吸力面凸台对缩放型流道涡轮动叶气动性能影响的数值研究  

EFFECTS OF SUCTION SURFACE BUMP ON TURBINE CONVERGENTDIVERGENT ROTOR AERODYNAMIC PERFORMANCE

作　　者：雒伟伟[1,2] 张磊[1,2] 王会社[1] 徐建中[1] 黄家骅[1] 

机构地区：[1]中国科学院工程热物理研究所,北京100190 [2]中国科学院研究生院,北京100190

出　　处：《工程热物理学报》2010年第8期1289-1293,共5页Journal of Engineering Thermophysics

基　　金：国家自然科学基金重大研究计划项目(No.90718025);国家重点基础研究发展计划(973计划)项目(No.2010CB227302)

摘　　要：本文采用数值模拟的方法对1＋1/2对转涡轮高压动叶吸力面内伸波作用位置添加凸台以降低激波损失的机理进行了研究。通过详细的数值模拟及流场分析可知,加凸台对于涡轮级间的匹配关系不会带来明显的影响,合适的凸台位置及高度能有效地抑制内伸波引起的边界层分离,并在一定程度上减小内伸波的强度,提高涡轮效率.本文研究结果显示,当凸台位于高压动叶吸力面84%～86%轴向弦长,最大高度为1 mm,且与叶片表面光滑连接时,效果最佳,此时涡轮效率提高约0.11%。A detailed numerical simulation has been carried out to investigate the control mechanism of suction surface bump to reduce the shock wave loss,and the bump places on the high-pressure （HP） rotor suction surface of the 1＋1/2 counter rotating turbine where the inner-extending shock impinges.Through analyzing the results,the bump on the suction surface of the HP rotor will not affect the matching of the turbine stages,however,the appropriate position and height of bump can inhibit effectively the boundary layer separation caused by the inner-extending shock,and decrease the strength of the inner-extending shock and improve the turbine efficiency.In this paper,when the bump locates on 84%～86%axial chord of the HP rotor suction surface and the maximum height of the bump is 1mm,and the bump connects with the rotor surface smoothly,the control effect of the bump is optimum,and the turbine efficiency increases about 0.11%.

关 键 词：1+1/2对转涡轮 缩放型流道 激波 流动控制 数值模拟 

分 类 号：V235[航空宇航科学与技术—航空宇航推进理论与工程]