温度传感器失效对航空发动机温度限制保护的影响分析

中国民用航空局颁布的《航空发动机适航规定》(CCAR-33R2),其中33.28条款对发动机控制系统做出了系统需容忍"单点故障"的规定.然而,传感器失效在所难免,而限制保护是发动机控制系统的重要组成部分.为保障控制系统安全可靠的运行,提高局方在传感器失效状态下对控制系统适航审查的能力,掌握传感器失效下限制保护的影响,进而为适航审定提供一定技术支持.在传感器失效下,探究了航空发动机限制保护控制系统的影响.利用MATLAB/Simulink平台搭建涡轮温度控制系统,以电流信号表征传感器故障,并针对高压涡轮出口温度(T48)的控制,设计了温度限制保护装置,并设定温度限制进行仿真分析.结果表明:过渡过程中,温度限制保护的两次切换可有效解决系统超调过大的现象,而传感器失效和改变参数的限制值均会对限制保护的切换时刻造成超前或滞后等影响,而对限制时间造成缩短或延长的影响.

Influence Analysis of Aero-engine Temperature Limit Protection under Temperature Sensor Failure

The CCAR-33 Regulation was promulgated by the Civil Aviation Administration, of which the aero-engine control system of the 33.28 clause has stipulated that the system needs to tolerate "single point failure". In order to investigate the impact of aero-engine limit protection control system under sensor failure for providing certain technical support of airworthness certification. We built turbine temperature control system on Matlab/Simulink platform, the current signal was used to characterize as sensor failure, and a device that temperature limit protection was designed for the control of T48, and the temperature limit was set for simulation analysis. The results show that switching twice of limit protection can effectively solve the phenomenon of excessive overshoot of the system during the transition state, and sensor failure and changing of the limit parameters will cause lead or lag of on the switching moment of limit protection. Meanwhile, limit time will happen some impacts such as short or extend.