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    • 53. 发明授权
    • Turbine blade tip squealer and rebuild method
    • 涡轮叶尖尖叫声和重建方法
    • US07591070B2
    • 2009-09-22
    • US11766488
    • 2007-06-21
    • Ching-Pang Lee
    • Ching-Pang Lee
    • B23P15/02F01D5/20
    • B23P6/007F01D5/005F01D5/20F05D2260/202Y10T29/49318Y10T29/49337Y10T29/49339Y10T29/49341Y10T29/49728Y10T29/53091
    • A turbine blade with a tip squealer and method of rebuilding a turbine blade for a gas turbine engine. The blade is of the type including an airfoil having first and second spaced-apart sidewalls defining an interior void and joined at a leading edge and a trailing edge. The first and second sidewalls extending from a root disposed adjacent the dovetail to a tip cap for channeling combustion gases, and a squealer tip including at least one tip rib extending outwardly from the tip cap. The method includes the steps of removing the squealer tip, including the at least one rib tip, from the tip cap and adding new material to the tip cap to serve as a new squealer tip. A plurality of spaced-apart notches is formed in the new material between the leading edge and the trailing edge of the airfoil. At least one hole is formed in each notch communicating with the interior void of the airfoil for channeling cooling air from the interior void of the airfoil to thereby form a squealer tip.
    • 具有尖端喷嘴的涡轮机叶片和用于重建用于燃气涡轮发动机的涡轮机叶片的方法。 叶片类型包括具有限定内部空隙并且在前缘和后缘处连接的第一和第二间隔开的侧壁的翼型件。 所述第一和第二侧壁从邻近所述燕尾榫设置的根部延伸到用于引导燃烧气体的尖端帽,以及尖叫尖端,其包括从所述尖端帽向外延伸的至少一个尖端肋。 该方法包括以下步骤:从顶盖移除包括至少一个肋尖端的尖叫尖端,并将新材料添加到尖端盖以用作新的尖叫尖端。 在翼缘的前缘和后缘之间的新材料中形成多个间隔开的凹口。 在与翼型件的内部空隙连通的每个凹口中形成至少一个孔,用于从翼型的内部空间引导冷却空气,从而形成尖叫尖端。
    • 59. 发明授权
    • Thermally compliant turbine shroud mounting assembly
    • 符合标准的涡轮机罩安装组件
    • US07438520B2
    • 2008-10-21
    • US11161516
    • 2005-08-06
    • Michael Anthony RuthemeyerGlenn Herbert NicholsChing-Pang Lee
    • Michael Anthony RuthemeyerGlenn Herbert NicholsChing-Pang Lee
    • F01D11/08
    • F01D11/08F01D11/12F01D11/122
    • A shroud assembly is provided for a gas turbine engine that has a temperature at a hot operating condition substantially greater than at a cold assembly condition thereof. The shroud assembly includes: at least one arcuate shroud segment adapted to surround a row of rotating turbine blades which has an arcuate, axially extending mounting flange; a shroud hanger having an arcuate, axially-extending hook disposed in mating relationship to the mounting flange; and an arcuate C-clip having inner and outer arms overlapping the hook and the mounting flange. The curvatures of the mounting flange and the inner arm of the C-clip are selected so as to define a matched interface therebetween. Their curvatures are substantially greater that the curvature of the hook.
    • 提供一种用于燃气涡轮发动机的护罩组件,其具有基本上大于其冷组装状态下的热操作状态的温度。 所述护罩组件包括:至少一个弧形护罩段,其适于包围一排旋转的涡轮叶片,所述旋转涡轮叶片具有弓形的轴向延伸的安装凸缘; 护罩悬挂器具有与安装凸缘成配合关系设置的弓形的轴向延伸的钩; 以及弓形C形夹具,其内外臂与钩和安装法兰重叠。 选择安装法兰和C形夹的内臂的曲率,以便在它们之间限定一个匹配的接口。 它们的曲率大大地大于钩的曲率。