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为改善叶片表面温度场,提高叶片气动效率,对燃气涡轮动叶进行了针对叶型以及冷却结构的气热耦合优化。优化结果表明:对冷却结构以及叶型优化后,叶片表面最高温度降低13.64K,平均温度降低6.46K,尾缝冷气出口温度提升6.81K,尾缝出口马赫数由0.24增大至0.30,高温函数降低85.20%,气动效率提高0.58%。通过分析,对该涡轮动叶,尾缘第三腔冷气流动速度的增大及第三腔叶顶冷气低速漩涡区的缩小是减小叶片表面温度的主要因素;型面压差减小导致横向二次流损失的降低及三个截面马赫数减小导致的激波损失降低是减小气动损失的主要因素。
In order to improve the temperature field of the blade surface and improve the aerodynamic efficiency of the blade, gas-air coupling optimization of the blade and the cooling structure of the gas turbine rotor blade is carried out. The optimization results show that the maximum temperature of the blade surface is reduced by 13.64K, the average temperature is reduced by 6.46K, the tail air outlet temperature is increased by 6.81K and the Mach number at the tail seam is increased from 0.24 to 0.30 after optimized cooling structure and leaf shape. Reduce 85.20%, aerodynamic efficiency increased by 0.58%. The analysis shows that the increase of the flow velocity of the cold air in the third chamber and the reduction of the low velocity swirl zone in the third chamber are the main factors to reduce the blade surface temperature. The reduction of secondary loss and the decrease of shock loss caused by the decrease of Mach number at three sections are the main factors to reduce the aerodynamic loss.