After optimization, the total pressure loss of the turbine vane was reduced by 0.95%, and the efficiency of the overall compressor was increased by 2.1%.
经优化后，透平高压级静叶的总压损失系数减少0.95%；多级压气机整机效率提高2.1%。
The influence of tip clearance on overall performance and detailed flow structure in tip region of an axial compressor rotor was investigated.
研究了顶部间隙对压气机转子总性能及内部流场的影响。
The overall performance for NASA 37 low-aspect ratio compressor stage at 70% design rotating speed was obtained and the internal flow fields at typical operating conditions were emphatically analyzed.
计算得到了NASA 37号低展弦比、跨音速轴流压气机级70％设计转速下的全工况性能曲线，并重点分析了其中一些典型工况下的内部流场。
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