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    • 1. 发明公开
    • 가스 터빈용 블레이드
    • 燃气轮机叶片
    • KR1020070006875A
    • 2007-01-11
    • KR1020067022554
    • 2005-04-19
    • 제네럴 일렉트릭 테크놀러지 게엠베하
    • 라트만울리히
    • F01D5/20F01D5/18F01D11/10
    • F01D11/10F01D5/186F01D5/187F01D5/225F05D2260/201F05D2260/202
    • The invention relates to a gas turbine blade (1) comprising a cover strip (3) which is cooled in different zones (A, B, C) by different cooling systems in accordance with the different thermal loads. In a first zone (A) an edge (8) is provided with bores which effect a convective cooling of the edge and a film cooling of the hot gas side of the edge. A second zone (B) is cooled by impingement cooling by a cooling air flow from a channel in the radially opposite stator housing. A third zone (C) is provided with a plurality of parallel bores that extend from a cooling channel of a cooling system for the blade to the radially outer surface of the cover strip. A cooling air flow flowing through these bores effects a convective cooling of this zone. ® KIPO & WIPO 2007
    • 本发明涉及一种包括盖带(3)的燃气轮机叶片(1),其通过不同的冷却系统根据不同的热负荷在不同的区域(A,B,C)中冷却。 在第一区域(A)中,边缘(8)设置有孔,其实现边缘的对流冷却和边缘的热气体侧的薄膜冷却。 第二区域(B)通过来自径向相对的定子壳体中的通道的冷却空气流的冲击冷却来冷却。 第三区域(C)设置有多个平行孔,其从用于叶片的冷却系统的冷却通道延伸到盖带的径向外表面。 流过这些孔的冷却空气流影响该区域的对流冷却。 ®KIPO&WIPO 2007