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    Gas turbine engine airfoil cooling passage configuration
    124.
    发明授权
    Gas turbine engine airfoil cooling passage configuration 有权

    公开(公告)号：US09803500B2

    公开(公告)日：2017-10-31

    申请号：US14696627

    申请日：2015-04-27

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  San Quach

    IPC: F01D5/18 ,  F01D25/12

    CPC classification number: F01D25/12 ,  F01D5/187 ,  F05D2220/32 ,  F05D2260/22141 ,  Y02T50/676

    Abstract: An airfoil for a gas turbine engine includes an airfoil body that extends in a radial direction from a support. The airfoil body has pressure and suction side walls joined at leading and trailing edges to provide an exterior airfoil surface. A chord-wise direction extends between the leading and trailing edges and a thickness direction transverse to chord-wise direction and extending between the pressure and suction side walls. Cooling passages extend from the support into the airfoil body. The cooling passages include adjacent passageways in the thickness direction and are separated by a chord-wise wall. One of the adjacent passageways is adjacent to another passageway in the chord-wise direction and is separated by a rib in the thickness direction. The rib is discontinued at a location along the radial direction to provide an opening that fluidly connects one of the adjacent passageways to the other passageway.

    INTERNAL COOLING CAVITY WITH TRIP STRIPS
    127.
    发明申请
    INTERNAL COOLING CAVITY WITH TRIP STRIPS 审中-公开
    内部冷却空气带

    公开(公告)号：US20160208619A1

    公开(公告)日：2016-07-21

    申请号：US14602035

    申请日：2015-01-21

    Applicant: United Technologies Corporation

    Inventor： San Quach ,  Atul Kohli ,  Matthew A. Devore ,  Steven Bruce Gautschi

    IPC: F01D5/18

    Abstract: An airfoil is provided. The airfoil may comprise a cross over, an impingement chamber in fluid communication with the cross over, and a first trip strip disposed on a first surface of the impingement chamber. A cooling system is also provided. The cooling system may comprise an impingement chamber, a first trip strip on a first surface of the impingement chamber, and a second trip strip on a second surface of the impingement chamber. An internally cooled engine part is further provided. The internally cooled part may comprise a cross over and an impingement chamber in fluid communication with the cross over. The cross over may be configured to direct air towards a first surface of the impingement chamber. A first trip strip may be disposed on the first surface of the impingement chamber.

    Abstract translation: 提供翼型。 所述翼型件可以包括十字交叉，与所述十字架流体连通的冲击室以及设置在所述冲击室的第一表面上的第一跳闸条。 还提供冷却系统。 冷却系统可以包括冲击室，冲击室的第一表面上的第一跳闸条和在冲击室的第二表面上的第二跳闸条。 还提供内部冷却的发动机部件。 内部冷却部分可以包括与交叉流体连通的交叉和冲击室。 十字架可以构造成将空气引向冲击室的第一表面。 第一跳闸条可以设置在冲击室的第一表面上。

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