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    Turbine sections of gas turbine engines with dual use of cooling air
    2.
    发明公开
    Turbine sections of gas turbine engines with dual use of cooling air 审中-公开
    Turbinenabschnitte von Gasturbinenmotoren mit Doppelter Verwendung derKühlluft

    公开(公告)号：EP2924238A1

    公开(公告)日：2015-09-30

    申请号：EP15151704.2

    申请日：2015-01-19

    申请人： Honeywell International Inc.

    发明人： Kanjiyani, Shezan ,  Gintert, John ,  Rana, Rajiv ,  Crosatti, Lorenzo ,  Tucker, Bradley Reed ,  Zurmehly, Ed

    IPC分类号： F01D5/18 ,  F01D11/08 ,  F01D25/12 ,  F01D25/14

    CPC分类号： F02C7/18 ,  F01D5/187 ,  F01D11/08 ,  F01D25/12 ,  F01D25/14 ,  F02C3/10 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/205 ,  Y02T50/673 ,  Y02T50/676

    摘要： A turbine section includes a stator assembly having an inner diameter end wall, an outer diameter end wall, and a stator vane; a turbine rotor assembly including a rotor blade extending into the mainstream gas flow path; a housing including an annular shroud that circumscribes the rotor blade and at least partially defines the mainstream hot gas flow path; a first baffle arranged to define a first cavity with the outer diameter end wall of the stator assembly; a second baffle; and a third baffle arranged to define a second cavity with the second baffle and a third cavity with the shroud. The first cavity is fluidly coupled to the second cavity and the second cavity is fluidly coupled to the third cavity such that cooling air flows from the first cavity to the second cavity and from the second cavity to the third cavity.

    摘要翻译： 涡轮部分包括具有内径端壁，外径端壁和定子叶片的定子组件; 包括延伸到主流气流路径中的转子叶片的涡轮转子组件; 壳体，其包括环绕转子叶片并且至少部分地限定主流热气体流动路径的环形护罩; 第一挡板，布置成限定具有定子组件的外径端壁的第一腔; 第二挡板 以及第三挡板，其布置成限定具有第二挡板的第二空腔和具有护罩的第三空腔。 第一空腔流体耦合到第二空腔，第二空腔流体耦合到第三空腔，使得冷却空气从第一空腔流到第二空腔，并从第二空腔流到第三空腔。

    GAS TURBINE ENGINE COMPONENTS HAVING SEALED STRESS RELIEF SLOTS AND METHODS FOR THE FABRICATION THEREOF
    4.
    发明公开
    GAS TURBINE ENGINE COMPONENTS HAVING SEALED STRESS RELIEF SLOTS AND METHODS FOR THE FABRICATION THEREOF 审中-公开
    带密封张力释放槽及其制造方法的燃气涡轮发动机部件

    公开(公告)号：EP2937518A1

    公开(公告)日：2015-10-28

    申请号：EP15154580.3

    申请日：2015-02-10

    申请人： Honeywell International Inc.

    发明人： Smoke, Jason ,  Tucker, Bradley Reed ,  Riahi, Ardeshir ,  Zurmehly, Ed ,  Mirzamoghadam, Alexander

    IPC分类号： F01D9/04 ,  F01D11/00

    CPC分类号： F01D11/005 ,  B22D19/00 ,  B22D25/02 ,  B22D25/06 ,  F01D1/06 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/30 ,  F05D2240/55 ,  F05D2260/20 ,  F05D2260/941

    摘要： Embodiments of a gas turbine engine component (60) having sealed stress relief slots are provided, as are embodiments of a gas turbine engine (20) containing such a component. In one embodiment, the gas turbine engine includes a core gas flow path (92), a secondary cooling flow path (94), and a turbine nozzle or other gas turbine engine component. The component includes, in turn, a component body (62, 64, 66) through which the core gas flow path extends, a radially-extending wall (70) projecting from the component body and into the secondary cooling flow path, and one or more stress relief slots (74) formed in the radially-extending wall. The stress relief slots are filled with a high temperature sealing material (104), which impedes leakage between the second cooling and core gas flow paths and which fractures to alleviate thermomechanical stress within the radially-extending wall during gas turbine engine operation.

    摘要翻译： 具有密封的燃气涡轮发动机组件（60）的实施例，提供应力消除狭槽，作为是含有搜索组件的燃气涡轮发动机（20）的实施例。 在一个中，实施例的燃气涡轮发动机包括核心燃气流动路径（92），二次冷却流路（94），和一个涡轮喷嘴或其它燃气涡轮发动机构件。 所述部件包括，反过来，一个组件体（62，64,66），通过该芯气体流动路径延伸，一个径向延伸的壁（70）从组件主体并进入二次冷却流路投影，以及一个或 在径向延伸的壁形成更多的应力释放槽（74）。 应力消除狭槽填充有第二冷却之间妨碍泄漏和coregas流动路径和骨折燃气涡轮发动机操作期间，径向延伸的壁内，以减轻热机械应力的高温密封材料（104）。

    Turbine nozzle assembly including radially-compliant spring member for gas turbine engine
    6.
    发明公开
    Turbine nozzle assembly including radially-compliant spring member for gas turbine engine 有权
    Turbinenleitschaufelanordnung mit radial-konformer Federfürein Gasturbinentriebwerk

    公开(公告)号：EP2278125A3

    公开(公告)日：2013-03-06

    申请号：EP10162759.4

    申请日：2010-05-12

    申请人： Honeywell International Inc.

    发明人： Smoke, Jason ,  Kujala, Stony ,  Woodcock, Gregory O. ,  Tucker, Bradley Reed

    IPC分类号： F01D11/02 ,  F01D9/04

    CPC分类号： F01D9/02 ,  F01D9/042 ,  F05D2260/38 ,  F05D2260/941

    摘要： Embodiments of a turbine nozzle assembly (58) are provided for deployment within a gas turbine engine (GTE 20) including a first GTE-nozzle mounting interface (101). In one embodiment, the turbine nozzle assembly includes a turbine nozzle flowbody, a first mounting flange (98) configured to be mounted to the first GTE-nozzle mounting interface, and a first radially-compliant spring member (131) coupled between the turbine nozzle flowbody and the first mounting flange (98). The turbine nozzle flowbody has an inner nozzle endwall (92) and an outer nozzle endwall (90), which is fixedly coupled to the inner nozzle endwall (92) and which cooperates therewith to define a flow passage (96) through the turbine nozzle flowbody. The first radially-compliant spring member (131) accommodates relative thermal movement between the turbine nozzle flowbody and the first mounting flange (98) to alleviate thermomechanical stress during operation of the GTE (20).

    摘要翻译： 涡轮喷嘴组件（58）的实施例被提供用于展开在包括第一GTE喷嘴安装界面（101）的燃气涡轮发动机（GTE 20）内。 在一个实施例中，涡轮喷嘴组件包括涡轮喷嘴流动体，构造成安装到第一GTE喷嘴安装界面的第一安装凸缘（98）和联接在涡轮喷嘴之间的第一径向柔性弹簧构件（131） 流体体和第一安装凸缘（98）。 涡轮喷嘴流动体具有内部喷嘴端壁（92）和外部喷嘴端壁（90），其固定地联接到内部喷嘴端壁（92）并与其配合以限定通过涡轮喷嘴流动体的流动通道（96） 。 第一径向顺应弹簧构件（131）容纳在涡轮喷嘴流动体和第一安装凸缘（98）之间的相对热运动，以减轻GTE（20）的运行期间的热机械应力。

    Turbine nozzle assembly including radially-compliant spring member for gas turbine engine
    10.
    发明公开
    Turbine nozzle assembly including radially-compliant spring member for gas turbine engine 有权
    Turbinenleitschaufelanordnung mit radialanpassungsfähigerFederfürein Gasturbinentriebwerk

    公开(公告)号：EP2278125A2

    公开(公告)日：2011-01-26

    申请号：EP10162759.4

    申请日：2010-05-12

    申请人： Honeywell International Inc.

    发明人： Smoke, Jason ,  Kujala, Stony ,  Woodcock, Gregory O. ,  Tucker, Bradley Reed

    IPC分类号： F01D9/02 ,  F01D11/02

    CPC分类号： F01D9/02 ,  F01D9/042 ,  F05D2260/38 ,  F05D2260/941

    摘要： Embodiments of a turbine nozzle assembly (58) are provided for deployment within a gas turbine engine (GTE 20) including a first GTE-nozzle mounting interface (101). In one embodiment, the turbine nozzle assembly includes a turbine nozzle flowbody, a first mounting flange (98) configured to be mounted to the first GTE-nozzle mounting interface, and a first radially-compliant spring member (131) coupled between the turbine nozzle flowbody and the first mounting flange (98). The turbine nozzle flowbody has an inner nozzle endwall (92) and an outer nozzle endwall (90), which is fixedly coupled to the inner nozzle endwall (92) and which cooperates therewith to define a flow passage (96) through the turbine nozzle flowbody. The first radially-compliant spring member (131) accommodates relative thermal movement between the turbine nozzle flowbody and the first mounting flange (98) to alleviate thermomechanical stress during operation of the GTE (20).

    摘要翻译： 涡轮喷嘴组件（58）的实施例被提供用于展开在包括第一GTE喷嘴安装界面（101）的燃气涡轮发动机（GTE 20）内。 在一个实施例中，涡轮喷嘴组件包括涡轮喷嘴流动体，构造成安装到第一GTE喷嘴安装界面的第一安装凸缘（98）和联接在涡轮喷嘴之间的第一径向柔性弹簧构件（131） 流体体和第一安装凸缘（98）。 涡轮喷嘴流动体具有内部喷嘴端壁（92）和外部喷嘴端壁（90），其固定地联接到内部喷嘴端壁（92）并与其配合以限定通过涡轮喷嘴流动体的流动通道（96） 。 第一径向顺应弹簧构件（131）容纳在涡轮喷嘴流动体和第一安装凸缘（98）之间的相对热运动，以减轻GTE（20）的运行期间的热机械应力。