跨声速多级轴流压气机特性预估及分析 *

Performance Prediction and Analysis of Multi-stage Transonic Axial Compressors

关键词:  跨声速  轴流压气机  流线曲率法  损失落后角模型

Key words:  Transonic  Axial compressor  Streamline curvature method  Loss and deviation model

摘要:

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。

Abstract:

An improved streamline curvature method (SLCM) which approximates the aerodynamic performance of transonic axial compressor through the inverse problem is developed. The loss and deviation model based on NASA low speed cascade test data is modified for a more realistic estimation considering transonic and 3-D flow phenomena. Moreover，a new shock loss estimation method in which the shock structure changes along with working condition is incorporated into the streamline curvature code (SLCC). The design and off-design performance of a two-stage transonic axial fan is predicted and the comparison with NASA original design and experiment data is made. The results show that the calculation error of design point is below 1.1% and consistent trend with test data is obtained at off-design conditions，which indicates that the improved SLCM is capable of overall performance predication for multistage transonic axial compressor efficiently.