摘要
提出了对大涵道比涡扇发动机涡轮监视温度的容错解析方法,以避免由于涡轮监视温度传感器故障造成的发动机控制降级,或未检测到故障导致发动机超温.解析方法包含两种:一种是基于涡轮排气总温的解析方法作为主解析方法;另一种是基于空气流量模型的解析方法作为余度解析方法,用于在主解析温度与测量温度差异较大时进行比较取真.使用发动机试车数据进行了方法验证,结果显示:主解析方法的稳态计算误差不超过0.33%;余度解析方法的稳态计算误差不超过0.8%.这表明两种解析方法都是有效的,可以用于发动机容错控制.
A turbine monitoring temperature analytic method was proposed for fault tolerance of high-bypass-ratio engine,so as to prevent engine control from degrading caused by turbine monitoring temperature sensor failure or overtemperature caused by undetected sensor failure.The analytic method includes two parts：one analytic method is based on turbine total exhaust temperature which is a main analytic unit;the other is based on air flow model as a redundant unit,which is used when the main analytic temperature differs a lot from the measurement temperature.An experiment on engine trial data was carried out.The results show that the main analytic unit＇s steady state error is less than 0.33%.The redundant unit＇s steady state error is less than 0.8%.Experiment results show these two analytic units are both valid and suitable for engine fault tolerant control.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2014年第11期2780-2784,共5页
Journal of Aerospace Power
关键词
发动机容错控制
涡轮监视温度
容错解析
涡轮排气总温
空气流量模型
engine fault tolerant control
turbine monitoring temperature
fault tolerance analysis
turbine total exhaust temperature
air flow model
