1+1/2对转涡轮高压动叶顶部间隙流场数值研究  

UNSTEADY NUMERICAL SIMULATION OF SHOCK SYSTEMS IN VANELESS COUNTER-ROTATING TURBINE

作　　者：王会社[1] 张惠[1] 赵庆军[1] 杨科[1] 张仲柱[1] 赵晓路[1] 徐建中[1] 

机构地区：[1]中国科学院工程热物理研究所,北京100080

出　　处：《工程热物理学报》2007年第5期751-754,共4页Journal of Engineering Thermophysics

摘　　要：本文对1+1/2对转涡轮中高压动叶顶部间隙中的流动进行了详细的数值研究。通过分析沿弦向不同位置截面上的相对马赫数、速度矢量及静压等的分布,研究了高压动叶间隙及附近的波系及涡系分布。由于1+1/2对转涡轮高压动叶为缩放型流道,其间隙中出现了明显的超音流动,这与普通涡轮间隙中的流动存在明显不同。A detailed numerical simulation has been carried out to investigate the flow in the tip clearance of the high pressure turbine rotor in a 1＋1/2 counter-rotating turbine. Through analyzing the distributions of relative Mach number, velocity and static pressure etc. on different chordwise sections of the vaneless counter-rotating turbine, the shock systems and vortexes in and near the tip clearance are acquired and analyzed particularly. Because of the convergent-divergent passage of the high pressure turbine rotor, a supersonic flow appeared in its tip clearance, which is different from a conventional turbine.

关 键 词：对转涡轮 间隙 数值模拟 激波 

分 类 号：V235[航空宇航科学与技术—航空宇航推进理论与工程]