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    LOW-DUCTILITY TURBINE SHROUD
    4.
    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。

    MOUNTING APPARATUS FOR LOW-DUCTILITY TURBINE SHROUD
    6.
    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。

    Method and system for supporting stator components
    7.
    发明授权
    Method and system for supporting stator components 有权
    支撑定子部件的方法和系统

    公开(公告)号：US08172522B2

    公开(公告)日：2012-05-08

    申请号：US12058980

    申请日：2008-03-31

    申请人： Jason David Shapiro ,  Victor Hugo Silva Correia

    发明人： Jason David Shapiro ,  Victor Hugo Silva Correia

    IPC分类号： F01D25/28

    CPC分类号： F01D9/042 ,  F01D25/246 ,  F04D29/526 ,  F04D29/644 ,  F05D2260/94 ,  F05D2260/941

    摘要： A method and system of supporting removable static components in a turbine engine stator assembly is described. The method comprises the steps of engaging a stator hanger located at a first location on a first static component with a post located on a first static structure whereby the post supports at least a part of the weight of the first static component, engaging a stator stopper located at a second location on the first static component that is located circumferentially apart from the first location with the stator hanger that is located on a second static component, and engaging a hook located at a third location on the first static component with a second static structure whereby the second static structure supports at least a part of the weight of the first static component.

    摘要翻译： 描述了一种在涡轮发动机定子组件中支撑可移除静态部件的方法和系统。 该方法包括以下步骤：将位于第一静态部件上的第一位置的定子吊架与位于第一静态结构上的柱接合，由此支柱支撑第一静态部件的重量的至少一部分， 位于所述第一静态部件上的第二位置，所述第二静止部件位于与所述第一位置周向隔开的位置处，所述第二静止部件位于所述第二静止部件上的所述定子衣架上，并且使位于所述第一静止部件上的第三位置的钩与第二静止部件 结构，由此第二静态结构支撑第一静态部件的重量的至少一部分。

    TURBINE STATOR MOUNT
    8.
    发明申请
    TURBINE STATOR MOUNT 有权
    涡轮定子装置

    公开(公告)号：US20090246012A1

    公开(公告)日：2009-10-01

    申请号：US12058972

    申请日：2008-03-31

    申请人： Jason David Shapiro ,  Victor Hugo Silva Correia

    发明人： Jason David Shapiro ,  Victor Hugo Silva Correia

    IPC分类号： F01D9/02 ,  F04D29/54

    CPC分类号： F01D9/042

    摘要： A reaction mount system that provides support for the stator vane for a gas turbine engine is described comprising a stator hanger located on an outer band at a first location and a stator stopper located at a second location that is located circumferentially apart from the first location. A stator assembly for a gas turbine engine is described, the stator assembly comprising a stator vane having an airfoil, an outer band located on a radially outer end of the airfoil, a shroud hanger located axially adjacent to the outer band, the shroud hanger comprising a post wherein at least a portion of the post extends in an axial direction over a portion of the outer band, and a reaction mount system located on the outer band wherein the reaction mount system engages with the post to provide support for the stator vane.

    摘要翻译： 描述了提供对用于燃气涡轮发动机的定子叶片的支撑的反应安装系统，其包括位于第一位置处的外带上的定子悬挂器和位于与第一位置周向隔开的第二位置的定子止动器。 描述了一种用于燃气涡轮发动机的定子组件，该定子组件包括具有翼型的定子叶片，位于翼型件的径向外端的外带，位于轴向邻近外带的护罩，衣架悬挂器包括 柱，其中所述柱的至少一部分在所述外带的一部分上沿轴向方向延伸;以及反应安装系统，位于所述外带上，其中所述反作用安装系统与所述柱接合以为所述定子叶片提供支撑。

    Turbine shroud assembly and method for assembling a gas turbine engine
    9.
    发明授权
    Turbine shroud assembly and method for assembling a gas turbine engine 有权
    涡轮罩组件及组装燃气轮机的方法

    公开(公告)号：US07377742B2

    公开(公告)日：2008-05-27

    申请号：US11250660

    申请日：2005-10-14

    申请人： Jason David Shapiro ,  Daniel Demers ,  Robert Patrick Tameo ,  Tyler F. Hooper ,  Robert Alexander Nicoll ,  Douglas Patrick Probasco

    发明人： Jason David Shapiro ,  Daniel Demers ,  Robert Patrick Tameo ,  Tyler F. Hooper ,  Robert Alexander Nicoll ,  Douglas Patrick Probasco

    IPC分类号： F01D25/26

    CPC分类号： F01D11/24 ,  F01D11/08 ,  F05D2230/90 ,  F05D2240/11 ,  F05D2300/611

    摘要： A method for assembling a gas turbine engine includes coupling a rotor assembly including a plurality of rotor blades about a rotatable main shaft of the gas turbine engine. The main shaft is aligned in an axial direction of the gas turbine engine. A shroud assembly is coupled to the gas turbine engine. The shroud assembly includes a plurality of shroud segments circumferentially coupled about the rotor assembly such that a shroud spacing gap is formed in the axial direction between adjacent shroud segments. A cooling fluid source is coupled to each shroud segment such that cooling fluid is channeled through each shroud segment into a corresponding shroud spacing gap to facilitate positive purge flow through the shroud spacing gap.

    摘要翻译： 一种用于组装燃气涡轮发动机的方法包括将包括多个转子叶片的转子组件围绕燃气涡轮发动机的可旋转主轴联接。 主轴沿燃气轮机的轴向对准。 护罩组件联接到燃气涡轮发动机。 护罩组件包括围绕转子组件周向耦合的多个护罩段，使得在相邻护罩段之间沿轴向方向形成护罩间隔间隙。 冷却流体源联接到每个护罩段，使得冷却流体通过每个护罩段引导成相应的护罩间隔间隙，以促进穿过护罩间隔间隙的正净化流动。

    Shroud hanger with diffused cooling passage
    10.
    发明授权
    Shroud hanger with diffused cooling passage 有权
    带有扩散冷却通道的衣架

    公开(公告)号：US08123473B2

    公开(公告)日：2012-02-28

    申请号：US12262606

    申请日：2008-10-31

    申请人： Jason David Shapiro

    发明人： Jason David Shapiro

    IPC分类号： F01D25/12 ,  F01D11/08

    CPC分类号： F01D25/246 ,  F01D11/08 ,  F01D25/14 ,  F05D2260/205 ,  Y10T29/49323

    摘要： A shroud hanger for a gas turbine engine has an arcuate body with opposed inner and outer faces and opposed forward and aft ends, the channel having at least one cooling passage therein which includes: (a) a generally axially-aligned channel extending through the body, the channel having one end open to an exterior of the body; and (b) a generally radially-aligned diffuser extending through the inner face and intersecting the channel.

    摘要翻译： 用于燃气涡轮发动机的护罩悬挂器具有弓形体，其具有相对的内表面和外表面以及相对的前端和后端，所述通道在其中具有至少一个冷却通道，其包括：（a）延伸穿过本体的大致轴向对齐的通道 ，所述通道的一端向所述主体的外部敞开; 和（b）通过径向对齐的扩散器延伸穿过内表面并与通道相交。