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为研究多级跨声速压气机的分析问题,以通流理论为基础,采用了一系列适用于跨声速压气机的攻角、落后角和损失等经验模型,发展了一套基于流线曲率法的通流计算程序来预测跨声速压气机流场及其工作特性。为提高经验模型的预测精度,考虑到真实压气机中复杂的三维流动效应,针对部分早期模型进行了合理改进,包括改进了落后角模型使其适用于更大弯度范围叶型,以及采用一种更为合理的可变结构激波损失预测模型。针对两台跨声速压气机算例进行了计算校验,并将校验结果与实验值和三维数值计算进行对比。对比表明,设计工况下总压比最大计算误差为4.1%,效率误差为1.1%,在非设计工况特性预测和展向流场参数计算中也能得到和实验值相符的变化趋势,该通流计算方法可为现代跨声速轴流多级压气机特性分析提供具有参考价值的预测结果。
In order to study the analytical problems of multistage transonic compressors, a series of empirical models suitable for the transonic compressor, such as the angle of attack, the backward angle and the loss, are adopted based on the flow theory. Through-flow calculation program to predict the transonic compressor flow field and its operating characteristics. In order to improve the prediction accuracy of the empirical model, some early models are improved reasonably considering the complicated three-dimensional flow effect in the real compressor, including the improvement of the backward angle model to be applied to the blade with larger camber range, A more reasonable predicting model of shock wave in variable structure. Computation of two transonic compressors was carried out, and the results were compared with the experimental and three-dimensional numerical calculations. The comparison shows that the maximum error of total pressure ratio under design conditions is 4.1% and the efficiency error is 1.1%. The variation trend corresponding to the experimental value can also be obtained in the prediction of non-design conditions and the calculation of flow field parameters Flow calculation method can provide valuable predictive results for the characteristics analysis of modern transonic multi-stage axial-flow multi-stage compressors.