摘要
采用数值模拟的方法,研究了跨声速涡轮叶栅中平面叶尖和双肋叶尖泄漏流的气动性能.平面叶尖比双肋叶尖的叶尖间隙内马赫数高,有反射激波结构;双肋叶尖的叶尖间隙内马赫数较低,没有形成明显的反射激波结构.平面叶尖和双肋叶尖的叶尖泄漏流质量流量分别为叶栅进口质量流量的3.87%和3.74%.平面叶尖的气动损失系数为0.079,双肋叶尖的气动损失系数为0.072.研究表明,双肋叶尖的气动性能要好于平面叶尖.
The aerodynamic performance of the tip leakage flow of flat tip and cavity tip was investigated numerically in transonic turbine cascade. The Mach number within the tip gap of flat tip was higher than that of cavity tip. Oblique shock wave structure appeared within the tip gap of flat tip. For cavity tip, the oblique shock wave structure was not obvi ous because of low Mach number within the tip gap. The mass flow ratios of tip leakage flow to the mass flow at the inlet of the cascade for flap tip and cavity tip were 3.87% and 3.74%, respectively. The aerodynamic loss coefficient was 0. 079 for flat tip and 0. 072 for cavity tip. The study shows that the aerodynamic performance of cavity tip is better than that of flat tip.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2013年第10期2316-2325,共10页
Journal of Aerospace Power
基金
航空科学基金(2011ZB71002)
国家自然科学基金(11202008)
关键词
跨声速
气动性能
高压涡轮
叶尖泄漏流
双肋叶尖
平面叶尖
transonic
aerodynamic performance
high pressure turbine
tip leakage flow
cavity tip
flat tip
