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选择了一套恰当的跨声速总压损失和落后角模型,将其与逐排基元叶片模型相结合,发展出了准一维多级轴流压气机性能预测方法,该方法进一步与复形调优法相结合,建立了一种新的多级轴流压气机多叶排调节扩稳工程方法,应用该方法对某8级轴流压气机实施了扩稳优化模拟,取得了明显扩稳效果,计算结果进一步表明,复形调优法中的反射系数对最终优化结果影响明显,选反射系数为1.15能够获得较优的优化结果.
A set of appropriate transonic total pressure loss and backward angle models was selected and combined with the row-by-row primitive blade model to develop a quasi-one-dimensional multi-stage axial flow compressor performance prediction method. This method was further compared with the complex shape Tuning method, a new multi-stage axial compressor multi-blade row regulation and expansion engineering method was established. With this method, a steady-state optimization simulation was carried out on an 8-stage axial compressor, and a significant stabilizing effect was obtained The calculation results further show that the reflection coefficient in the complex shape tuning method has a significant effect on the final optimization result, and the optimal reflection coefficient can be obtained by selecting the reflection coefficient of 1.15.