BLADE OUTER AIR SEAL FOR A GAS TURBINE ENGINE
    1.
    发明申请
    BLADE OUTER AIR SEAL FOR A GAS TURBINE ENGINE 审中-公开
    燃气涡轮发动机叶片外部气密封

    公开(公告)号:WO2014028090A3

    公开(公告)日:2014-05-01

    申请号:PCT/US2013042969

    申请日:2013-05-29

    Abstract: A blade outer air seal (BOAS) segment according to an exemplary embodiment of the present disclosure can include a seal body having a radially inner face and a radially outer face that circumferentially extend between a first mate face and a second mate face and axially extend between a leading edge face and a trailing edge face. At least one of the first mate face, the second mate face, the radially outer face and the radially inner face can include an inner wall having a ledge and an undercut passage radially inward from the ledge that extends uninterrupted along a length of the ledge.

    Abstract translation: 根据本公开的示例性实施例的叶片外部空气密封件(BOAS)节段可以包括密封体,该密封体具有径向内面和径向外面,该径向内面和径向外面在第一配合面和第二配合面之间沿周向延伸, 前缘面和后缘面。 第一配合面,第二配合面,径向外面和径向内面中的至少一个可以包括内壁,该内壁具有凸缘和从凸缘径向向内的底切通道,该凸缘沿着凸缘的长度不间断地延伸。

    COOLING SYSTEM FOR A TURBINE VANE

    公开(公告)号:SG11201404364TA

    公开(公告)日:2014-10-30

    申请号:SG11201404364T

    申请日:2013-03-25

    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
    5.
    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

    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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