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为通过气热耦合优化计算改善叶片表面温度场,提高叶片气动效率,编制了气热耦合气动和冷却结构参数化方法程序及网格自动生成程序,采用该程序对燃气涡轮静叶进行了考虑叶型及冷却结构的气热耦合优化。优化结果表明:对叶型及冷却结构优化后,形成解集中气动效率分别提升0.3%和0.17%,主流流量仅变化0.116%和0.058%,高温函数降低38.55%、51.6%,叶片表面最大温度降低5.6 K、6.9 K,平均温度降低5 K、7 K。通过分析,前缘第一腔高温区雷诺数的增大以及第三腔低速回流区的减小是改善叶片温度场的主要因素;根中截面的型面压差的减小导致横向二次流损失的降低是减小气动损失的主要原因。
In order to improve the aerodynamic efficiency of the blade by optimizing the calculation of the air-heat coupling, the aerodynamic and air-coupled pneumatic and cooling structure parameterization program and the automatic mesh generation program were prepared. The program was used to consider the gas turbine vane Air-Heat Coupling Optimization of Type and Cooling Structures. The optimization results show that the aerodynamic efficiency of solution aerosol increases by 0.3% and 0.17%, the main flow rate only changes by 0.116% and 0.058%, the high temperature function decreases by 38.55% and 51.6%, and the maximum surface temperature decreases 5.6 K, 6.9 K, 5 K, 7 K lower average temperature. Through the analysis, the increase of Reynolds number in the first cavity high temperature zone and the decrease of the third cavity low velocity recirculation zone are the main factors to improve the blade temperature field. The decrease of profile pressure in the root cross section leads to the lateral secondary flow The loss reduction is the main reason to reduce the aerodynamic loss.