论文部分内容阅读
针对目前发动机性能仿真中燃气热力性质计算方法适用范围和通用性差的问题,加入一种变成分的求解方法,并利用面向对象技术构建了通用的航空发动机性能仿真系统.建模中考虑了部件特性耦合、引气、冷却和功率提取等影响.同时在程序中加入了一些异常处理机制,以便于快速准确地进行调试,增强系统的可靠性.最后利用该仿真系统进行了某型双转子混排涡扇发动机的稳态特性计算,并与试验数据进行了比较.结果表明采用的变成分法进行发动机性能仿真的推力误差一般不超过3%,耗油率误差不超过2.5%,取得了良好的精度.尤其在高空小马赫数时变成分法的精度高于传统的拟合法.
Aiming at the problem of poor applicability and commonality of calculation method of gas thermal properties in current engine performance simulation, a solution method of variable component is introduced and a common simulation system of aeroengine performance is constructed by using object-oriented technology. The components Characteristics coupling, bleed air, cooling and power extraction, etc. At the same time, some abnormal processing mechanisms are added in the program to facilitate the rapid and accurate debugging and enhance the reliability of the system.Finally, a dual-rotor hybrid The steady-state characteristic of the exhaust-turbofan engine is calculated and compared with the experimental data.The results show that the thrust error of the engine used to simulate the engine performance is not more than 3% and the fuel consumption error is less than 2.5% Good accuracy, especially in high-altitude small Mach number becomes more accurate than the traditional method of fitting.