某型飞机/发动机一体化性能计算

钱飞; 宋文艳; 骆广琦

某型飞机/发动机一体化性能计算

1.
西北工业大学动力与能源学院, 西安 71007
2.
空军工程大学工程学院, 西安 710038

计量
- 文章访问数: 1951
- HTML浏览量: 203
- PDF量: 1092
- 被引次数: 0
出版历程
- 收稿日期: 2012-02-28
- 刊出日期: 2013-05-28

Calculation of integrated performance for aircraft/engines

1.
School of Power and Energy, Northwestern Polytechnical University, Xi'an 71007
2.
Engineering Institute, Air Force Engineering University, Xi'an 710038, China

摘要

摘要: 研究了飞机/发动机一体化性能计算模型,并开发了一套相应的可视化计算软件.计算模型包括发动机非安装性能计算模型,进气道、尾喷管/后体特性转换模型,安装性能计算模型以及飞机性能计算模型.根据进气道、尾喷管安装特性法(INSTAL),利用进气道、尾喷管/后体特性转换程序求出实际的进气道、尾喷管安装特性,结合非安装性能计算程序,计算了发动机安装性能,并在此基础上计算了飞机性能.该软件已用于某型飞机的一体化性能计算,使用结果表明:①与经验公式法相比,采用INSTAL所得发动机安装性能估算结果与资料值接近程度普遍提高,最高可提高13%;②该软件计算结果合理,计算所需时间短,计算精度较高.
- 非安装性能 /
- 安装性能 /
- 飞机性能 /
- 进气道、尾喷管安装特性法 /
- 一体化
Abstract: An integrated performance computing model for aircraft/engines was studied,and a visual software based on the model was further developed.The model consisted of engine's uninstalled performance computing model,inlet and nozzle/aftbody performance characteristic transferring model,engine's installed performance computing model and flight performance computing model.Using inlet and nozzle installation methods(INSTAL),the installed engine performance was calculated in conjunction with uninstalled engine performance and installed performance characteristics of the inlet and nozzle/aftbody which had been obtained through inlet and nozzle/aftbody installation transferring program.Based on above study,the aircraft performance was calculated as well.The software was applied to estimate integrated performance of a certain aircraft.The results show: (1) comparing with the empirical formula method, the degree of closeness between the estimation of installed engine performance using INSTAL and the data from designer is increased in general, and it can be increased by 13% in maximum; (2) the calculating results are reasonable with short executing time and high accuracy.
- uninstalled engine performance /
- installed engine performance /
- flight performance /
- INSTAL(inlet and nozzle installation methods) /
- integration

HTML

参考文献(15)

[1]	尤哥夫,塞里万诺夫.飞机与发动机特性匹配[M].北京:国防工业出版社,1989.
[2]	Mattingly J D,Haiser W H,Parret D T.Aircraft engine design[M].Reston,VA,US:AIAA Education Series,2005.
[3]	Raymer D P.Aircraft design:a conceptual approach[M].Reston,VA,US:AIAA Education Series,2005.
[4]	Sobieszczanski-Sobieski J.A system approach to aircraft optimization[R].NASA TM-104074,1991.
[5]	Swavely C E,Soileau J F.Aircraft aftbody/propulsion system integration for low drag[R].AIAA-72-1101,1972.
[6]	Oates G C.Aircraft propulsion systems technology and design[M].Reston,VA,US:AIAA Education Series,1989.
[7]	汪家芸,张津,朱一锟.飞机/发动机一体化评估系统研究[J].航空学报,1992,13(10):517-526. WANG Jiayun,ZHANG Jin,ZHU Yikun.Aircraft/propulsion integrated assessment system[J].Acta Aeronautica et Astronautica Sinica,1992,13(10):517-526.(in Chinese)
[8]	张津,陈大光,汪家芸,等.机动飞机/涡扇发动机设计参数的一体化选择[J].推进技术,1996,17(6):18-23. ZHANG Jin,CHEN Daguang,WANG Jiayun,et al.An integrated selection of design parameters for airplane/engines with high maneuverability[J].Journal of Propulsion Technology,1996,17(6):18-23.(in Chinese)
[9]	陶增元,王如根.飞机推进系统总体设计[M].北京:国防工业出版社,2002.
[10]	骆广琦,桑增产,王如根.航空燃气涡轮发动机数值仿真[M].北京:国防工业出版社,2007.
[11]	Kowalski E J.A computer code for estimating installed performance of aircraft gas turbine engines:Vol Ⅲ library of maps[R].NASA CR159693,1979.
[12]	Kowalski E J.A computer code for estimating installed performance of aircraft gas turbine engines:VolⅠfinal report[R].NASA CR159691,1979.
[13]	刘鹏超,宋文艳,骆广琦.某型飞机发动机的安装推力计算[J].航空工程进展,2010,1(3):268-272. LIU Pengchao,SONG Wenyan,LUO Guangqi.Installed thrust calculation for turbofan engine[J].Advances in Aeronautical Science and Engineering,2010,1(3):268-272.(in Chinese)
[14]	方振平,陈万春,张曙光.航空飞行器飞行动力学[M].北京:北京航空航天大学出版社,2005.
[15]	王占学,乔渭阳,蔡元虎.某型弹用涡喷发动机安装性能分析[J].推进技术,2003,24(1):12-16. WANG Zhanxue,QIAO Weiyang,CAI Yuanhu.Analysis of installation performance of the missile turbojet engine[J].Journal of Propulsion Technology,2003,24(1):12-16.(in Chinese)