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目前航空发动机涡轮叶片的弦中区大多采用稀疏型(相对叶片前缘)气膜冷却技术。实验研究了这种复合冷却方式中带有冲击射流和没有冲击射流两种情况下的稀疏型气膜出流内部冷气侧换热特性,通过对大量的实验数据分析,得出了诸多流动及几何参数对叶片内表面换热特性的影响,并在实验参数范围内整理出了换热准则关系式。其分析结果及相应准则关系式对叶片的结构设计具有直接的指导意义。
At present, the aero-engine turbine blade chordal zone mostly adopts the sparse type (relative blade leading edge) film cooling technology. Experiments were carried out to study the heat transfer characteristics of the spilled gas film outflow in the combined cooling mode with and without impinging jets. By analyzing a large amount of experimental data, many flow and geometry Parameters on the heat transfer characteristics of the inner surface of the blade, and sorted out the heat transfer criterion within the experimental parameters. The analysis results and the corresponding relationship between the rules of the blade structure design has a direct guiding significance.