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    End rail cooling for combined high and low pressure turbine shroud
    1.
    发明授权
    End rail cooling for combined high and low pressure turbine shroud 有权
    用于组合的高低压涡轮机护罩的末端导轨冷却

    公开(公告)号：US06340285B1

    公开(公告)日：2002-01-22

    申请号：US09590590

    申请日：2000-06-08

    申请人： Craig Alan Gonyou ,  Roger Lee Doughty ,  Monty Lee Shelton

    发明人： Craig Alan Gonyou ,  Roger Lee Doughty ,  Monty Lee Shelton

    IPC分类号： F04D3100

    CPC分类号： F01D11/005 ,  F01D25/246 ,  F02C7/28 ,  F05D2240/11 ,  F05D2260/20 ,  F05D2260/202

    摘要： A segmented turbine cooling component, such as shroud segment for the high pressure and low pressure turbine sections of a gas turbine engine, useful in providing preferential cooling to the side rails or panels of the turbine component through the combination of cooling air fed into the intermediate pressure cavity between the discourager and primary seals and then through recesses in the bottom wall of the lower discourager seal slot that impinges air on the portion of the side panel below the discourager seal. The side panels of the turbine component have an upper primary seal slot and a lower discourager seal slot with a bottom wall having a plurality of alternating lands and recesses along the length thereof and a plurality of cooling air passages having outlets exiting into the lower slot above the lands. The subassembly can be formed from a plurality of such turbine components where the spacing of the lands and recesses of the lower discourager slots of the adjacent side panels are staggered such that the lands of the lower slot of one adjacent panel are opposite the recesses of the lower slot of the other adjacent side panel. This subassembly also has primary and discourager seals received by the respective upper and lower slots that are positioned in the gap between the adjacent panels which define the intermediate pressure cavity therebetween and trench below the discourager seal that is purged by spent cooling air from the recesses in the lower slot.

    摘要翻译： 分段涡轮机冷却部件，例如用于燃气涡轮发动机的高压和低压涡轮机部分的护罩段，其可用于通过组合供应到中间体中的冷却空气向涡轮机部件的侧轨或侧板提供优先冷却 沮丧者和初级密封件之间的压力空腔，然后通过下部砸痕器密封槽的底壁中的凹槽，其将空气撞击在挡板密封件下方的侧板部分。 涡轮机部件的侧板具有上主要密封槽和下部盘片密封槽，其底壁具有沿着其长度的多个交替的平台和凹部，以及多个冷却空气通道，其具有出口到上述下槽中 土地 子组件可以由多个这样的涡轮机部件形成，其中相邻侧板的下部罢工槽的平台和凹槽的间隔交错，使得一个相邻面板的下槽的平台与 另一个相邻侧面板的下槽。 该子组件还具有由相应的上部和下部狭槽接收的主要和沮丧的密封件，该密封件定位在相邻面板之间的间隙中，在相邻面板之间的间隙中限定了中间压力空腔，并且在捣实器密封件下方的沟槽被消耗的冷却空气从凹部 下槽。

    MOUNTING APPARATUS FOR LOW-DUCTILITY TURBINE SHROUD
    2.
    发明申请
    MOUNTING APPARATUS FOR LOW-DUCTILITY TURBINE SHROUD 有权
    低密度涡轮机安装装置

    公开(公告)号：US20130156550A1

    公开(公告)日：2013-06-20

    申请号：US13327349

    申请日：2011-12-15

    申请人： Michael John Franks ,  Jason David Shapiro ,  Samuel Ross Rulli ,  Roger Lee Doughty

    发明人： Michael John Franks ,  Jason David Shapiro ,  Samuel Ross Rulli ,  Roger Lee Doughty

    IPC分类号： F04D29/40

    CPC分类号： F01D25/246 ,  F01D5/284 ,  F01D11/08 ,  F01D11/12 ,  F01D11/24 ,  F05D2240/11 ,  F05D2250/41 ,  F05D2260/38 ,  Y02T50/672

    摘要： A shroud apparatus for a gas turbine engine includes: an annular metallic hanger; a shroud segment disposed inboard of the hanger, comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface; and a retainer mechanically coupled to the hanger which engages the shroud segment to retain the shroud segment to the hanger while permitting movement of the shroud segment in a radial direction.

    摘要翻译： 用于燃气涡轮发动机的护罩装置包括：环形金属吊架; 设置在所述衣架内的护罩区段，包括低延展性材料并且具有由相对的前壁和后壁限定的横截面形状，以及相对的内壁和外壁，所述壁在相对的第一和第二端面之间延伸， 壁定义了弧形内流道表面; 以及保持器，其机械地联接到所述衣架，其接合所述护罩区段，以将所述护罩区段保持在所述衣架上，同时允许所述护罩区段在径向方向上移动。

    LOW-DUCTILITY TURBINE SHROUD
    7.
    发明申请
    LOW-DUCTILITY TURBINE SHROUD 有权
    低密度涡轮SHROUD

    公开(公告)号：US20130156556A1

    公开(公告)日：2013-06-20

    申请号：US13402616

    申请日：2012-02-22

    申请人： Michael John Franks ,  Jason David Shapiro ,  Samuel Ross Rulli ,  Roger Lee Doughty ,  Joshua Brian Jamison

    发明人： Michael John Franks ,  Jason David Shapiro ,  Samuel Ross Rulli ,  Roger Lee Doughty ,  Joshua Brian Jamison

    IPC分类号： F04D29/42

    CPC分类号： F01D25/246 ,  F01D5/284 ,  F01D11/08 ,  F01D11/24 ,  F05D2240/11 ,  F05D2250/41 ,  F05D2250/61 ,  F05D2250/712 ,  F05D2260/38 ,  F05D2300/6033

    摘要： A shroud segment for a gas turbine engine, the shroud segment constructed from a composite material including reinforcing fibers embedded in a matrix, and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface; and wherein a compound fillet is disposed at a junction between first and second ones of the walls, the compound fillet including first and second portions, the second portion having a concave curvature extending into the first one of the walls.

    摘要翻译： 一种用于燃气涡轮发动机的护罩段，所述护罩段由复合材料构成，所述复合材料包括嵌入基质中的增强纤维，并且具有由相对的前壁和后壁限定的横截面形状，以及相对的内壁和外壁，所述壁延伸 在相对的第一和第二端面之间，其中所述内壁限定弓形的内部流路表面; 并且其中复合圆角设置在第一和第二壁之间的接合处，所述复合圆角包括第一和第二部分，所述第二部分具有延伸到所述第一壁中的凹曲率。