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.
出处
《火箭推进》
CAS
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)
