发明公开
    COOLING SYSTEM FOR A TURBINE VANE 审中-公开
    KÜHLSYSTEMFÜREINE TURBINENSCHAUFEL

    公开(公告)号：EP2834498A4

    公开(公告)日：2016-07-06

    申请号：EP13772338

    申请日：2013-03-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BERGMAN RUSSELL J ,  GREGG SHAWN J ,  PAPPLE MICHAEL ,  LUTJEN PAUL M ,  CAPRARIO JOSEPH T ,  ENNACER MOHAMMED ,  DABBS THURMAN CARLO

    IPC: F02C7/12 ,  F01D5/18 ,  F01D25/08 ,  F01D25/14 ,  F01D25/24

    CPC classification number: F01D25/246 ,  F01D25/14 ,  F05D2240/81

    Abstract: A cooling system for a gas turbine engine includes a first plenum, a first cooling flow passageway, and a second cooling flow passageway. The first cooling flow passageway is in fluid communication with the first plenum and with a first airfoil cooling channel within an airfoil of the stator vane. The first airfoil cooling channel is for cooling a leading edge of the airfoil. The second cooling flow passageway is in fluid communication with the first plenum and with a platform cooling channel within an outer diameter platform of the stator vane. The first cooling flow passageway and the second cooling flow passageway are disposed within a mounting hook. The first cooling flow passageway and the second cooling flow passageway are not in fluid communication with each other.

    Abstract translation: 用于燃气涡轮发动机的冷却系统包括第一增压室，第一冷却流通道和第二冷却流通道。 第一冷却流通道与第一增压室流体连通，并且与定子叶片的翼型内的第一翼型冷却通道形成流体连通。 第一翼型冷却通道用于冷却翼型件的前缘。 第二冷却流通道与第一集气室流体连通，并且在定子叶片的外径平台内具有平台冷却通道。 第一冷却流通道和第二冷却流通道设置在安装钩内。 第一冷却流路和第二冷却流路不相互流体连通。

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