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涡轮叶片内的冲击换热多取近距离散冲击换热 (冲击距与喷孔直径之比 Zn/dn<3,喷孔中心距与喷孔直径之比 Cn/dn<3)。由于在叶片前缘有气膜出流孔 ,因而对叶片内前缘冲击换热做大面积平均实用意义较小。所以本实验旨在总结近距冲击下驻点连线及驻点附近小面积的换热规律并得出新的经验公式 ,这具有较大的实用意义。
The impact heat exchanger in the turbine blade should take close proximity impact heat transfer (the ratio of impact distance to orifice diameter is Zn / dn <3, the ratio of orifice center to orifice diameter Cn / dn <3). Because there is a film outlet hole in the leading edge of the blade, it is of less practical significance to apply a large area to the impact heat exchange in the leading edge of the blade. Therefore, the purpose of this experiment is to summarize the rule of heat transfer and the new empirical formula for the connection of stagnation point and the small area near stagnation under the close impact, which has great practical significance.