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为探索转子叶尖叶型对轴流压气机叶尖端壁区域流动的影响,进一步改善轴流压气机性能,采用近似函数与遗传算法相结合的优化方法,针对1/2+1级轴流压气机在级环境下进行转子叶尖叶型优化设计,并对优化前后轴流压气机级流场进行对比分析。结果表明:转子叶尖优化改型后,轴流压气机级效率提升0.77%,设计转速下全工况范围内效率、压比均得到显著提高;该压气机效率的提高主要得益于叶型损失和泄漏流损失的降低,优化改型后的叶型更能适应叶尖区域的高亚声来流,转子叶尖激波被有效抑制,叶尖泄漏流减弱,叶尖端壁区域流动明显改善。
In order to explore the influence of the rotor blade tip on the axial flow compressor tip end wall area and to further improve the performance of the axial compressor, the optimization method combining the approximate function and the genetic algorithm is adopted. According to the 1/2 + 1 axial compression The rotor blade tip optimization design was carried out in the grade environment, and the axial compressor flow field was compared before and after optimization. The results show that the axial compressor efficiency increases by 0.77% after optimization of the rotor tip, and the efficiency and pressure ratio are significantly increased under the full operating conditions at design speed. The efficiency of the compressor is mainly due to the increase of the efficiency of the blade Loss and loss of leakage flow. The optimized modified leaf shape can adapt to the high subsonic flow in the tip region, the rotor tip shock is effectively suppressed, the tip leakage flow is weakened, and the flow in the tip tip wall area is obviously improved.