摘要
对航空发动机控制系统进行仿真是航空发动机可靠性工程的研究方向之一。本研究针对发动机在加速过程中必须保证发动机不会发生喘振、不出现超温的情况,对加速过程进行了分析。采用部件法建立了分开排气的涡轮风扇发动机加速过程的稳态模型和动态模型。利用Matlab语言及其函数库编写了基于Newton-Raphson的稳态算法,并进行了稳态仿真,得出了高压转速、低压转速、推力等性能参数与供油量之间的关系。研究了迭代法,利用Matlab(Simulink)实现了涡扇发动机的动态仿真,给出了不同加速供油情况下的性能变化情况。最后对3种不同加速时间下的喘振裕度进行了分析,得出了不同加速时间对喘振的影响。
The simulation of aircraft engine control system is one of the aircraft engine reliability engineering research. Because the engine in accelerating the process, must ensure that the engine does not surge, does not appear over-temperature, we analyze the accelerate process. The steady-state and dynamic models for a separate exhaust turbofan engine are presented by utilizing component characteristics. The use of the Matlab language and its libraries compile the Newton-Raphson algorithm based on the steady state, and steady-state simulation, obtain the relationship between a high-pressure speed, low speed, thrust and other performance parameters and fuel supply. Achieve the dynamic simulation of a turbofan engine using Matlab （Simulink） by researching Iterative method, give the performance in the case of accelerated oil change. Finally, by analyzing the surge margin of three different acceleration time, we draw the influence of different acceleration time to surge.
出处
《中国民航大学学报》
CAS
2013年第3期36-39,53,共5页
Journal of Civil Aviation University of China
关键词
涡扇发动机
加速过程
数值仿真
部件法
turbofan engine
acceleration process
numerical calculation
component characteristics
