燃气轮机火焰筒肋化壁面逆流气膜冷却的数值模拟

Numerical Simulation for Counterflow Convection-Film Cooling of Gas Turbine Combustor Liner with Ribbed Wall

针对燃气轮机火焰筒肋化壁面逆流气膜冷却的问题,建立了火焰筒内壁面冷却传热的流固耦合数学模型.考虑湍流切应力的传播,近壁利用k-ω模型的鲁棒性,捕捉黏性底层的流动.主流区域利用k-ε模型避免k-ω模型对入口湍流参数过于敏感的劣势. SST k-ω模型是用混合函数将k-ω模型和k-ε模型结合互补所取得的更适合本问题的湍流模型.数值分析结果清晰展示了计算域流体的流场、温度场及火焰筒肋化壁面的温度场分布,并与文献中的实验结果符合良好.

To study the cooling structure of gas turbine with counterflow convection-film for combustor liner,a fluid-solid coupling mathematical model of the cooling heat transfer of the combustor liner was established.Considering the propagation of Reynolds stress,the robustness of the k-ωmodel was used to capture the flow of viscous underlying layer in the near wall.The k-εmodel was used in the mainstream areas to avoid the k-ωmodel being too sensitive to inlet turbulence parameters.The SST k-ωmodel was a turbulence model which was more suitable for this study by using a mixture function combined with the k-ωand the k-εmodels.The results provided not only the distribution of flow and temperature fields in the computational domain fluid,but also the temperature distribution of the ribbed walls of the combustor liner.Moreover,these simulation results well agreed with the experimental ones.