多级轴流压气机二维性能预测方法  

2Dperformance prediction approach for multi-stage axial compressors

作　　者：杨晓飞 蒋永松 潘若痴 孟德君 YANG Xiaofei;JIANG Yongsong;PAN Ruochi;MENG Dejun(AECC Shenyang Engine Research Institute,Shenyang 110015,China)

机构地区：[1]中国航发沈阳发动机研究所,沈阳110015

出　　处：《航空学报》2020年第3期200-210,共11页Acta Aeronautica et Astronautica Sinica

摘　　要：为了满足多级轴流压气机性能预估需求,在一个流线曲率程序基础上开展了经验、半经验关系式研究。通过对文献中的损失模型进行校验及融合,建立了相匹配的损失计算模块,并改进了端壁损失计算方法;研究了利用S1流面计算修正S2正问题的方法,解决了基于传统平面叶栅试验数据的攻角、落后角模型与先进技术叶型之间不匹配的问题,继而发展出了一个高精度的S2正问题计算方法。为了验证计算方法,利用3个不同负荷水平的、经试验验证的多级压气机进行了校验计算。对比表明,发展的程序对多级压气机具有很高的计算精度和稳定性,可用于多级轴流压气机性能分析。This paper conducts a study on the empirical and semi-empirical models for performance prediction of multi-stage axial compressors based on a streamline curvature code.By verifying and integrating the models in literature,a matching loss calculation module is set up,and the endwall loss model is improved.An approach for revising the S2forward problem is developed with S1stream surface calculation,and the contradiction between the angle of incidence and deviation angle models based on the data from traditional cascade tests and state-of-the-art airfoils is solved.Then,a S2analysis program with high solution accuracy is developed.Three experimental compressors with different work coefficients are used to validate the approach.An overall comparison demonstrates that the improved program can have high accuracy and stability,and is applicable for performance analysis of multi-stage axial compressors.

关 键 词：多级压气机 性能预测 损失 攻角 落后角 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]