基于辅助进气门的进气道/发动机一体化稳定性控制研究

Research on Inlet and Engine integrated model stability control Based on Auxiliary door

关键词:  辅助进气门  总压畸变  大机动飞行  喘振裕度  估计模型

Key words:  Auxiliary door  Total pressure distortion  Large maneuvering flight  Surge margin  estimation model.

摘要:

为了实现发动机在大机动飞行时高品质稳定运行,提出了一种基于辅助进气门调节的进气道/发动机一体化稳定性控制方法。首先,基于某进气道CFD模型,通过飞行条件和辅助进气门开度计算出口性能参数,考虑总压畸变对风扇特性的影响,建立了进气道实时模型和总压畸变模型,并将其与发动机部件级模型匹配,建立进/发一体化模型。其次,为了直接控制发动机安全裕度,选取发动机部分可测参数作为输入,通过非线性拟合方法建立风扇喘振裕度实时估计模型,相比于直接压比控制可以充分发挥发动机的潜能。进/发一体化控制是通过调节辅助进气门开度控制进气道出口总压恢复系数以满足发动机进口截面需求,并基于 鲁棒控制实现对发动机的转速和安全裕度的控制。仿真结果表明,所提出的方法可以实现发动机在大机动飞行过程中安全稳定工作,推力损失不超过2%。

Abstract:

In order to achieve high quality and stable operation of the engine during large maneuvering flight, an integrated stability control method of inlet/engine based on auxiliary door regulation is proposed. Firstly, based on the CFD model of the inlet, the outlet performance parameters are calculated through flight conditions and auxiliary door. Considering the influence of total pressure distortion on fan characteristics, the real-time inlet model and total pressure distortion model are established, which were matched with the engine component level model to establish the integrated inlet/engine model. Secondly, In order to directly control the engine safety margin, a real-time estimation model of fan surge margin is established by using the non-linear fitting method. Compared with the direct pressure ratio control, the potential of the engine can be fully utilized. The control method of the integrated intake/engine is to control the total pressure recovery coefficient of the inlet by adjusting the auxiliary door to meet the demand of the engine inlet section, and to control the engine speed and safety margin based on robust control. The simulation results show that the proposed method can realize the safe and stable operation of the engine in the process of large maneuvering flight, and the thrust loss is less than 2%.