摘要
采用气热耦合方法对采用径向内冷方式的MarkII型跨声速高压燃气涡轮金属导叶进行数值模拟,通过分析叶片通道内的传热和流动过程发现叶片表面附面层内流动非常复杂,包含层流流动、转捩和湍流流动状态,所以只有使用转捩模型计算的叶片附面层内流动与实际情况相符,叶片壁面温度和换热系数分布与实验结果吻合的较好,使用其他湍流模型由于不能准确描述附面层内流动而使得计算结果误差相对较大,但是所有的湍流模型都能很好的模拟附面层以外流动.
In order to accurately predict aerodynamics and heat transfer between external hot gas and internal cooling passages as well as conduction within metal blade, numerical analysis using conjugate heat transfer methodology for the MarkII transonic turbine guide vane, which was cooled internally by air flowing through 10 radial round pipes, was carried out. The results show that the flow inside boundary layer is very complex, which includes laminar flow, transition process and turbulent flow. The prediction with M-L （Menter and Langtry） transition model provides the closest agreement with the actual flow conditions inside boundary layer, and the distributions of vane temperature and heat transfer coefficient predicted by this model agree well with the measured experimental data whereas the results with other turbulence models over-predict. However, all turbulence models can well predict aerodynamics of gas outside boundary layer.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2008年第2期201-207,共7页
Journal of Aerospace Power
基金
国家自然科学基金(50476028)
国家自然科学基金(50576017)
关键词
航空、
航天推进系统
气热耦合
高压燃气涡轮
内部冷却
转捩流动
数值模拟
aerospace propulsion pressure turbine guide simulation system
conjugate heat transfer methodology
high vane
internal cooling
transition process
numerical
