外涵静子后掠对某风扇/增压级气动特性的影响  

Effect of Bypass Duct Backward Swept Stator Blade on Performance of Fan/Compressor

作　　者：李晓娟[1] 金海良[2] 桂幸民[3] 

机构地区：[1]中国航天工程咨询中心,北京100037 [2]中航工业航空动力机械研究所,湖南株洲412002 [3]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《航空发动机》2013年第4期26-31,共6页Aeroengine

基　　金：国家自然科学基金(50736007;51006005)资助

摘　　要：针对某大涵道比风扇/增压级外涵静子后掠降噪的优化设计目标,采用1种周向平均快速特性预测计算方法和3维数值模拟软件NUMECA,对其100%设计转速下外涵静子无后掠及轴向后掠22.5°和30°算例的特性曲线及流场进行了对比分析,以研究外涵静子轴向后掠对风扇/增压级特性及气动性能的影响规律。结果表明:一定程度的轴向后掠角度会使静子表面静压在叶尖处增强,而根部的叶片表面静压分布更趋均匀,风扇/增压级的外涵气动特性在裕度上无明显恶化;但严重的后掠角度则会导致叶尖叶片表面载荷显著增加,从而造成外涵的喘振裕度减小,进而影响整个风扇/增压级的气动性能。To meet the challenge of a high bypass ratio fan/compressor optimization design on noise reduction, using the circumferentially-averaged method and the multi-blade-row computational techniques, the aerodynamic performance of three types with swept bypass stator at 0°, 22.5° and 30° sweep angle were simulated at 100% design rotational speed, and the detailed results were analyzed respectively and compared with results obtained from 3D numerical simulation software NUMECA. The results show that the axial sweep degree will make the blade surface pressure of the stator static pressure increase in tip, and the blade surface static pressure distribution of root become more uniform, then the aerodynamic performance margine of fan/compressor bypass is changed a little. But larger sweep degree will increase blade tip surface load, decrease bypass surge margin, furthermore it affects the aerodynamic performance of the fan/compressor bypass.

关 键 词：风扇 增压级 外涵静子 降噪 后掠 航空发动机 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]