一种多级轴流压气机不同工况叶尖间隙预估模型  

A prediction model for tip clearance of multi-stage axial compressor in different operating conditions

作　　者：杨栋[1,2] 李绍斌[1,2] 李秋实[1,2] 

机构地区：[1]北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室,北京100191 [2]先进航空发动机协同创新中心,北京100191

出　　处：《航空动力学报》2014年第11期2579-2586,共8页Journal of Aerospace Power

基　　金：国家自然科学基金(51176005)

摘　　要：考虑热负荷以及机械负荷的影响,建立了一种多级轴流压气机不同工况叶尖间隙的预估模型.模型针对多级轴流压气机考虑了温度在径向和轴向的分布,保证了模型的准确性.通过与通用电气公司E3发动机试验结果的对比,计算模型预估叶尖间隙在第3,5,10级的相对误差分别为0.8%,5.6%,3.7%,显示该方法能很好地揭示叶尖间隙在不同工况下的变化规律.模型在叶尖间隙随轮盘内腔冷气流量的变化趋势上预估与试验是一致的,在第3,10级叶尖间隙预估值的相对误差分别为9.7%,6.7%.试验中使用主动控制技术,得到其所能达到的最大叶尖间隙关小量在第10级转子处为0.203 2mm,而模型预估所得调节流量所能达到的最大叶尖间隙关小量在第10级转子处为0.14mm,显示模型较好地反映了主动叶尖间隙控制技术的效果.A prediction model for tip clearance of multi-stage axial compressors in different operating conditions was proposed,considering the effect of thermal and mechanical loading.The radial and axial temperature distribution across every stage of the multi-stage axial compressors was considered by the proposed model to ensure the accuracy.The model was validated by General Electric Company（GE）E3engine test results.The comparison shows that the proposed model has high accuracy to uncover the varying rule of tip clearance in different operating conditions,and the relative errors are 0.8%,5.6%,3.7%in the calculation of tip clearance for stage 3,5,and 10,respectively.The estimated trend in the variation of disk cavity cold airflow with tip clearance is consistent with the experimental data,and the relative errors are 9.7% and 6.7%in the estimated tip clearance of stage 3and 10,respec-tively.The maximum change of tip clearance obtained with the active control technology in the tests is 0.203 2mm at the stage 10,which is estimated as 0.14 mm using the model.The magnitude of tip clearance and the tip clearance active control technology effects are estimated quite well,and the proposed model is verified.

关 键 词：多级轴流压气机 叶尖间隙 不同工况 温度分布 预估模型 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]