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    Compliant coupling systems and methods for shrouds
    1.
    发明授权
    Compliant coupling systems and methods for shrouds 有权

    公开(公告)号：US10030542B2

    公开(公告)日：2018-07-24

    申请号：US14873853

    申请日：2015-10-02

    申请人： HONEYWELL INTERNATIONAL INC.

    发明人： Ed Zurmehly ,  David R. Waldman ,  Deanna Pinar Chase ,  David K Jan ,  Gregory Ockenfels ,  Alonso Peralta-Duran

    IPC分类号： F01D25/24 ,  F01D9/02 ,  F01D11/00

    摘要： Compliant coupling systems and methods are provided for coupling a shroud to an engine casing. The complaint coupling system includes a retaining ring adapted to be positioned adjacent to the shroud and adapted to be coupled to the engine casing. The retaining ring defines a coupling channel about a circumference of the retaining ring and at least one notch that interrupts the coupling channel. The complaint coupling system also includes a first clip received within the coupling channel. The first clip has a biasing portion that extends into a space defined by the at least one notch, and the biasing portion is adapted to contact the shroud. The complaint coupling system includes a second clip received within the coupling channel. The second clip has a bumper portion that extends into the spaced defined by the at least one notch, and the bumper portion is adapted to contact the shroud.

    TURBINE SECTIONS OF GAS TURBINE ENGINES WITH DUAL USE OF COOLING AIR
    3.
    发明申请
    TURBINE SECTIONS OF GAS TURBINE ENGINES WITH DUAL USE OF COOLING AIR 有权
    具有双重冷却空气使用的涡轮发动机涡轮段

    公开(公告)号：US20150275763A1

    公开(公告)日：2015-10-01

    申请号：US14227924

    申请日：2014-03-27

    申请人： HONEYWELL INTERNATIONAL INC.

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

    IPC分类号： F02C7/18 ,  F02C3/10

    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; 涡轮转子组件，其包括延伸到主流气流路径中的转子叶片; 壳体，其包括环绕所述转子叶片并且至少部分地限定所述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。 第一腔体流体地联接到第二腔体，而第二腔室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，并从第二腔体流到第三空腔。

    GAS TURBINE ENGINE COMPONENTS HAVING SEALED STRESS RELIEF SLOTS AND METHODS FOR THE FABRICATION THEREOF
    5.
    发明申请
    GAS TURBINE ENGINE COMPONENTS HAVING SEALED STRESS RELIEF SLOTS AND METHODS FOR THE FABRICATION THEREOF 有权
    具有密封应力消除槽的气体涡轮发动机部件及其制造方法

    公开(公告)号：US20150300192A1

    公开(公告)日：2015-10-22

    申请号：US14257485

    申请日：2014-04-21

    申请人： HONEYWELL INTERNATIONAL INC.

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

    IPC分类号： F01D11/00 ,  F01D9/04 ,  B22D19/00 ,  B22D25/02 ,  B22D25/06 ,  F01D1/06 ,  F01D25/12

    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 having sealed stress relief slots are provided, as are embodiments of a gas turbine engine containing such a component and embodiments of a method for fabricating such a component. In one embodiment, the gas turbine engine includes a core gas flow path, a secondary cooling flow path, and a turbine nozzle or other gas turbine engine component. The component includes, in turn, a component body through which the core gas flow path extends, a radially-extending wall projecting from the component body and into the secondary cooling flow path, and one or more stress relief slots formed in the radially-extending wall. The stress relief slots are filled with a high temperature sealing material, 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 operation of the gas turbine engine.

    摘要翻译： 提供了具有密封的应力消除槽的燃气涡轮发动机部件的实施例，其中包括含有这种部件的燃气涡轮发动机和用于制造这种部件的方法的实施例的实施例。 在一个实施例中，燃气涡轮发动机包括核心气体流动路径，二次冷却流动路径，以及涡轮喷嘴或其它燃气涡轮发动机部件。 该组件又包括核心气体流路延伸穿过的组件主体，从组件主体突出并进入二次冷却流动路径的径向延伸的壁，以及一个或多个形成在径向延伸的应力释放槽 壁。 应力释放槽填充有高温密封材料，其阻止第二冷却和核心气体流动路径之间的泄漏，并且其在燃气涡轮发动机的操作期间破裂以减轻径向延伸的壁内的热机械应力。

    THERMAL ISOLATING SERVICE TUBES AND ASSEMBLIES THEREOF FOR GAS TURBINE ENGINES
    7.
    发明申请
    THERMAL ISOLATING SERVICE TUBES AND ASSEMBLIES THEREOF FOR GAS TURBINE ENGINES 有权
    用于气体涡轮发动机的热隔离管及其组件

    公开(公告)号：US20150052872A1

    公开(公告)日：2015-02-26

    申请号：US13971671

    申请日：2013-08-20

    申请人： HONEYWELL INTERNATIONAL INC.

    发明人： Ed Zurmehly ,  Cristopher Frost ,  Michael O'Brien ,  Donald G Godfrey

    IPC分类号： F01D25/12 ,  F01D25/18

    CPC分类号： F01D25/125 ,  F01D9/065 ,  F01D25/145 ,  F01D25/18 ,  F01D25/26

    摘要： Thermal isolating service tubes and assemblies thereof for gas turbine engines are provided. The thermal isolating service tube comprises an inner tubular member defining a fluid passage and at least one outer tubular member disposed about the inner tubular member. A spacing volume is defined between at least the inner tubular member and an adjacent outer tubular member. The thermal isolating service tube comprises a unitary structure and has at least one portion with a curved configuration, a non-circular cross-sectional shape, or both.

    摘要翻译： 提供了用于燃气涡轮发动机的隔热管件及其组件。 隔热管件包括限定流体通道的内部管状构件和围绕内部管状构件设置的至少一个外部管状构件。 在至少内部管状构件和相邻的外部管状构件之间限定间隔体积。 隔热保护管包括整体结构，并且具有至少一部分具有弯曲构型，非圆形横截面形状或两者。

    Gas turbine engine components having sealed stress relief slots and methods for the fabrication thereof
    10.
    发明授权
    Gas turbine engine components having sealed stress relief slots and methods for the fabrication thereof 有权
    具有密封应力消除槽的燃气涡轮发动机部件及其制造方法

    公开(公告)号：US09506365B2

    公开(公告)日：2016-11-29

    申请号：US14257485

    申请日：2014-04-21

    申请人： HONEYWELL INTERNATIONAL INC.

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

    IPC分类号： F01D11/00 ,  B23D19/00 ,  F01D1/06 ,  F01D9/04 ,  F01D25/12 ,  B22D25/02 ,  B22D25/06 ,  B22D19/00

    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 having sealed stress relief slots are provided, as are embodiments of a gas turbine engine containing such a component and embodiments of a method for fabricating such a component. In one embodiment, the gas turbine engine includes a core gas flow path, a secondary cooling flow path, and a turbine nozzle or other gas turbine engine component. The component includes, in turn, a component body through which the core gas flow path extends, a radially-extending wall projecting from the component body and into the secondary cooling flow path, and one or more stress relief slots formed in the radially-extending wall. The stress relief slots are filled with a high temperature sealing material, 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 operation of the gas turbine engine.

    摘要翻译： 提供了具有密封的应力消除槽的燃气涡轮发动机部件的实施例，其中包括含有这种部件的燃气涡轮发动机和用于制造这种部件的方法的实施例的实施例。 在一个实施例中，燃气涡轮发动机包括核心气体流动路径，二次冷却流动路径，以及涡轮喷嘴或其它燃气涡轮发动机部件。 该组件又包括核心气体流路延伸穿过的组件主体，从组件主体突出并进入二次冷却流动路径的径向延伸的壁，以及一个或多个形成在径向延伸的应力释放槽 壁。 应力释放槽填充有高温密封材料，其阻止第二冷却和核心气体流动路径之间的泄漏，并且其在燃气涡轮发动机的操作期间破裂以减轻径向延伸的壁内的热机械应力。