基于定部件效率的航空发动机通用性能仿真系统构建
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摘要
根据飞机设计阶段对航空发动机性能仿真简便、快速和有效的要求,在基于定部件效率的航空发动机性能仿真方法基础上,对航空发动机部件进行通用性建模,并采用面向对象技术构建通用航空发动机性能仿真系统。采用定部件效率模型对航空发动机性能进行仿真,降低了航空发动机性能仿真过程的专业性要求;同时,采用面向对象技术建立通用的航空发动机性能仿真系统,提高了仿真代码的重用性及仿真系统的适用性。利用该仿真系统建立双转子混排涡扇发动机和自由涡轮式单转子涡轮螺旋桨发动机仿真对象模型,并对某型双转子混排涡扇发动机稳态特性进行仿真,验证了仿真系统的有效性。
According to the simple,fast and effective requirements of aeroengine performance simulation in aircraft design stage,the general model of aeroengine components was established on the basis of the performance simulation method based on fixed component efficiency. The general aeroengine performance simulation system was constructed by using object-oriented technology. The performance of aeroengine was simulated by the fixed component efficiency model,which reduced the professional requirement of the aeroengine performance simulation process. At the same time,the general aeroengine performance simulation system was established by using objectoriented technology,which improved the reusability of simulation code and the applicability of simulation system. By using the simulation system,the simulation object models of the two-spool mixed flow turbofan engine and the free turbine one-spool turboprop engine were established,and the steady state characteristics of a two-spool turbofan engine were simulated. The effectiveness of the simulation system was verified.
According to the simple,fast and effective requirements of aeroengine performance simulation in aircraft design stage,the general model of aeroengine components was established on the basis of the performance simulation method based on fixed component efficiency. The general aeroengine performance simulation system was constructed by using object-oriented technology. The performance of aeroengine was simulated by the fixed component efficiency model,which reduced the professional requirement of the aeroengine performance simulation process. At the same time,the general aeroengine performance simulation system was established by using objectoriented technology,which improved the reusability of simulation code and the applicability of simulation system. By using the simulation system,the simulation object models of the two-spool mixed flow turbofan engine and the free turbine one-spool turboprop engine were established,and the steady state characteristics of a two-spool turbofan engine were simulated. The effectiveness of the simulation system was verified.
引文
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[2]Visser W P J.Generic analysis methods for gas turbine engine performance:The development of the gas turbine simulation program GSP[D].The Netherland:Technische Universiteit Delft,2015.
[3]Joachim Kurzke.Gas Turb 13 user′s manual[M].Germany:MTUAero Engines,2017:2-31.
[4]Visser W P J,Broomhead M J.GSP.A generic object-oriented gas turbine simulation environment[R].NLR-TP-2000-267.
[5]Joachim Kurzke.How to creat a performance model of a gas turbine from a limited amount of information[R].ASME-GT-2005-68536.
[6]张晓博,王占学,蔡元虎.面向对象的航空发动机性能仿真系统研究[J].机械设计与制造,2010(11):133-135.ZHANG Xiaobo,WANG Zhangxue,CAI Yuanhu.A study of object oriented aero-engine performance simulation system[J].Machinery Design&Manufacture,2010(11):133-135.(in Chinese)
[7]骆广琦,刘琨.李游,等.面向对象的航空发动机性能仿真系统框架设计[J].空军工程大学学报,2013,14(4):1-4.LUO Guangqi,LIU Kun,LI You,et al.A study of object-oriented approach to aero-engine performance simulation framework[J].Journal of Air Force Engineering University,2013,14(4):1-4.(in Chinese)
[8]胡伟波,程邦勤,陈志敏,等.面向对象的通用航空发动机建模技术研究[J].航空动力学报,2015,30(10):2539-2545.HU Weibo,CHENG Bangqin,CHEN Zhimin,et al.Research of object-oriented general aero-engine modeling techniques[J].Journal of Aerospace Power,2015,30(10):2539-2545.(in Chinese)
[9]唐海龙,张津.面向对象的航空发动机性能仿真程序设计方法研究[J].航空动力学报,1999,14(4):421-424.TANG Hailong,ZHANG Jin.A study of object-oriented approach for aeroengine performance simulation[J].Journal of Aerospace Power,1999,14(4):421-424.(in Chinese)
[10]徐鲁兵,潘宏亮,周鹏.基于面向对象技术的航空发动机性能仿真框架设计[J].测控技术,2006,26(4):83-86.XU Lubing,PAN Hongliang,ZHOU Peng.Design of a aeroengine peroformance simulation framwork based on object-oriented technique[J].Measurement and Control Technology,2006,26(4):83-86.(in Chinese)
[11]窦建平,黄金泉,周文祥.基于UML的航空发动机仿真建模研究[J].航空动力学报,2005,20(4):684-688.DOU Jianping,HUANG Jinquan,ZHOU Wenxiang.Researching of aeroengine modeling based on UML[J].Journal of Aerospace Power,2005,20(4):684-688.(in Chinese)
[12]刘慧,刘永文.基于通用级特性图的压气机特性计算方法[J].能源技术,2008,29(2):72-78.LIU Hui,LIU Yongwen.Performance calculation of axial flow compressor with generalized stage characteristics[J].Enegry Technology,2008,29(2):72-78.(in Chinese)
[13]Mattingly J D,Heise W H,Pratt D T.Aircraft engine design[M].Reston,VA:AIAA Education Series,2002:95-187.
[14]Oates G C.The aerothermodynamics of gas turbine and rocket propulsion[M].3rd ed Reston,VA:AIAA Education Series,1997:301-313.
[15]廉筱纯,吴虎.航空发动机原理[M].西安:西北工业大学出版社,2005:183-187.LIAN Xiaochun,WU Hu.Aviation engine principle[M].Xi′an:Northwestern Polytechnical University Press,2005:183-187.(in Chinese)