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为研究气膜冷却涡轮叶片中叶型与气膜孔参数变化对涡轮静叶性能的影响,利用气膜冷却涡轮多目标优化平台对存在多列气膜孔的静叶进行多目标优化.获得在优化变量允许范围内针对气动效率与传热效果以及高温目标函数的Pareto前沿解集,整体性能得到了提高,不同方案中气动效率最高提升0.35%,叶片表面温度最大下降0.74%,高温函数降低的最大幅值为45.71%.结果表明:气动效率提升的主要原因是后弯角的提升使得叶型和二次流损失下降;接近驻点处前缘气膜孔方向的改变导致的冷气分流是叶片根部和前缘附近压力侧的冷却情况得到改善的主要原因.
In order to study the influence of the parameters of vane type and film hole in the film-cooled turbine blade on the performance of the turbine vane, multi-objective optimization of the vane with multiple gas film holes is carried out by using the multi-objective optimization platform of the film cooling turbine, The overall performance of Pareto front solutions for aerodynamic efficiency and heat transfer and high-temperature target function is improved within the allowable range of variables. The highest aerodynamic efficiency increases 0.35%, the maximum temperature decreases 0.74% and the maximum temperature decreases most And the amplitude is 45.71%. The results show that the main reason for the increase of aerodynamic efficiency is the decrease of the loss of the blade type and the secondary flow due to the increase of the posterior horn angle. The cooling air diversion caused by the change of the leading gas film hole near the stagnation point is the root of the blade And the cooling of the pressure side near the leading edge are the main reasons for improvement.