跨声速涡轮叶片半劈缝长度及冷气量对叶栅流场的影响  

Effects of Cut-back Length and Ejection Rate of Coolant on the Flow Field in a Transonic Turbine Cascade

作　　者：王宇峰[1] 蔡乐[1] 王松涛[1] 周逊[1] WANG Yu-feng;CAI Le;WANG Song-tao;ZHOU Xun(Engine Aerodynamics Research Centre,Harbin Institute of Technology,Harbin 150001,China)

机构地区：[1]哈尔滨工业大学发动机气体动力研究中心,哈尔滨150001

出　　处：《汽轮机技术》2018年第1期37-40,52,共5页Turbine Technology

摘　　要：通过在不同尾部劈缝结构以及冷气量情况下对某型跨声速叶栅数值模拟,得出了劈缝长度及冷气量对叶栅流道内及尾缘附近流场结构影响的规律。主要表现为:尾缘劈缝结构使叶片尾缘内伸波变为两道;长尾缘劈缝以及大尾缘冷气量不仅能够减小尾迹宽度、降低尾缘损失,也能够使叶片吸力面分离泡减小,黏性损失降低。In order to find out the mechanism of how cut-back length and coolant ejection rate at trailing edge affect the flow structures in transonic turbine cascades,numerical simulations were performed in several cascades with varying cut-back lengths and ejecting rates.The results showed that the cut-back structure at trailing edge can separate inner-extending shockwave into two shockwaves.Longer cut-backs or higher ejection rates of trailing edge coolant can reduce flow separation on suction side near trailing edge,which narrows the wake flow and decrease trailing edge loss.Besides,longer cut-backs or higher ejection rates can also diminish the separation bubble on suction side and reduce viscosity loss of blade profile.

关 键 词：尾缘劈缝 冷气 激波 损失 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]