带有轮缘密封的涡轮动叶轮毂端壁造型  

Endwall profiling of turbine blade hub with rim seal

作　　者：何振鹏 周佳星 辛佳 杨成全 孙爱俊 黎柏春 HE Zhenpeng;ZHOU Jiaxing;XIN Jia;YANG Chengquan;SUN Aijun;LI Baichun(School of Aeronautical Engineering,Civil Aviation University of China,Tianjin 300300,China)

机构地区：[1]中国民航大学航空工程学院,天津300300

出　　处：《北京航空航天大学学报》2023年第10期2596-2607,共12页Journal of Beijing University of Aeronautics and Astronautics

基　　金：中央高校基本科研业务费专项资金(3122019075)。

摘　　要：为通过主动端壁控制技术减弱轮缘密封流对主流通道的影响,基于轮毂端壁静压对高压涡轮动叶端壁非轴对称端壁造型,分析了转静间隙密封流与主流相互作用及端壁造型后损失减弱的效果。结果表明:非轴对称端壁造型后密封流对主流通道的堵塞减弱,主流质量流量增加,合理控制端壁造型幅值能够提升涡轮级工作效率;靠近动叶前缘向上凸起的端壁造型增加了轮缘密封腔出口位置的径向压力梯度,增大了燃气入侵与密封出流的强度;主动端壁控制技术降低了主流通道内的横向压力梯度和轮毂二次流结构径向位置,减弱了由密封流引起的二次流损失;密封流质量流量比为1.2%时,造型幅值为5%和8%模型二次流动能分别减少了1.18%和3.76%。To investigate the effect of active endwall control on reducing the influence of rim seal flow on the mainstream passage,this study analyzed the aerodynamic losses of the interaction between the purge flow and the main flow,and the effect of the endwall profiling on the losses reduction,based on the non-axisymmetric endwall profiled by hub static pressure.The results showed that the non-axisymmetric endwall profiling reduces the blockage of the main flow passage by the purge flow,and increases the mass flow rate.The efficiency of the turbine can be increased with a reasonable control of the endwall profiling amplitude.The convex end wall profiling near the leading edge of the blade increases the radial pressure gradient at the exit of the rim seal cavity,and increases the intensity of gas ingestion and purge flow injection.The non-axisymmetric hub endwall profiling reduces the transverse pressure gradient in the main flow passage,lowers the radial position of the hub secondary flow structure and reduces the secondary flow losses caused by the purge flow.The secondary flow kinetic energy is reduced by 1.18%and 3.76%for models with modelling amplitudes of 5%and 8%respectively at the purge flow ratio of 1.2%.

关 键 词：非轴对称端壁 轮缘密封 燃气入侵 密封效率 端区流动 

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]