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    • 1. 发明申请
    • AIR COOLED GAS TURBINE COMPONENTS AND METHODS OF MANUFACTURING AND REPAIRING THE SAME
    • 空气冷却气体涡轮机组件及其制造和修理方法
    • US20090142548A1
    • 2009-06-04
    • US11926986
    • 2007-10-29
    • David Bruce PattersonJohn StarkweatherThomas HollandThomas Tomlinson
    • David Bruce PattersonJohn StarkweatherThomas HollandThomas Tomlinson
    • B32B3/10B05D3/12B32B43/00
    • F01D25/12C23C4/01C23C4/02C23C28/3215C23C28/325C23C28/345C23C28/3455F01D5/005F01D5/288F01D9/023F23M2900/05004F23R3/007F23R3/06Y02T50/67Y02T50/675Y02T50/6765Y10T428/24322
    • A component suitable for use in a gas turbine engine. The component includes a substrate defining a surface of the component and has a first surface and a second surface. At least one aperture extends through the substrate from the first surface to the second surface, and has a first open area. The component has a first coating on at least one of the first surface and the second surface adjacent to the at least one aperture. The component also has a second coating overlying the first coating adjacent to the at least one aperture, such that at least a portion of the first coating is exposed adjacent to the at least one aperture. The first coating defines a second open area which is smaller than the first open area. In another aspect, a method of manufacturing a component suitable for use in a gas turbine engine, comprising the steps of forming the component from a substrate having a first surface and a second surface, forming at least one aperture through the substrate from the first surface to the second surface having a first open area, applying a first coating to at least one of the first surface and the second surface adjacent to the at least one aperture, the aperture remaining at least partially unobstructed by the first coating, applying a second coating to the first coating adjacent to the at least one aperture, the aperture remaining at least partially unobstructed by the second coating, and removing the second coating from the aperture, leaving most or all of the first coating to define a second open area which is smaller than the first open area. In a further aspect, a method of repairing a component suitable for use in a gas turbine engine, the method comprising the steps of removing coatings from the component, repairing any defects in the substrate of the component, and applying coatings as described herein.
    • 适用于燃气涡轮发动机的部件。 该部件包括限定部件的表面并具有第一表面和第二表面的基板。 至少一个孔从第一表面延伸穿过基底到第二表面,并且具有第一开口区域。 所述部件在与所述至少一个孔相邻的所述第一表面和所述第二表面中的至少一个上具有第一涂层。 所述部件还具有覆盖邻近所述至少一个孔的所述第一涂层的第二涂层,使得所述第一涂层的至少一部分暴露于所述至少一个孔附近。 第一涂层限定比第一开口区域小的第二开口区域。 在另一方面,一种制造适用于燃气涡轮发动机的部件的方法,包括以下步骤:从具有第一表面和第二表面的基底形成所述部件,从所述第一表面形成穿过所述基板的至少一个孔 到具有第一开放区域的第二表面,向邻近所述至少一个孔的所述第一表面和所述第二表面中的至少一个施加第一涂层,所述孔至少部分地被所述第一涂层阻挡,施加第二涂层 至少邻近于所述至少一个孔的所述第一涂层,所述孔至少部分地被所述第二涂层阻挡,并且从所述孔移除所述第二涂层,使所述第一涂层的大部分或全部限定为较小的第二开口区域 比第一个开放区域。 在另一方面,一种修复适用于燃气涡轮发动机的部件的方法,所述方法包括以下步骤:从组件去除涂层,修复部件的基底中的任何缺陷,以及如本文所述的涂覆涂层。