考虑端区黏性和径向掺混的流线曲率通流算法研究

高负荷多级压气机的技术难点之一在于如何快速、完整、准确地获得全工况下叶片前尾缘气动参数分布和整机特性结果,而通流计算凭借速度快、指向性明确的优点,一直是多级压气机设计的核心技术。为了提高通流代码的适用范围和预测精度,推导了统一适用于轴流、斜流、离心压气机的流线曲率方程,引入端区黏性和径向掺混模型,应用Fortran语言针对轴流压气机全新开发了其通流特性计算程序,对NASA Rotor37、Rotor67转叶和GY1-2J压气机进行了计算,计算结果表明:新模型的加入提高了程序的计算精度,初步验证了程序的有效性。并提出提高程序的通用性是今后通流计算的发展方向。

Streamline Curvature Algorithm Considering Viscosity and Radial Mixing on Tip Region

One technical difficulty of high loading multi-stage compressor is how to get the distribution of aerodynamic parameters along blade leading and trailing edge under all operation conditions and the whole engine characteristics quickly, completely and accurately. The through flow calculation is the core technology in multi-stage compressor design based on its quick calculating speed and explicit orientation. In order to improve the applicable scope and accuracy of the code, a uniform streamline curvature equation for both axial and centrifugal compressor was derived. The through flow performance calculation code of axial compressor was newly developed by importing the tip region viscosity and radial nuxing model, and applying the Fortran language. The performance of NASA Rotor 37, Rotor 67 and GY1-2J compressor was calculated, and the results show that calculation precision of the code is improved by the new model, and the effectiveness of the code is validated. To improve the universality of the code is the development direction of through flow calculation in the future.