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    Gas turbine engine components having sealed stress relief slots and methods for the fabrication thereof
    55.
    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。

    SHROUDED BONDED TURBINE ROTORS AND METHODS FOR MANUFACTURING THE SAME
    56.
    发明申请
    SHROUDED BONDED TURBINE ROTORS AND METHODS FOR MANUFACTURING THE SAME 审中-公开
    SHROUDED BONDED TURBINE ROTORS AND METHODS FOR MANUIFACTTING THE SAME

    公开(公告)号：US20160084103A1

    公开(公告)日：2016-03-24

    申请号：US14495319

    申请日：2014-09-24

    申请人： HONEYWELL INTERNATIONAL INC.

    发明人： Michael Kahrs ,  Timothy Vander Hoek ,  Loris Bedrosyan ,  Jason Smoke ,  Ardeshir Riahi ,  Daniel C. Crites

    IPC分类号： F01D11/12 ,  F01D5/22 ,  B23P15/04

    CPC分类号： B23P15/04 ,  B23K20/02 ,  B23K20/233 ,  B23K2101/001 ,  B23K2103/18 ,  B23K2103/26 ,  B23P15/006 ,  F01D5/3061 ,  F01D5/34 ,  F05D2230/232

    摘要： Methods are provided for manufacturing a shrouded bonded turbine rotor. A shrouded blade ring is formed. The shrouded blade ring is formed by bonding a unitary shroud ring to an assembled blade ring or assembling a plurality of shrouded turbine blade segments. The shrouded blade ring is bonded to a hub. The shrouded bonded turbine rotors are also provided. The shrouded bonded turbine rotor comprises a shrouded blade ring and a shroud. The shrouded blade ring comprises a plurality of turbine blade segments and a shroud. Each turbine blade segment comprises an airfoil portion including an airfoil having a root and a tip. The shroud covers the tip of each airfoil in the shrouded blade ring. A hub is bonded with the shrouded blade ring.

    摘要翻译： 提供了用于制造被覆盖的粘结涡轮转子的方法。 形成有盖的叶片环。 被覆盖的叶片环通过将整体护罩环结合到组装的叶片环或组装多个带盖的涡轮叶片段而形成。 被覆盖的叶片环结合到轮毂。 还提供了带盖的粘合涡轮转子。 被覆盖的粘合涡轮转子包括被覆盖的叶片环和护罩。 被覆盖的叶片环包括多个涡轮叶片段和护罩。 每个涡轮机叶片段包括翼型部分，其包括具有根部和尖端的翼型件。 护罩覆盖被覆盖的叶片环中每个翼型的末端。 轮毂与被覆盖的叶片环结合。