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选取NASA-Mark Ⅱ跨声速叶片为算例,研究了Transition k-kl-ω转捩模型在内冷叶片气热耦合计算中的应用,探讨了整场耦合与冷却通道内采用对流换热系数准则耦合的差异。结果表明,该转捩模型相比其它全湍流模型能够更准确预测附面层内的层流和转捩状况;由于Transition k-kl-ω转捩模型转捩前期采用层流动能来描述扰动的发展,避免了使用含有来流湍流度的经验公式,引入了“分裂机制”来描述层流与湍流脉动间的相互作用,并且在旁路转捩和自然转捩源项模化中加入了Tollmien-Schlichting波的影响,对强激波后的温度计算相比常用的间歇因子转捩模型与实验值更吻合;换热系数准则耦合用于冷却通道传热计算,避免了冷却通道边界条件带来的误差,计算结果与实验吻合较好,更易于工程应用。
Taking NASA-Mark II transonic blade as an example, the application of Transition k-kl-ω transition model to the calculation of the inner-blade thermal-aerodynamic coupling is studied. The criterion of convective heat transfer in the whole coupling and cooling channels is also discussed Differences in coupling. The results show that the transition model can predict the laminar flow and transition state more accurately than other full turbulence models. Since the Transition k-kl-ω transition model uses laminar flow energy to describe the disturbance Development and avoiding the use of an empirical formula with turbulence, introducing the “split mechanism” to describe the interaction between laminar and turbulent pulsations, and adding in the bypass and natural transition models The effect of Tollmien-Schlichting wave is more consistent with the calculation of the temperature coefficient of shock wave than that of the conventional intermittent factor transition model. The heat transfer coefficient criterion is used to calculate the heat transfer of the cooling channel, which avoids the influence of the cooling channel boundary conditions Bring the error, the calculation result is in good agreement with the experiment, and is easier to be applied in engineering.