某涡轮导向叶片换热实验与计算

针对某涡轮导向叶片，实验测量了光滑叶片表面的压力系数和速比系数，并使用瞬态液晶测量技术获得了叶片全表面传热系数分布.分别使用shear stress transport（SST），k-ω，k-ε和renormalization group（RNG）k-ε四种湍流模型模拟了相同结构尺寸的叶栅通道内的流动与换热，并与实验结果进行对比.结果表明:压力面压力系数沿弧长方向逐渐下降，吸力面上压力系数先快速下降达到最小值后缓慢上升（出现逆压梯度）.叶栅通道和叶片表面附近气流流动结构的复杂性导致叶片表面传热系数分布较为复杂.4种湍流模型对压力系数和速比系数的计算结果相互差别不大，计算数据也比较接近实验值.关于叶片表面传热系数，SST模型计算结果分布规律与实验接近，而其他3种湍流模型都没有能模拟出吸力面边界层分离对换热的影响. 

Heat transfer experiment and computation of a gas turbine vane

The surface pressure coefficient and velocity ratio coefficient were tested on a gas turbine vane,and the surface heat transfer coefficient was measured with transient liquid crystal technique.For the same structure vane cascade,the performances of four turbulence models(SST, k-ω, k-ε and RNG k-ε) were simulated the flow and heat trasfer, and compared data with experimental results.The result shows that, pressure coefficient declined on the pressure side along the acr direction,however, droped quickly to the minimum on the suction side and then slowly increased,which is the adverse pressure gradient. The distribution of heat transfer coefficient is strongly influenced by the complex flow pattern around the blade in the cascade passage.For pressure coefficient and velocity ratio coefficient,the results of four turbulence models have no big difference and are all very close to experimental data.Surface heat transfer coefficient distribution of SST model has similar trend with experimental data,while the other three models cannot simulate the effect of boundary layer separation on the suction side.