轮缘密封导流段轴向相对位置对涡轮级气动冷却特性影响的数值研究  

Numerical Investigations for Effects of the Rim Seal Position on Aerodynamic Performance of Turbine Stage and Film Cooling Performance on Rotor Hub Platform

作　　者：高庆 朱蓬勃[1,2] 石慧 屈杰[1,2] 居文平 李军[3] GAO Qing;ZHU Peng-bo;SHI Hui;QU Jie;JU Wen-ping;LI Jun(Xi'an Thermal Power Research Institute Co.,Ltd.,Xi'an 710054,China;Xi'an TPRI Energy Conservation Technology Co.,Ltd.,Xi'an 710054,China;Institute of Turbomachinery,Xi'an Jiaotong University,Xi'an 710049,China)

机构地区：[1]西安热工研究院有限公司,西安710054 [2]西热节能技术有限公司,西安710054 [3]西安交通大学叶轮机械研究所,西安710049

出　　处：《汽轮机技术》2021年第4期264-267,272,共5页Turbine Technology

基　　金：国家自然科学基金资助项目(51776151)。

摘　　要：系统深入研究了不同导流段轴向相对位置轮缘密封射流对涡轮级气动性能及下游动叶端壁冷却性能影响规律。通过求解三维RANS方程组和SST湍流模型,计算对比了L_(d)=5mm、L_(d)=11mm以及L_(d)=14mm时3种不同导流段与动叶前缘相对位置、轮缘密封射流对涡轮级气动性能的影响以及对下游动叶端壁气膜保护的效果。研究结果表明:随着导流段与动叶前缘轴向相对距离的增加,涡轮级气动性能提高,同时冷气流可以更加深入到动叶通道内部,从而增加动叶端壁前缘冷却区域的面积。In current paper,the effects of rim seal position on aerodynamic performance of turbine stage and film cooling performance on rotor hub platform were analyzed with axial rim seal.Three-dimensional steady Reynolds-averaged Navier-Stokes(RANS)equations,coupled with a fully-developed Shear Stress Transport(SST)turbulent model were utilized to assess influence of rim seal position on the interaction of the hub leakage flows with the mainstream in the turbine stage and also to examine cooling potential of the hub leakage flows on blade platform.The results showed that with the increase of the distance between rim seal and blade leading edge,the turbine efficiency increased.Meanwhile,the purge flow could go deeply into rotor blade passage and thereby increase the film cooling area of rotor hub platform.

关 键 词：涡轮级 轮缘密封 气动性能 冷却特性 数值模拟 

分 类 号：TK472[动力工程及工程热物理—动力机械及工程]