压气机S型过渡段的低速模拟方法研究

Analysis of the Low-Speed Similarity Design Principle for a Compressor S-shaped Duct

针对压气机S型过渡段,利用数值模拟方法,发展了一种低速模拟设计方法,给出了高低速模拟转换过程中应保证的相似准则。计算结果表明:与几何简单放大的低速计算结果相比,低速模拟得到的过渡段内附面层的发展过程与高速原型的结果更加接近,从而也使得过渡段内损失的发展趋势与高速原型更加一致;最终得到的低速模拟的过渡段进出口总口压损失与高速原型的差异由10.9%降低至2.7%。从而证明了本文提出的过渡段低速模拟方法的可靠性,可用于开展过渡段低速大尺寸情况下的实验研究。

A numerical simulation investigation has been carried out to determine the low-speed similarity of the annual S-shaped duct that used to connect the compressor spools of aircraft gas turbine engines.A low-speed modeling method was proposed,and the design criterions that need to be maintained among the low-speed modeling design were analyzed.Compared with the results of the low speed simulation on the proportionally amplified S-duct,both the evolution of the endwall boundary layer and the total pressure loss along the streamwise location of the simulated results on the low-speed modeling S-duct are more coincident with the results of the original high speed case.And the final difference of the total pressure loss between the low-speed modeling S-duct and the original high speed one,i.e.,2.7%,is much lower than the total pressure loss difference between the low-speed proportionally amplified S-duct and the original high speed one,i.e.,10.9%,which can verify the reliability of the low-speed modeling method.Hence,the proposed low-speed modeling method can be used to conduct experimental investigation of the compressor S-shaped Duct in the low-speed and large-scale situation.