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    Borescope assembly and method of installing borescope plugs
    2.
    发明授权
    Borescope assembly and method of installing borescope plugs 有权
    内窥镜组件及安装孔镜插头的方法

    公开(公告)号：US09416679B2

    公开(公告)日：2016-08-16

    申请号：US13961257

    申请日：2013-08-07

    申请人： General Electric Company

    发明人： Kenneth Damon Black

    IPC分类号： F02C7/00 ,  F01D21/00 ,  F01D25/00 ,  G02B23/24

    CPC分类号： F01D21/003 ,  F01D25/00 ,  F02C7/00 ,  F05D2250/11 ,  F05D2250/12 ,  F05D2250/121 ,  F05D2250/131 ,  F05D2250/132 ,  F05D2250/23 ,  F05D2250/231 ,  F05D2260/80 ,  G02B23/2476

    摘要： A borescope assembly includes a first borescope plug comprising a first perimeter geometry portion. Also included is a second borescope plug comprising a second perimeter geometry portion distinct from the first perimeter geometry portion. Further included is a first borescope hole comprising a first hole geometry portion corresponding to the first perimeter geometry portion of the first borescope plug. Yet further included is a second borescope hole comprising a second hole geometry portion corresponding to the second perimeter geometry portion of the second borescope plug.

    摘要翻译： 管状窥镜组件包括第一内窥镜插头，其包括第一周边几何部分。 还包括第二内窥镜插塞，其包括与第一周边几何部分不同的第二周边几何部分。 还包括第一管孔孔，其包括对应于第一管孔塞的第一周边几何部分的第一孔几何部分。 还包括第二孔眼孔，其包括对应于第二内窥镜插头的第二周边几何形状部分的第二孔几何部分。

    Use of multi-faceted impingement openings for increasing heat transfer characteristics on gas turbine components
    3.
    发明授权
    Use of multi-faceted impingement openings for increasing heat transfer characteristics on gas turbine components 有权
    使用多面冲击开口来增加燃气轮机部件的传热特性

    公开(公告)号：US09151173B2

    公开(公告)日：2015-10-06

    申请号：US13326372

    申请日：2011-12-15

    申请人： Jaime Javier Maldonado

    发明人： Jaime Javier Maldonado

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

    CPC分类号： F01D9/041 ,  F01D5/189 ,  F01D9/065 ,  F05D2250/131 ,  F05D2260/201 ,  Y02T50/676

    摘要： An improved nozzle vane for a gas turbine engine, comprising a vane wall having inner and outer wall surfaces, the wall surfaces being spaced from one another to define a plurality of fluid passageways for a cooling medium; discreet cavities formed by interior wall members disposed between the inner and outer wall surfaces and within the fluid passageway for the cooling medium; a plurality of impingement cooling sleeves disposed in the discreet cavities defined by the inner and outer wall surfaces and by interior wall members; and a plurality of non-round, e.g., serrated, openings in each of the impingement cooling sleeves, with the openings being sufficient in size and number to accommodate the flow of a cooling media.

    摘要翻译： 一种用于燃气涡轮发动机的改进的喷嘴叶片，包括具有内壁和外壁表面的叶片壁，所述壁表面彼此间隔开以限定用于冷却介质的多个流体通道; 由设置在内壁和外壁之间以及用于冷却介质的流体通道内的内壁构件形成的疏散空腔; 多个冲击冷却套筒，其设置在由内壁和外壁表面以及内壁构件限定的离散空腔中; 以及每个冲击冷却套筒中的多个非圆形例如锯齿形开口，其中开口的尺寸和数量足以适应冷却介质的流动。

    COOLED AIRFOIL TRAILING EDGE AND METHOD OF COOLING THE AIRFOIL TRAILING EDGE
    4.
    发明申请
    COOLED AIRFOIL TRAILING EDGE AND METHOD OF COOLING THE AIRFOIL TRAILING EDGE 有权
    冷却空气涡轮叶片和冷却空气涡轮叶片的方法

    公开(公告)号：US20150147158A1

    公开(公告)日：2015-05-28

    申请号：US14089920

    申请日：2013-11-26

    申请人： General Electric Company

    发明人： Guanghua Wang ,  Ronald Scott Bunker ,  Jeremy Clyde Bailey ,  James Peter DeLancey ,  David Benjamin Helmer

    IPC分类号： F01D5/18 ,  F01D9/02

    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 靠近翼型件的后缘。 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出槽供应。 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。

    BIRD AND DEBRIS DEFLECTOR FOR AIRCRAFT JET ENGINES
    6.
    发明申请
    BIRD AND DEBRIS DEFLECTOR FOR AIRCRAFT JET ENGINES 有权
    飞机喷气发动机的BIRD和DEBRIS偏差器

    公开(公告)号：US20100180566A1

    公开(公告)日：2010-07-22

    申请号：US12689554

    申请日：2010-01-19

    申请人： JEFFREY A. MATOS

    发明人： JEFFREY A. MATOS

    IPC分类号： F02C7/055

    CPC分类号： F02C7/055 ,  B64D33/02 ,  B64D2033/022 ,  F05D2250/131 ,  Y10T137/0536 ,  Y10T137/0645

    摘要： A retractable deflector serves to deflect birds and debris from an air intake duct of an aircraft jet engine. The intake duct has a central longitudinal axis and a forward opening for the receipt of air. The deflector includes a plurality of elongate first support members disposed on the air intake duct in spaced relation to each other and having leading ends which extend from a perimeter of said forward opening. These members are mounted for movement to extend and retract the leading ends. A second support member is coupled to the leading ends of these first support members to retain said leading ends in spaced relation. The second support member is extendible in length and configured to hold the leading ends of the first support members sufficiently close together to cause said first support members to deflect at least one of a bird and debris, when in a first, deployed position, and to allow the leading ends of the first support members to maintain a spaced-apart relation along a line which approximately corresponds to the perimeter of the air duct when in a second, retracted position.

    摘要翻译： 可伸缩偏转器用于使飞机和飞机喷气发动机的进气管道上的鸟类和碎屑偏转。 入口管道具有中心纵向轴线和用于接收空气的前部开口。 偏转器包括多个细长的第一支撑构件，其布置在进气管道上，彼此间隔开并且具有从所述向前开口的周边延伸的前端。 这些构件安装成用于移动以延伸和缩回前端。 第二支撑构件联接到这些第一支撑构件的前端，以保持间隔开的前端。 第二支撑构件的长度可延伸并且构造成将第一支撑构件的前端充分靠近在一起，以使得所述第一支撑构件在处于第一展开位置时使鸟和碎屑中的至少一个偏转，并且 允许第一支撑构件的前端在处于第二缩回位置时沿着大致对应于空气管道的周边的线保持间隔开的关系。

    SHROUD HANGER ASSEMBLY
    10.
    发明申请
    SHROUD HANGER ASSEMBLY 审中-公开

    公开(公告)号：US20170198607A1

    公开(公告)日：2017-07-13

    申请号：US15316577

    申请日：2015-04-23

    申请人： GENERAL ELECTRIC COMPANY

    发明人： Jason David SHAPIRO ,  Jan Christopher SCHILLING ,  Michael John FRANKS

    IPC分类号： F01D25/24 ,  F01D25/12

    CPC分类号： F01D25/246 ,  F01D25/12 ,  F01D25/24 ,  F05D2220/32 ,  F05D2250/131 ,  F05D2300/50212 ,  Y02T50/672

    摘要： A shroud hanger assembly or shroud assembly is provided for dimensionally incompatible components wherein the assembly includes a multi-piece hanger, for example having a forward hanger portion and a rearward hanger portion. A cavity is formed between the parts; wherein a shroud may be positioned which is formed of a low coefficient of thermal expansion material. The hanger and shroud may be formed of the same material or differing materials in order to better match the thermal growth between the hanger and the shroud. When the shroud is positioned within the hanger opening or cavity, one of the forward and rearward hanger portions may be press fit or otherwise connected into the other of the forward and rearward hanger portion.