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提高涡轮前温度可改善发动机性能。当前国外先进航空发动机的涡轮前温度已提 高到1700K左右。远远超过了材料容许的温度,这就必须采用有效的冷却技术。在涡轮叶片上以冲击-气膜复合冷却应用得最为广泛。在国内外发表的一些文献中,对纯冲击冷却及纯气膜冷却都曾进行过大量研究。但目前对冲击-气膜复合冷却的研究公开发表的文献尚不多见。本文仅就叶片前缘的冲击-气膜复合冷却的机理通过实验作初步的探讨。
Increasing the turbine’s temperature improves engine performance. The current foreign advanced aero-engine turbine front temperature has been increased to about 1700K. Far beyond the allowable temperature of the material, which necessitates effective cooling techniques. Impact on the turbine blade - air-film composite cooling is the most widely used. In some published literature both at home and abroad, a great deal of research has been conducted on pure impingement cooling and pure film cooling. However, the published literature on the impact-film composite cooling is still rare. In this paper, only the impact of the leading edge of the blade - the mechanism of film composite cooling through experiments for preliminary discussion.