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    TURBINE AIRFOIL COOLING CORE EXIT
    12.
    发明公开
    TURBINE AIRFOIL COOLING CORE EXIT 审中-公开
    汽轮机冷却启动器

    公开(公告)号：EP3060761A4

    公开(公告)日：2016-10-19

    申请号：EP14856429

    申请日：2014-09-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： QUACH SAN ,  SLAVENS THOMAS N

    IPC: F01D5/18 ,  B22C9/10 ,  F01D25/12 ,  F02C7/18

    CPC classification number: F01D5/187 ,  B22C9/00 ,  B22C9/10 ,  B22C9/24 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/31 ,  F05D2230/50 ,  F05D2240/305 ,  F05D2240/307 ,  F05D2260/20 ,  Y02T50/676

    Abstract: A gas turbine engine component has an airfoil extending from a platform to a tip at an end of the airfoil spaced from the platform. The airfoil has a suction wall and a pressure wall, with at least one channel extending toward the tip from the platform. A plenum communicates with the at least one channel. The plenum flows from the suction wall toward the pressure wall at the tip to communicate with cooling holes near the pressure wall. The plenum has a reduced cross-sectional area between the suction wall and the pressure wall, and an increase in cross-sectional area downstream of the reduced cross-sectional area. A mold core is also disclosed.

    Abstract translation: 燃气涡轮发动机部件具有从平台延伸到在与平台间隔开的翼型的端部处的尖端的翼型件。 翼型件具有吸力壁和压力壁，至少一个通道从平台向尖端延伸。 一个通风室与至少一个通道通信。 气室从吸力壁流向尖端处的压力壁，以与压力壁附近的冷却孔连通。 增压室在吸力壁和压力壁之间具有减小的横截面积，并且在减小的横截面积的下游的横截面面积增加。 还公开了一种模芯。

    INCIDENT TOLERANT TURBINE VANE COOLING
    16.
    发明公开
    INCIDENT TOLERANT TURBINE VANE COOLING 审中-公开
    BUG容忍涡轮桶冷却

    公开(公告)号：EP3060764A4

    公开(公告)日：2016-12-28

    申请号：EP14855765

    申请日：2014-10-17

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SLAVENS THOMAS N ,  DEVORE MATTHEW A

    IPC: F01D25/12 ,  F01D5/18 ,  F01D9/02

    CPC classification number: F01D9/023 ,  F01D5/18 ,  F01D5/188 ,  F01D9/041 ,  F01D17/162 ,  F01D25/12 ,  F05D2240/121 ,  F05D2260/201

    Abstract: A disclosed turbine vane assembly for a gas turbine engine includes an airfoil including a pressure side and a suction side that extends from a leading edge toward a trailing edge. The airfoil is rotatable about an axis transverse to an engine longitudinal axis and includes a forward chamber within the airfoil and in communication with a cooling air source, a forward impingement baffle defining a pre-impingement cavity within the forward chamber. The pre-impingement cavity is split into a leading edge cavity, pressure side cavity and a suction side cavity defined between an inner surface of the forward chamber and an outer surface of the forward impingement baffle.

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