为快速得到轴流压气机气动设计方案，缩短设计周期，发展了一套基于多流线法的准二维快速气动设计方法，开发完成相应的设计程序。该方法使用由简化径向平衡方程推导的多流线法，在一维平均中径法设计的基础上，引入多条流线，求解得到不同径向位置上流场气动参数，无需进行流线反复迭代，并嵌入物性计算软件提高计算精度。通过与叶片造型衔接，得到压气机几何模型后进行三维数值模拟，获取初始设计方案的流场细节。为验证程序和方法的准确性，参照某跨音风扇算例的设计参数，设计并验证了一个单转子压气机的性能，结果表明，设计得到的单转子子午流道几何和性能基本满足轴流压气机初始设计方案要求，多流线方法可以在轴流压气机初始设计阶段更快速、稳定地提供气动设计方案。

In order to rapidly obtain the aerodynamic design scheme of axial compressors and shorten the design cycle, a quasi-two-dimensional rapid aerodynamic design method based on the multi-streamline theory is developed. To do this, the multi-streamline approach is first derived based on the simplified radial equilibrium equation. After multiple streamlines are introduced, it can determine aerodynamic parameters of the flow field at different radial positions based on one-dimensional mean-line design, without the need for repeated streamline iterations. It is embedded in physical property calculation software to improve calculation accuracy. By connecting with the blade design, the geometric model of the compressor is obtained and then subjected to three-dimensional numerical simulation to obtain the flow field details of the initial design scheme. To verify the accuracy of the program and the method, a single rotor compressor was designed and validated based on the design parameters of a transonic fan example. The results showed that the geometry of the designed single rotor meridional flow path and performance characteristic basically met the requirements of the initial design scheme of the axial compressor. The multi streamline method offer an aerodynamic design scheme more rapidly and stably in the initial design stage of the axial compressor.

TK221

航空发动机及燃气轮机基础科学中心项目；国家重大科技专项