This study proposes a 1D meanline program for the modeling of modern transonic axial multistage compressors. In this method, an improved blockage factor model is proposed. Work-done factor that varies with the compressor performance conditions is added in this program, and at the same time a notional blockage factor is kept. The coefficient of deviation angle model is tuned according to experimental data. In addition, two surge methods that originated from different sources are chosen to add in and compare with the new method called mass flow separation method. The salient issues presented here deal first with the construction of the compressor program. Three well-documented National Aerodynamics and Space Administration (NASA) axial transonic compressors are calculated, and the speedlines and aerodynamic parameters are compared with the experimental data to verify the reliability and robustness of the proposed method. Results show that consistent agreement can be obtained with such a performance prediction program. It was also apparent that the two common methods of surge prediction, which rely upon either stage or overall characteristic gradients, gave less agreement than the method called mass flow separation method.

这项研究提出了用于现代跨音速轴向多级压缩机建模的一维平均线程序。在该方法中，提出了一种改进的阻塞因子模型。在此程序中添加了随压缩机性能条件而变化的工作系数，同时还保留了名义上的阻塞系数。根据实验数据对偏角系数模型进行了调整。此外，还选择了两种源自不同来源的喘振方法，并与称为质量流分离方法的新方法进行了比较。这里提出的突出问题首先涉及压缩机程序的构建。计算了三份有据可查的美国国家航空航天局（NASA）轴向跨音速压缩机，将速度线和空气动力学参数与实验数据进行比较，以验证所提方法的可靠性和鲁棒性。结果表明，使用这种性能预测程序可以获得一致的一致性。同样明显的是，依赖于阶段或总体特征梯度的两种常见的喘振预测方法与被称为质量流分离方法的方法相比，一致性较差。