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为了研究跨声速轴流压气机的性能分析问题,采用流线曲率法结合损失落后角模型,发展了一种利用反问题方程求解正问题的数值方法。在NASA低速平面叶栅试验数据的基础上考虑三维效应的修正,根据激波结构随工况的变化发展了一种新的激波损失计算方法,整理了一套适合跨声速轴流压气机的损失落后角模型。对两级跨声速轴流风扇进行了数值模拟研究,进行了设计工况的校核计算和全工况特性预测,并将计算结果与NASA试验值进行了比较分析。结果显示,设计点计算误差在1.1%以下,非设计点也能得到与试验值吻合的趋势,表明所建立的方法和模型可以有效地对跨声速多级轴流压气机进行全工况特性预测。
In order to study the performance analysis of transonic axial flow compressors, a numerical method of solving positive problems using inverse problem equations is developed by using streamline curvature method and loss-backward angle model. Based on NASA’s low-speed plane cascade test data, a three-dimensional correction is considered. Based on the change of shock wave structure with the working conditions, a new shock loss calculation method is developed and a set of suitable transonic axial compressors Loss of backward angle model. The two-stage transonic axial fan was numerically studied, the calculation of design conditions and the prediction of full-load conditions were carried out. The calculated results were compared with the NASA test values. The results show that the calculated error of design point is below 1.1%, and the non-designed point can also be in agreement with the experimental value. It shows that the proposed method and model can effectively predict the performance of transonic multistage axial-flow compressor .