基于主动防喘的航空发动机加速控制仿真

Adaptive Acceleration Control for Aero-Engine Based on Active Anti-Surge Control

开展基于主动防喘的航空发动机加速控制仿真研究。在建立航空发动机数学模型的基础上,设计了基本加速率控制、基于主动防喘的加速率控制、基于主动防喘的喘振裕度控制及基于喘振裕度估计的喘振裕度控制等4个发动机加速控制方案。仿真结果表明:①主动防喘控制可以在发动机稳定性恶化的情况下,通过较小的控制输出和性能损失实现无喘加速;②主动防喘控制与直接喘振裕度控制相结合可以简化发动机加速控制器设计,不需要额外的优化过程便能得到较优的加速性能;③主动防喘控制可以降低发动机设计点的喘振裕度,从整体上提高了发动机的性能。

Simulation researches have been carried out on acceleration control for aero-engines based on active anti-surge.Based on established aero-engine mathematic model,four acceleration control schemes have been designed：basic acceleration rate control,acceleration rate control based on active anti-surge,surge margin control based on active anti-surge and surge margin control based on surge margin estimation.The simulation results show that：①Using active anti-surge control,safe acceleration process in aero-engines can be achieved with small control out-put and performance reduction under stability deterioration conditions;②The combination of active anti-surge control and surge margin control will simplify the design process of aero-engine acceleration control plan by avoiding additional optimization procedures;③Using active anti-surge control,overall efficiency and performance of aero-engines can be improved greatly with lower designed surge margin.