一种基于发动机喘振实时模型的主动稳定性控制方法

张海波; 华伟; 吴伟超

一种基于发动机喘振实时模型的主动稳定性控制方法

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

基金项目: 航空科学基金(2010ZB52011)

计量
- 文章访问数: 1422
- HTML浏览量: 3
- PDF量: 1470
- 被引次数: 0
出版历程
- 收稿日期: 2012-04-22
- 刊出日期: 2013-05-28

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

1.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
China Aviation Motor Control System Institution, Aviation Industry Corporation of China, Wuxi Jiangsu 214063, China

摘要

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.
- 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
Abstract: 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.
- post-stall model /
- active stability control /
- post-stall characteristic /
- blow out characteristic /
- distortion /
- pressure correlation measure

HTML

参考文献(20)

[1]	Hosny W M,Bitter S J,Steenken W G.Turbofan engine nonrecoverable stall computer-simulation development and validation[R].AIAA 85-1432,1985.
[2]	Chung K,Leamy K R,Collins T P.A turbine engine aerodynamic model for in-stall transient simulation[R].AIAA-85-1429,1985.
[3]	Garg S.NASA Glenn research in controls and diagnostics for intelligent aerospace propulsion systems[R].NASA/TM-2005-214036,2005.
[4]	Nathan G.Intelligent engine systems adaptive control[R].NASA/CR-2008-215240,2008.
[5]	刘大响,叶培良,胡骏,等.航空燃气涡轮发动机稳定性设计与评定技术[M].北京:航空工业出版社,2004.
[6]	Epstein A H,Williams J E F,Greitzer E M,et al.Active suppression of aerodynamic instabilities in turbomachines[J].Journal of Propulsion and Power,1989,5(22):204-211.
[7]	Camp T R,Day I J.A study of spike and modal stall phenomena in a low-speed axial compressor[J].Journal of Turbomachinery,1998,120(3):393-401.
[8]	Hoying D A,Tan C S,Grietzer E M.Role of blade passage flow structures in axial compressor rotating stall inception[R].ASME Paper 98-GT-588,1998.
[9]	Breuer T,Servaty S.Stall inception and surge in high speed compressors[R].AGARD CP-571 26/1-17.0,1996.
[10]	Garnier V H,Epstein A H,Grietzer E M.Rotating waves as a stall inception indication in axial compressors[J].Journal of Turbomachinery,1991,113(2):290-301.
[11]	Litt J S,Simon D L,Garg S,et al.A survey of intelligent control and health management technologies for aircraft propulsion systems[J].Journal of Aerospace Computing Information and Communications,2004,1(12):543-563.
[12]	Inoue M,Kuroumaru M,Iwamoto T,et al.Detection of a rotating stall precursor in isolatated axial flow compressor rotors[J].Journal of Turbomachinery,1991,113(2):281-289.
[13]	Inoue M,Kuroumaru M,Tanino T,et al.Propagation of multiple short-length-scale stall cells in axial compressor rotor[J].Journal of Turbomachinary,2000,122(1):45-54.
[14]	Dhingra M.Compressor stability management[D].Atlanta:University of Georgia,2007.
[15]	Dhingra M,Neumeier Y,Prasad J,et al.A stochastic model for a compressor stability measure[J].Journal of Engineering for Gas Turbines and Power,2007,129(3):730-737.
[16]	LIU Yuan,Dhingra M,Prasad J V R.Benefits of active compressor stability management on turbofan engine operability[R].ASME Paper GT-2008-51307,2008.
[17]	LIU Yuan,Dhingra M,Prasad J V R.Active compressor stability management via a stall margin control mode[J].Journal of Engineering for Gas Turbines and Power,2010,132(5):051602.1-051602.10.
[18]	Christensen D,Cantin P,Gutz D,et al.Development and demonstration of a stability management system for gas turbine engines[J].Journal of Turbomachinery,2008,130(3):031011.1-031011.9.
[19]	杨刚,孙健国.一种不需要迭代的发动机辅助变量建模方法[J].航空动力学报,2003,18(2):289-294. YANG Gang,SUN Jianguo.A non-iterative method of aeroengine modeling using complementary variables[J].Journal of Aerospace Power,2003,18(2):289-294.
[20]	Ko H S,Jatskevich J,Dumont G.An advanced LMI-based-LQR design for voltage control of grid-connected wind farm[J].Electric Power System Research,2008,78(4):539-546.