一种简化算法的航空发动机全状态数学模型

通过一种简化的燃气空间模型对某型双转子混排加力涡扇发动机各部件进行了建模和仿真计算,并给出了详细的计算流程以及数学公式.在仿真过程中结合实际工程应用经验,对涡轮处采用一个局部的小循环迭代以减小涡轮部件内燃气空间计算的时间步长,提高计算精度.与其他数值方法相比,该简化算法避免了求解非线性方程组时大范围的循环迭代,提高了全状态数学模型的计算速度.通过仿真结果与发动机实际试车数据的对比,证明该方法有足够的计算精度. 

Full range modeling of aero engine systems based on a simplified algorithm

A simplified gas flow domain model was applied to modeling and simulation of a bypass dual-spool mix flow turbofan engine,and the detailed calculation process and all formulas were presented.According to the engineering experience,a small-scale local iteration was introduced to reduce the time step of calculating the parameters in turbine components and significantly improve the solution.On a comparative basis,this method avoids large-scale iteration for solving non-linear equations,thus ensuring faster calculation of the full range aero-engine simulation program.This method is proved to provide enough calculation accuracy when the simulation results are compared with the test run data of engine.