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    FASTBACK TURBULATOR
    2.
    发明公开
    FASTBACK TURBULATOR 审中-公开
    FastBack的湍流器

    公开(公告)号：EP3149279A1

    公开(公告)日：2017-04-05

    申请号：EP15727287.3

    申请日：2015-05-29

    申请人： General Electric Company

    发明人： BUNKER, Ronald, Scott ,  BRIGGS, Robert, David ,  PEARSON, Shawn, Michael

    IPC分类号： F01D5/14 ,  F01D5/18 ,  F01D25/12 ,  F23R3/00 ,  F28F13/12

    CPC分类号： F01D5/145 ,  F01D5/141 ,  F01D5/187 ,  F01D9/04 ,  F01D25/12 ,  F05D2220/30 ,  F05D2240/127 ,  F05D2260/2212 ,  F23R3/005 ,  F23R2900/03045 ,  Y02T50/673 ,  Y02T50/676

    摘要： A structure for disrupting the flow of a fluid is provided, the structure comprising: a first lateral wall and a second lateral wall spaced apart from one another a distance across an X-axis; and a turbulator extending between the first lateral wall and the second lateral wall, the turbulator extending away from the floor. The turbulator includes a first front surface extending between the first lateral wall and the second lateral wall, a second front surface extending between the first lateral wall and the second lateral wall, a first rear surface extending between the first lateral wall and the second lateral wall, the first rear surface extending between the first front surface and the floor, and a second rear surface adjoining the first rear surface and extending between the first lateral wall and the second lateral wall, the second rear surface extending between the second front surface and the floor.

    摘要翻译： 提供了一种用于破坏流体流动的结构，该结构包括：第一侧壁和第二侧壁，彼此间隔开X轴的距离; 以及在所述第一侧壁和所述第二侧壁之间延伸的湍流器，所述湍流器远离所述地板延伸。 所述湍流器包括在所述第一侧壁和所述第二侧壁之间延伸的第一前表面，在所述第一侧壁和所述第二侧壁之间延伸的第二前表面，在所述第一侧壁和所述第二侧壁之间延伸的第一后表面 ，所述第一后表面在所述第一前表面和所述地板之间延伸，以及邻接所述第一后表面并在所述第一侧壁和所述第二侧壁之间延伸的第二后表面，所述第二后表面在所述第二前表面和所述第二前表面之间延伸， 地板。

    ENGINE COMPONENT ASSEMBLY
    7.
    发明公开
    ENGINE COMPONENT ASSEMBLY 审中-公开
    发动机部件总成

    公开(公告)号：EP3212892A1

    公开(公告)日：2017-09-06

    申请号：EP15791450.8

    申请日：2015-10-27

    申请人： General Electric Company

    发明人： BUNKER, Ronald, Scott ,  RAUSCH, Jonathan, Michael ,  CLARK, Emily, Rosette

    IPC分类号： F01D5/18 ,  F01D9/04 ,  F01D25/12

    CPC分类号： F01D5/187 ,  F01D9/041 ,  F01D9/065 ,  F01D25/12 ,  F05D2220/32 ,  Y02T50/676

    摘要： An engine component assembly includes an engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface in fluid communication with a cooling fluid flow. Multiple, non-linear channels are provided on the cooling surface of the engine component. At least a portion of the cooling fluid flow is orthogonal to an extension axis of the channels.

    摘要翻译： 发动机部件组件包括发动机部件，该发动机部件具有与热燃烧气流热连通的热表面和与冷却流体流动流体连通的冷却表面。 在发动机部件的冷却表面上提供多个非线性通道。 冷却流体流的至少一部分与通道的延伸轴正交。

    COOLED AIRFOIL TRAILING EDGE AND METHOD OF COOLING THE AIRFOIL TRAILING EDGE
    8.
    发明公开
    COOLED AIRFOIL TRAILING EDGE AND METHOD OF COOLING THE AIRFOIL TRAILING EDGE 审中-公开
    GEKÜHLTETRAGFLÄCHENHINTERKANTEUND VERFAHREN ZURKÜHLUNGDERTRAGFLÄCHENHINTERKANTE

    公开(公告)号：EP3074604A2

    公开(公告)日：2016-10-05

    申请号：EP14868713.0

    申请日：2014-11-21

    申请人： General Electric Company

    发明人： WANG, Guanghua ,  BUNKER, Ronald, Scott ,  BAILEY, Jeremy, Clyde ,  DELANCEY, James, Peter ,  HELMER, David, Benjamin

    IPC分类号： F01D5/18 ,  F01D9/04 ,  F01D9/06

    CPC分类号： F01D5/186 ,  F01D5/187 ,  F01D9/041 ,  F01D9/065 ,  F05D2240/304 ,  F05D2250/13 ,  F05D2250/131 ,  F05D2250/14 ,  F05D2250/141 ,  F05D2250/324 ,  F05D2260/2212 ,  Y02T50/673 ,  Y02T50/676

    摘要： An airfoil and method of cooling a airfoil including a leading edge, a trailing edge, a suction side, a pressure side and at least one internal cooling channel configured to convey a cooling fluid, is provided. A plurality of trailing edge bleed slots are in fluid communication with the at least one internal cooling channel, wherein a downstream edge of the pressure side of the airfoil lies upstream of a downstream edge of the suction side to expose the plurality of trailing edge bleed slots proximate to the trailing edge of the airfoil. The at least one internal cooling channel is configured to supply the cooling fluid from a source of cooling fluid towards the plurality of trailing edge bleed slots. A plurality of obstruction features are disposed within the at least one internal cooling channel and at a downstream edge of the remaining pressure side. The one or more obstruction features are configured having a predefined substantially polygon shape, to distribute a flow of the cooling fluid and provide distributed cooling to the plurality of trailing edge bleed slots.

    摘要翻译： 提供了一种用于冷却包括前缘，后缘，吸力侧，压力侧和构造成输送冷却流体的至少一个内部冷却通道的翼型的翼型件和方法。 多个后缘排出槽与至少一个内部冷却通道流体连通，其中翼型的压力侧的下游边缘位于吸力侧的下游边缘的上游，以暴露多个后缘排放槽 靠近翼型的后缘。 至少一个内部冷却通道构造成将冷却流体从冷却流体源向多个后缘排放槽供应。 多个阻塞特征设置在至少一个内部冷却通道内和在剩余压力侧的下游边缘处。 一个或多个障碍物特征被构造成具有预定的基本上多边形的形状，以分配冷却流体的流动并且向多个后缘排放槽提供分布式冷却。