GE90大涵道比涡扇发动机动态性能研究
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摘要
航空发动机数学模型的建立对于发动机控制十分关键,GE90系列发动机作为大涵道比超大推力涡扇发动机的代表,对于国内大推力发动机的研究具有重要意义和参考价值。以GE90-85B型号发动机作为研究对象,选择部件级特性建模方法,建立大涵道比涡扇发动机的稳态及动态模型,研究发动机在加减速过程各参数变化情况以及对性能的影响。结果表明,在高压转子80%转速、燃油流量阶跃增加,和高压转子100%转速、燃油流量阶跃降低的两种情况下,空气流量、油气比、燃烧室出口温度呈现出与燃油流量同增同减的状态;燃油流量阶跃变化时空气流量无法立即阶跃跟随,致使油气比出现超调的情况;加速时考虑高温部件寿命的影响需避免超温,减速需考虑油气比低导致的燃烧室熄火。
The establishment of aero-engine mathematical model is very important for engine control. As the representative of large bypass ratio large turbofan engines,the GE90 series engine is of great significance and reference value for the research of domestic large-thrust engines. Taking the GE90-85 B engine as the research object,the component-level characteristics modeling method is selected to establish the steady-state and dynamic model of the turbofan engine with large bypass ratio. The changes of parameters of the engine during accelerating and decelerating and the influence on the performance are studied. At 80% speed of the high-pressure rotor,the fuel flow increases step by step; at 100% speed of the high-pressure rotor,the fuel flow decreases step by step; in the two cases,air flow,gas-oil ratio,and outlet temperature of combustion chamber increase or decrease at the same time with fuel flow; at the change of fuel flow step change,air flow cannot follow step by step immediately,thus resulting in the oversupply of oil and gas; over-temperature should be avoided with a view to the impact on service life of high-temperature components in acceleration,and flameout of combustion chamber caused by low gas-oil ratio should be taken into consideration in deceleration.
The establishment of aero-engine mathematical model is very important for engine control. As the representative of large bypass ratio large turbofan engines,the GE90 series engine is of great significance and reference value for the research of domestic large-thrust engines. Taking the GE90-85 B engine as the research object,the component-level characteristics modeling method is selected to establish the steady-state and dynamic model of the turbofan engine with large bypass ratio. The changes of parameters of the engine during accelerating and decelerating and the influence on the performance are studied. At 80% speed of the high-pressure rotor,the fuel flow increases step by step; at 100% speed of the high-pressure rotor,the fuel flow decreases step by step; in the two cases,air flow,gas-oil ratio,and outlet temperature of combustion chamber increase or decrease at the same time with fuel flow; at the change of fuel flow step change,air flow cannot follow step by step immediately,thus resulting in the oversupply of oil and gas; over-temperature should be avoided with a view to the impact on service life of high-temperature components in acceleration,and flameout of combustion chamber caused by low gas-oil ratio should be taken into consideration in deceleration.
引文
[1]刘大响.航空发动机技术的发展和建议[J].中国工程科学,1999,1(2):24-29.
[2]姚华.航空发动机全权限数字电子控制系统[M].北京:航空工业出版社,2014:6.
[3]RICHTER H.涡扇发动机先进控制[M].覃道亮,王曦,译.北京:国防工业出版社,2013:8.
[4]翟高兰.航空发动机非线性参数估计方法研究[D].南京:南京航空航天大学,2008.
[5]冯海峰.航空涡轴发动机数学建模方法与控制规律研究[D].西安:西北工业大学,2007.
[6]周文祥.航空发动机及控制系统建模与面向对象的仿真研究[D].南京:南京航空航天大学,2006.
[7]葛海.大涵道比涡轮风扇发动机建模技术研究[D].南京:南京航空航天大学,2013.
[8]李家瑞.航空发动机建模技术研究[D].南京:南京航空航天大学,2005.
[9]李刚团.民用大涵道比涡扇发动机动态性能模拟研究[J].燃气涡轮试验与研究,2011,24(1):8-14,50.
[10]张大义,刘烨辉,梁智超,等.航空发动机双转子系统临界转速求解方法[J].推进技术,2015,36(2):292-298.
[11]赵军,陈必华,唐庆如,等.民航大涵道比涡扇发动机动态性能研究[J].计算机仿真,2017,34(4):77-81,367.
[2]姚华.航空发动机全权限数字电子控制系统[M].北京:航空工业出版社,2014:6.
[3]RICHTER H.涡扇发动机先进控制[M].覃道亮,王曦,译.北京:国防工业出版社,2013:8.
[4]翟高兰.航空发动机非线性参数估计方法研究[D].南京:南京航空航天大学,2008.
[5]冯海峰.航空涡轴发动机数学建模方法与控制规律研究[D].西安:西北工业大学,2007.
[6]周文祥.航空发动机及控制系统建模与面向对象的仿真研究[D].南京:南京航空航天大学,2006.
[7]葛海.大涵道比涡轮风扇发动机建模技术研究[D].南京:南京航空航天大学,2013.
[8]李家瑞.航空发动机建模技术研究[D].南京:南京航空航天大学,2005.
[9]李刚团.民用大涵道比涡扇发动机动态性能模拟研究[J].燃气涡轮试验与研究,2011,24(1):8-14,50.
[10]张大义,刘烨辉,梁智超,等.航空发动机双转子系统临界转速求解方法[J].推进技术,2015,36(2):292-298.
[11]赵军,陈必华,唐庆如,等.民航大涵道比涡扇发动机动态性能研究[J].计算机仿真,2017,34(4):77-81,367.