航空涡扇发动机偏流板前扩稳控制技术研究

Steady Enhancement Control Technology of Aircraft Turbofan Engine for Surface Takeoff

摘要:

为提升航空涡扇发动机舰面偏流板前起飞时的气动稳定性，提出利用压气机进口温度和总增压比两种方法识别发动机进口温升，进而调节压气机可调叶片角度，以提高舰面起飞时发动机稳定裕度。此外，为改善偏流板前进气畸变环境，提出在主机状态不变前提下直接减小加力供油量，以降低发动机出口排气温度，实现发动机舰面起飞前主动扩稳，仿真结果表明提出的措施有效可行。上述方法和措施，可为舰载战斗机发动机舰面起飞扩稳控制提供参考。

Abstract:

In order to improve the aerodynamic stability of aircraft turbofan engines for surface takeoff, two methods of compressor inlet temperature and total supercharging ratio were proposed to identify engine inlet temperature rise, and then the adjustable blade Angle of the compressor was adjusted to improve the engine stability margin during takeoff. In addition, to improve the intake distortion circumstances, a method was introduced that reducing the he afterburner oil gas ratio directly while the main engine state remains unchanged to reduce the exhaust temperature of the engine outlet. The simulation results show that the measure are effective and feasible. The above methods and measures can provide reference for carrier-based fighter engine stability control.