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    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

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

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

    IPC: F04D29/40

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

    Abstract: 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.

    Abstract translation: 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。

    MULTI-SOURCE GAS TURBINE COOLING
    3.
    发明申请
    MULTI-SOURCE GAS TURBINE COOLING 有权
    多源气体涡轮冷却

    公开(公告)号：US20100281879A1

    公开(公告)日：2010-11-11

    申请号：US11965402

    申请日：2007-12-27

    Applicant: Jason David Shapiro ,  David Allen Flodman ,  Samuel Ross Rulli ,  Samir Dimitri Sayegh ,  Norman Clement Brackett

    Inventor： Jason David Shapiro ,  David Allen Flodman ,  Samuel Ross Rulli ,  Samir Dimitri Sayegh ,  Norman Clement Brackett

    IPC: F02C7/18 ,  F02C6/08

    CPC classification number: F02C7/18 ,  F01D5/08 ,  F01D9/041 ,  F01D9/06 ,  F01D11/001 ,  F01D11/08 ,  F01D25/12 ,  F01D25/246 ,  F05D2220/3213 ,  F05D2240/11 ,  F05D2260/201 ,  Y02T50/676

    Abstract: A cooling arrangement for a gas turbine engine includes: (a) a turbine nozzle having: (i) spaced-apart arcuate inner and outer bands; and (ii) a hollow, airfoil-shaped turbine vane extending between the inner and outer bands, the vane disposed in a primary flowpath of the engine; (b) a supporting structure coupled to the outer band such that an outer band cavity is defined between the outer band and the stationary structure; (c) a first conduit passing through the outer band cavity and communicating with the interior of the vane, the first conduit coupled to a first source of cooling air within the engine; and (d) a second conduit communicating with the outer band cavity, the second conduit coupled to a second source of cooling air within the engine.

    Abstract translation: 用于燃气涡轮发动机的冷却装置包括：（a）涡轮喷嘴，其具有：（i）间隔开的弓形内部和外部带; 和（ii）在所述内带和外带之间延伸的中空翼型涡轮叶片，所述叶片设置在所述发动机的主流路中; （b）耦合到所述外带的支撑结构，使得在所述外带和所述固定结构之间限定外带空腔; （c）通过所述外带空腔并与所述叶片内部连通的第一管道，所述第一管道联接到所述发动机内的第一冷却空气源; 和（d）与外带空腔连通的第二导管，第二导管连接到发动机内的第二冷却空气源。

    Multi-source gas turbine cooling
    5.
    发明授权
    Multi-source gas turbine cooling 有权
    多源燃气轮机冷却

    公开(公告)号：US07946801B2

    公开(公告)日：2011-05-24

    申请号：US11965402

    申请日：2007-12-27

    Applicant: Jason David Shapiro ,  David Allen Flodman ,  Samuel Ross Rulli ,  Samir Dimitri Sayegh ,  Norman Clement Brackett

    Inventor： Jason David Shapiro ,  David Allen Flodman ,  Samuel Ross Rulli ,  Samir Dimitri Sayegh ,  Norman Clement Brackett

    IPC: F01D5/08

    CPC classification number: F02C7/18 ,  F01D5/08 ,  F01D9/041 ,  F01D9/06 ,  F01D11/001 ,  F01D11/08 ,  F01D25/12 ,  F01D25/246 ,  F05D2220/3213 ,  F05D2240/11 ,  F05D2260/201 ,  Y02T50/676

    Abstract: A cooling arrangement for a gas turbine engine includes: (a) a turbine nozzle having: (i) spaced-apart arcuate inner and outer bands; and (ii) a hollow, airfoil-shaped turbine vane extending between the inner and outer bands, the vane disposed in a primary flowpath of the engine; (b) a supporting structure coupled to the outer band such that an outer band cavity is defined between the outer band and the stationary structure; (c) a first conduit passing through the outer band cavity and communicating with the interior of the vane, the first conduit coupled to a first source of cooling air within the engine; and (d) a second conduit communicating with the outer band cavity, the second conduit coupled to a second source of cooling air within the engine.

    Abstract translation: 用于燃气涡轮发动机的冷却装置包括：（a）涡轮喷嘴，其具有：（i）间隔开的弓形内部和外部带; 和（ii）在所述内带和外带之间延伸的中空翼型涡轮叶片，所述叶片设置在所述发动机的主流路中; （b）耦合到所述外带的支撑结构，使得在所述外带和所述固定结构之间限定外带空腔; （c）通过所述外带空腔并与所述叶片内部连通的第一管道，所述第一管道联接到所述发动机内的第一冷却空气源; 和（d）与外带空腔连通的第二导管，第二导管连接到发动机内的第二冷却空气源。

    LOW-DUCTILITY TURBINE SHROUD
    6.
    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

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

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

    IPC: F04D29/42

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

    Abstract: 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.

    Abstract translation: 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。

    TURBINE SHROUD SUPPORT THERMAL SHIELD
    7.
    发明申请
    TURBINE SHROUD SUPPORT THERMAL SHIELD 审中-公开
    涡轮SHROUD支持热风罩

    公开(公告)号：US20110206502A1

    公开(公告)日：2011-08-25

    申请号：US12712639

    申请日：2010-02-25

    Applicant: Samuel Ross Rulli ,  Charles Mendes ,  John Alan Manteiga

    Inventor： Samuel Ross Rulli ,  Charles Mendes ,  John Alan Manteiga

    IPC: F02C7/12

    CPC classification number: F01D25/145 ,  F01D11/24 ,  F01D25/246 ,  F05D2250/283 ,  Y02T50/671 ,  Y02T50/675 ,  Y02T50/6765

    Abstract: A turbine shroud assembly includes an annular thermal shield around an annular shroud support. A honeycomb layer is attached to the shroud support along an inner side of the honeycomb layer and a heat shield is attached to an outer side of the honeycomb layer. The honeycomb layer may be brazed to the shroud support and the heat shield may be brazed to the honeycomb layer. A lip may depend inwardly from a forward end of the heat shield and an axial extension may extend beyond an aft end of the honeycomb layer. The thermal shield may be segmented. The shroud assembly may include axially spaced apart first and second stage thermal shields circumferentially disposed around an annular shroud support and may be incorporated in a high pressure turbine including first and second stage shrouds coupled to shroud hangers that are inwardly supported by hooks of the shroud support.

    Abstract translation: 涡轮机护罩组件包括围绕环形护罩支撑件的环形热屏蔽。 蜂巢层沿着蜂窝层的内侧安装在护罩支撑体上，在蜂窝层的外侧附着有隔热罩。 蜂窝层可以钎焊到护罩支撑件上，并且热屏蔽件可以钎焊到蜂窝层。 唇缘可以从隔热罩的前端向内取向，并且轴向延伸部可以延伸超过蜂窝层的后端。 热屏蔽可以被分段。 护罩组件可以包括轴向间隔开的第一和第二级热屏蔽件，周向设置在环形护罩支撑件周围，并且可以并入高压涡轮机中，该高压涡轮机包括联接到护罩悬挂器的第一和第二级护罩，该护罩悬挂器由护罩支撑件 。

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