【摘要】 J级重型燃气轮机（进口设计流量约1 000 kg/s）的首级压气机直径可达3 m，难以开展全尺寸几何模型试验，基于相似原理开展缩尺研究是一种经济且简便可行的方法。基于数值方法开展尺寸效应对小/大模型性能及损失影响的对比研究，分析尺寸效应对小/大模型损失影响机制。性能分析结果表明：气动相似的大模型等熵效率明显高于缩比模型，而Casey等提出的等熵效率修正模型偏差不超过0.5%。机理分析表明：在叶尖强激波诱导的泄漏涡破碎区域，二次流主导，大模型损失强于小模型；而其他区域则以基元损失为主，边界层和尾迹掺混损失小模型损失更强；但综合损失仍然是小模型更大。因此影响小/大模型等熵效率的差异主要来源于基元边界层和尾迹掺混损失，而叶尖二次流损失造成的差异并不起决定性作用。这项工作致力于给工业重型燃气轮机设计初期提供参考。更多还原

【Abstract】 It is difficult to conduct the full-scale testing for J-class heavy-duty gas turbine transonic compressors(with an inlet design mass-flow rate of roughly 1 000 kg/s),the diameter of the first stage compressor was nearly 3 m,the turbomachinery designers scaled-down the geometry to meet thepower limitation, which is a convenient method based on similarity principle. This work performed comparative investigations of scaling effects on the aerodynamic performance and loss mechanisms based on the numerical simulation. The results showed that the larger model operated at a higher isentropic efficiency condition. The Casey’s prediction models had a deviation of less than 0.5%. The shock/tip leakage vortex loss and shock-boundary layer interaction loss of the larger model were stronger than those in the prototype model, while the profile boundary loss and wake mixing loss of the prototype model were stronger than the larger model. The profile losses(boundary layer and wake mixing loss) were the main loss source causing the difference in the isentropic efficiency between the prototype and scaled-up compressor rotor,meanwhile,the difference caused by tip secondary flow loss was not the main source.This investigation is intended to provide suggestions for industrial preliminary design stages of the heavyduty gas turbine compressors.更多还原