航空发动机整机二维气动热力数值模拟

Aerothermodynamic Numerical Simulation of Integrated Aero Engine System

研究了用于航空发动机整机数值仿真的含粘性力项的二维欧拉流动模型,进行了整机流场数值仿真。用代数和椭圆形偏微分方程混合方法分别生成叶栅通道和燃烧室内贴体坐标网格;分别针对压气机转子、静子和涡轮叶栅,定义了三种不同损失系数;采用高阶精度Godunov格式和时间推进法,交替使用显/隐格式,收敛速度快,计算准确度高。计算了某双轴涡扇发动机设计点的整机性能与部件性能,计算结果与设计数据相吻合,分析整机仿真计算得出的流场参数分布,可以更好的了解流场细节。数值试验表明,建立的程序可以预测发动机稳态条件下的整机性能以及用于发动机的设计与改进,奠定了二维数值试验台建设的基础。

A two dimensional flow Euler model with viscous force terms was constructed for integrated turbofan engine systems.Grids in the flow passage and combustion chamber were generated by employing algebraic and elliptically partial differential equation composite methods.Three viscous losses coefficients in accordance with compressor rotors,stators and turbine blades were defined separately.Flow calculation from engine inlet to exit was executed using high order Godunov scheme,time matching method and alternatively explicit/imp licit schemes.Convergence was fast and the accuracy was satisfactory.The flow control characteristics and the effects of inner duct exit dimension on overall engine performances were presented by the program.The simulation results show good accuracy compared with test data,which provides the possibility to investigate the flow in details.