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    • 2. 发明申请
    • FILM COOLING OF TURBINE BLADES OR VANES
    • 涡轮叶片或风扇的薄膜冷却
    • US20140255200A1
    • 2014-09-11
    • US14235060
    • 2012-07-13
    • Liang GuoJohn David MaltsonYuying Yan
    • Liang GuoJohn David MaltsonYuying Yan
    • F01D5/18F01D5/14
    • F01D5/147F01D5/145F01D5/186F01D9/041F05D2240/12F05D2260/202
    • The present invention relates to a turbine assembly having an aerofoil and/or an end wall each having an outer surface with a structure for directing a flow of a cooling medium at the outer surface. The structure at the outer surface has at least a first groove and a second groove extending in the outer surface from a leading to a trailing edge and being oriented in at least two different directions with a deflection angle (α) towards each other, with the deflection angle (α) having a component in a span wise direction of the aerofoil. The structure at the outer surface of the end wall has at least a first groove and a second groove extending in an axial direction of the turbine assembly, matching an outer profile of the aerofoil and oriented in at least two different directions with a deflection angle (α) towards each other.
    • 本发明涉及一种具有机翼和/或端壁的涡轮组件,每个翼片和/或端壁都具有外表面,该外表面具有用于引导冷却介质在外表面的流动的结构。 外表面上的结构具有至少第一凹槽和第二凹槽,该第二凹槽和第二凹槽在外表面中从引导向后缘延伸,并且在至少两个不同的方向上以相对于彼此的偏转角(α)定向, 偏转角(α)在机翼的跨度方向上具有分量。 在端壁的外表面处的结构具有至少第一凹槽和在涡轮组件的轴向方向上延伸的第二凹槽,其匹配翼型的外轮廓并且在至少两个不同方向上以偏转角( α)朝向彼此。