一种基于发动机喘振实时模型的主动稳定性控制方法  

Active stability control method for turbofan engine based on post-stall model

作　　者：张海波[1] 华伟[1,2] 吴伟超[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国航空工业集团公司中航工业航空动力控制系统研究所,江苏无锡214063

出　　处：《航空动力学报》2013年第5期1150-1158,共9页Journal of Aerospace Power

基　　金：航空科学基金(2010ZB52011)

摘　　要：提出了涡扇发动机喘振实时模型建立方法,该模型考虑了发动机容腔的容积动力学效应,风扇、压气机的失速区特性,燃烧室的熄火特性,同时建立了发动机进口总温畸变、总压畸变及组合畸变模型;提出了一种基于压力相关度测量的发动机主动稳定性控制技术,通过测量压气机转子叶片尖端区域的压力相关度,得到相关度值穿越阈值的次数,根据穿越阈值次数与喘振裕度值固有的特性关系,得到压气机的喘振裕度,进而通过鲁棒控制方法设计了主动稳定性控制律,并进行了仿真研究,结果表明:相比于常规控制,基于压力相关度测量主动稳定性控制可以实现发动机过渡态过程中压缩系统不进喘,明显提高了发动机过渡态的动态性能.A method to set up turbofan engine post-stall model was proposed in consideration of the volume effectiveness,the characteristics of post-stall of the fan and compressor,the combustors with rich fuel and lean fuel characteristics.The models of engine inlet＇s total temperature distortion,total pressure distortion,and the combination of two kinds of distortions were established.The active control method proposed was based on the correlation measure of pressure.Correlation measure threshold crossing events increased in magnitude and number as the compressor approached the limit of stable operation,so the stall margin could be calculated in a real-time manner.The active control mode was established based on robust control design method.At last,the numerical simulations were carried out.The results show that the active control based on the method of correlation measure successfully makes the compressing part of engine do not enter into stall during transient process,highly improving the dynamic response in the whole transient process.

关 键 词：喘振实时模型 主动稳定性控制 失速特性 熄火特性 畸变 压力相关度测量 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]