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    • 10. 发明授权
    • Methods and apparatus for cooling combustion turbine engine components
    • 用于冷却燃气涡轮发动机部件的方法和装置
    • US07303372B2
    • 2007-12-04
    • US11282348
    • 2005-11-18
    • James Anthony WestWilliam Stephen KvasnakBrendan Francis Sexton
    • James Anthony WestWilliam Stephen KvasnakBrendan Francis Sexton
    • F03B11/02
    • F01D9/047F01D5/187F01D9/065F01D11/001F02C3/14F02C6/08F02C7/18Y02T50/673Y02T50/676
    • A turbine nozzle cooling sub-system is provided. The sub-system includes at least one turbine nozzle segment. The segment includes an arcuate, radially outermost endwall, an arcuate, radially innermost endwall, and at least one airfoil vane. The endwalls each include at least one open passage. The airfoil vane extends between and is coupled to the endwalls. The vane further includes a cavity, a leading edge, a trailing edge, and an airfoil vane external surface. The cavity includes an airfoil vane internal surface and a plurality of turbulators. The cavity and the open passages are in flow communication such that an airfoil cooling air stream flow is facilitated. The sub-system also includes at least one diffuser in flow communication with a compressor assembly and the segment. The diffuser includes at least one diffuser wall and cavity. The diffuser wall extends from the compressor assembly to the segment such that a channeling of the airfoil cooling air stream to the segment is facilitated. The airfoil cooling air stream includes at least a portion of a compressor assembly discharge air stream flow.
    • 提供涡轮喷嘴冷却子系统。 该子系统包括至少一个涡轮喷嘴段。 该段包括弧形的径向最外端壁,弧形径向最内端壁和至少一个翼型叶片。 端壁每个包括至少一个开放通道。 翼型叶片在端壁之间延伸并连接到端壁。 叶片还包括空腔,前缘,后缘和翼型叶片外表面。 空腔包括翼型叶片内表面和多个湍流器。 空腔和开放的通道是流动连通的,使得翼型件冷却空气流流动变得容易。 子系统还包括至少一个与压缩机组件和段流动连通的扩散器。 扩散器包括至少一个扩散器壁和空腔。 扩散器壁从压缩机组件延伸到段,使得翼型冷却空气流向段的通道变得容易。 翼型冷却空气流包括至少一部分压缩机组件排出气流。