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基于亚声速叶栅设计点损失预估模型,结合无粘S1流场与附面层迭代计算发展了一套计算大弯角轴流压气机平面叶栅流场程序。增加弯度比分布及最大厚度修正得到设计点损失预估模型,采用马赫数修正后的叶栅有效工作范围得到一套大弯角叶栅全工况损失预估模型。分析了轴向密流比在实验中对叶栅损失系数的影响。结果表明,S1流场计算程序与修正后的损失预估模型均能准确地预估出大弯角叶栅设计点损失系数,误差分别小于0.006与0.004。非设计点损失模型能有效地预估得到叶栅有效工作范围内的损失随攻角的分布。初步验证了损失模型对高亚声速大弯角平面叶栅损失系数预估的准确性。
Based on the prediction model of the design point loss of subsonic cascades, a set of program to calculate the flow field in the plane cascade of the large-angled axial compressor was developed based on the calculation of the flow field of viscous S1 and the iterative calculation of the surface layer. Increasing the distribution of camber ratio and the maximum thickness correction to get the prediction model of the design point loss, and using Mach-corrected blade effective working range to get a prediction model of the loss of full-load cascade at large camber angle. The effect of axial flow ratio on the cascade loss coefficient in the experiment was analyzed. The results show that both the S1 flow field calculation program and the revised prediction model can accurately estimate the design point loss coefficient of cascade cascades with errors less than 0.006 and 0.004 respectively. The non-design point loss model can effectively predict the distribution of loss with angle of attack in the effective working range of cascade. The accuracy of the loss model for predicting the loss coefficient of cascades at high subsonic speed is verified.