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    GAS TURBINE ENGINE COMPONENTS HAVING SEALED STRESS RELIEF SLOTS AND METHODS FOR THE FABRICATION THEREOF
    1.
    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

    Applicant: HONEYWELL INTERNATIONAL INC.

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

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

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

    Abstract: 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.

    Abstract translation: 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。

    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

    Applicant: HONEYWELL INTERNATIONAL INC.

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

    IPC: F02C7/18 ,  F02C3/10

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

    Abstract: 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.

    Abstract translation: 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。

    TURBINE NOZZLES AND METHODS OF MANUFACTURING THE SAME
    4.
    发明申请
    TURBINE NOZZLES AND METHODS OF MANUFACTURING THE SAME 有权
    涡轮喷嘴及其制造方法

    公开(公告)号：US20140321965A1

    公开(公告)日：2014-10-30

    申请号：US13869085

    申请日：2013-04-24

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Rajiv Rana ,  Ardeshir Riahi ,  Bradley Reed Tucker ,  David Chou

    IPC: F01D9/02

    CPC classification number: F01D9/065 ,  F01D5/187 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/676

    Abstract: A turbine nozzle assembly includes an inner circumferential support platform, an outer circumferential support platform, and a plurality of airfoil vanes disposed between the inner circumferential support platform and the outer circumferential support platform. The turbine nozzle assembly further includes a plurality of impingement plates disposed along a radially outer surface of the outer circumferential support platform or a radially inner surface of the inner circumferential support platform, and a plurality of gap-maintaining features disposed between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates. Each gap-maintaining feature of the plurality of gap-maintaining features is provided at a height such that a cooling air flow space is maintained between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates.

    Abstract translation: 涡轮喷嘴组件包括内周支撑平台，外周支撑平台以及设置在内圆周支撑平台和外圆周支撑平台之间的多个翼型叶片。 涡轮喷嘴组件还包括沿着外周支撑平台的径向外表面或内周支撑平台的径向内表面设置的多个冲击板，以及多个间隙保持特征，其设置在多个外周或 内圆周支撑平台和多个冲击板。 多个间隙保持特征的每个间隙保持特征都设置在使多个外周或内周支撑平台与多个冲击板之间保持冷却空气流动空间的高度。

    Turbine nozzles and methods of manufacturing the same
    6.
    发明授权
    Turbine nozzles and methods of manufacturing the same 有权

    公开(公告)号：US09719362B2

    公开(公告)日：2017-08-01

    申请号：US13869085

    申请日：2013-04-24

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Rajiv Rana ,  Ardeshir Riahi ,  Bradley Reed Tucker ,  David Chou

    IPC: F01D5/14 ,  F01D9/06 ,  F01D5/18

    CPC classification number: F01D9/065 ,  F01D5/187 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/676

    Abstract: A turbine nozzle assembly includes an inner circumferential support platform, an outer circumferential support platform, and a plurality of airfoil vanes disposed between the inner circumferential support platform and the outer circumferential support platform. The turbine nozzle assembly further includes a plurality of impingement plates disposed along a radially outer surface of the outer circumferential support platform or a radially inner surface of the inner circumferential support platform, and a plurality of gap-maintaining features disposed between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates. Each gap-maintaining feature of the plurality of gap-maintaining features is provided at a height such that a cooling air flow space is maintained between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates.

    Gas turbine engine components having sealed stress relief slots and methods for the fabrication thereof
    8.
    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

    Applicant: HONEYWELL INTERNATIONAL INC.

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

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

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

    Abstract: 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.

    Abstract translation: 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。

    TURBINE NOZZLES AND COOLING SYSTEMS FOR COOLING SLIP JOINTS THEREIN
    10.
    发明申请
    TURBINE NOZZLES AND COOLING SYSTEMS FOR COOLING SLIP JOINTS THEREIN 有权
    用于冷却SLIP接头的涡轮喷嘴和冷却系统

    公开(公告)号：US20150337680A1

    公开(公告)日：2015-11-26

    申请号：US14283104

    申请日：2014-05-20

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Lorenzo Crosatti ,  Ardeshir Riahi ,  Bradley Reed Tucker ,  Shezan Kanjiyani

    IPC: F01D25/12 ,  F01D9/02

    CPC classification number: F01D9/02 ,  F01D9/04 ,  F01D9/042 ,  F01D9/065 ,  F01D25/12 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

    Abstract: Turbine nozzles and cooling systems for cooling slip joints therein are provided. The turbine nozzle has an endwall, a vane coupled to the endwall, a slip joint, and a plurality of airfoil quenching holes that cooperate with a plurality of endwall cooling holes. The vane comprises a leading edge and a trailing edge interconnected by a pressure sidewall and a suction sidewall and an end portion. The slip joint is between the end portion and the endwall. The airfoil quenching holes are defined through the pressure sidewall in the end portion. The endwall cooling holes are defined through the endwall along the pressure sidewall and in proximity to the leading edge. The airfoil quenching holes and endwall cooling holes are disposed adjacent the slip joint.

    Abstract translation: 提供了用于冷却滑动接头的涡轮喷嘴和冷却系统。 涡轮喷嘴具有端壁，联接到端壁的叶片，滑动接头以及与多个端壁冷却孔配合的多个翼型骤冷孔。 叶片包括通过压力侧壁和吸力侧壁和端部部分互连的前缘和后缘。 滑动接头位于端部和端壁之间。 翼型淬火孔通过端部中的压力侧壁限定。 端壁冷却孔沿着压力侧壁并且靠近前缘限定通过端壁。 翼片淬火孔和端壁冷却孔设置在滑动接头附近。

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