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采用数值计算方法对具有大扩张角中间机匣的某型涡轮低压级子午流道型线进行了改型设计 ,提出了7种型线设计方案 ,并应用N S方程全三维粘性求解程序对 7种方案进行了验算。结果表明 :子午扩张型流道外壁型线的改变 ,对低压导向器出口能量损失的影响是显著的 ,设计气动性能优良的子午扩张型线能明显削弱由于大扩张角引起的气流分离 ,降低涡轮低压级的损失。
A numerical calculation method is used to design the low-pressure stage meridian flow line profile of a turbine with a large expansion angle intermediate receiver. Seven kinds of profile design schemes are proposed. The full three-dimensional viscous solution equation of NS equation The program has been checked. The results show that the change of the outer wall profile of the meridional expansion runner has significant effect on the energy loss at the exit of the low pressure guide. The meridional expansion line with excellent aerodynamic performance can obviously weaken the airflow separation due to the large divergence angle, Low-level loss.