U型槽对高负荷低压涡轮叶型攻角特性影响  

Effect of U-grooves on high-lift low pressure turbine profile's incidence characteristics

作　　者：张波[1,2] 李伟[1,2] 杜强[1,2] 黄恩亮[1,2] 卢新根[2] 朱俊强[2] 

机构地区：[1]中国科学院研究生院,北京100190 [2]中国科学院工程热物理研究所轻型动力重点实验室,北京100190

出　　处：《航空动力学报》2012年第7期1503-1510,共8页Journal of Aerospace Power

基　　金：国际科技合作项目(2010DFB70620);国家自然科学基金(51176187)

摘　　要：以某高负荷低压涡轮叶型为研究对象,分析了该叶型在低雷诺数下的攻角特性,并应用了表面嵌壁式U形槽的被动控制方法来提高该叶型的攻角裕度.数值模拟的结果表明:相比较大的正攻角流动状况,叶型较大的负攻角并不会引起吸力面大的流动分离,从而减小了叶型损失;表面嵌壁式U型槽通过推迟分离、加速再附来减小分离泡甚至减小湍流湿面积,从而降低叶型损失;表面嵌壁式U型槽能否提高该叶型的攻角裕度与开槽位置和深度有关系,在±15°攻角范围内72%轴向弦长位置处开槽明显的降低了叶型损失而开槽深度为0.40mm时叶型损失最小.The high-lift low pressure turbine blade profile incidence characteristics under low Reynolds number were investigated. The modification used recessed U-grooves to im- prove the profiles~ incidence margin. The numerical simulations suggest that compared with high incidence flow condition, lower incidence does not induce large separation which ap- pears on the suction surface of the profile and hence lessens profile loss. The recessed U- grooves delay the separation location, accelerate reattach location, decrease the turbulent wetted area, thereby the separation bubble is suppressed and the profile loss decreases. Whether or not the recessed U-grooves can improve the incidence margin is related to the depth and location of the U-grooves. With±15 incidence degrees, the U-grooves located in 72% axial chord length showed lower profile loss, and when the depth was 0. 40mm the pro- file loss was the lowest.

关 键 词：低雷诺数 高负荷 攻角裕度 叶型损失 嵌壁式U型槽 

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]