动叶顶部间隙结构对涡轮性能影响的数值分析  

Numerical analysis on influence of rotor tip clearance structure on turbine performance

作　　者：王晓锋[1] 李昌奂[1] 韩飞[1] 陈本森[1] 

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2013年第2期24-28,共5页Journal of Rocket Propulsion

基　　金：中国航天科技集团公司支撑项目(2008JY07)

摘　　要：富氧燃气中工作的涡轮动叶顶部间隙较大,导致泄漏损失很大通过对四种不同动叶顶部结构的涡轮级进行流场数值模拟,比较了其对涡轮性能、流场的影响。结果表明,动叶顶部围带与壳体迷宫结构的泄漏量最小,因而效率损失最小。The large rotor tip clearance of the turbine operating in rich-oxygen gas leads to high leakage loss. In order to investigate the effect of rotor tip structure on turbine performance and flow field, numerical simulations of four rotor tip structures in turbine stage are conducted. The results show that the leakage through the tip clearance formed by tip shroud and labyrinth structure is minimal. so is the efficiency loss.

关 键 词：液体火箭发动机 涡轮 顶部间隙 

分 类 号：V434.211[航空宇航科学与技术—航空宇航推进理论与工程]