着陆襟翼打开状态下抓斗式反推装置 三维流动数值模拟

刘春阳; 王占学; 王家启; 尹方; 孔德英

着陆襟翼打开状态下抓斗式反推装置三维流动数值模拟

1.
西北工业大学动力与能源学院, 西安 71007
2.
中国航空工业集团公司第一飞机设计研究院,西安 710089

基金项目: 西北工业大学基础研究基金(JC200815); 航空科学基金(2008ZB53012)

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出版历程
- 收稿日期: 2009-11-15
- 修回日期: 2010-05-20
- 刊出日期: 2010-12-28

Numerical simulation on flow field of the clamshell thrust reverser with landing flap deployed

1.
School of Power and Energy, Northwestern Polytechnical University,Xian 71007
2.
The First Aircraft Institute, Aviation Industry Corporation of China,Xian 710089,China

摘要

摘要: 基于求解三维Reynolds-averaged Navier-Stokes方程,数值模拟了着陆襟翼打开状态下抓斗式反推装置工作时流场分布特性.网格采用非结构化四面体与六面体混合分区生成技术,湍流模型选用Spalart-Allmaras模型.结果表明,在计算滑跑速度范围内,反向排气流不会被进气道重新吸入;高温反向排气流会冲击到飞机吊挂及部分机翼,需引起注意;随着滑跑速度的降低,反向排气流侧向影响范围急剧增大,若机翼后掠角较大,则反向排气流容易被相邻发动机再次吸入,引起进气畸变;当滑跑速度降低到34m/s时,反向流开始吹向地面,可能会卷起地面颗粒物并且被进气道吸入;随着滑跑速度的降低,反推力减小.
- 着陆襟翼 /
- 抓斗式反推装置 /
- 反向排气流 /
- 进气畸变 /
- 反推力
Abstract: Computational fluid dynamics (CFD) technology was used to investigate the flow field distribution characteristic of a clamshell thrust reverser with landing flap deployed.The computational grid was generated with unstructured tetrahedron and hexahedron meshes,and Spalart-Allmaras (S-A) turbulent model based on solving Reynolds-averaged Navier-Stokes (RANS) equations was adopted.The results show that,in the range of landing speed,the hot reverse exhaust flow from the clamshell thrust reverser is not re-injected into the engine inlet,but it impinges on part of the aerofoil and pylon.As landing speed decreases,the hot reverse exhaust flow spreads forward and laterally deeper,so it may be re-injected by near engine inlet if the aerofoil sweepback is large enough,resulting possibly in inlet distortion.When landing speed decreases down to 34m/s,the hot reverse exhaust flow starts to impinge on the ground,which may wind up some dross to the inlet.At last,the reverse thrust decreases as landing speed decreases.
- landing flap /
- clamshell thrust reverser /
- reverse exhaust flow /

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参考文献(12)

[1]	Obye R C,Hakim A D.Axisymmetric approach and landing thrust reverser concepts:hot flow test results .AIAA-84-1176,1984.
[2]	靳宝林,刑伟红,刘殿春.飞机/发动机推进系统反推力装置[J].航空发动机,2004,30(3):48-52. JIN Baolin.XING Weihong.LIU Dianchun.Thrust reversers of aircraft/engine propulsion system[J].Aeroengine,2004,30(3):48-52.(in Chinese)
[3]	邵万仁,叶留增,沈锡钢,等.反推力装置关键技术及技术途径初步探讨 //大型飞机关键技术高层论坛暨中国航空学会2007年学术年会论文集.深圳:中国航空学会,2007.
[4]	王玉新.飞机发动机反推力装置的创新设计 //大型飞机关键技术高层论坛暨中国航空学会2007年学术年会论文集.深圳:中国航空学会,2007.
[5]	王占学,张晨,刘春阳.抓斗式反推装置打开时反推性能参数计算[J].航空动力学报,2009,24(10):2157-2162. WANG Zhanxue,ZHANG Chen,LIU Chunyang.Mathematical model for calculating effects of target type thrust reverser on turbofan engine performance[J].Journal of Aerospace Power,2009,24(10):2157-2162.(in Chinese)
[6]	Andrade F O,Ferreira S B.Study of the influence of aircraft geometry on the computed flowfield during thrust reversers operation .AIAA 2006-0367,2006.
[7]	Strash D J,Summa J M,Frank J H,et al.Aerodynamic analysis of an installed thrust reverser .AIAA 1997-3153,1997.
[8]	王占学,黄杰.喷管/飞行器后体一体化数值模拟[J].西北工业大学学报,2000,18(4):587-590. WANG Zhanxue,HUANG Jie.Numerical simulation of integration of nozzle/vehicle-afterbody[J].Journal of Northwestern Polytechnical University,2000,18(4):587-590.(in Chinese)
[9]	Yao H,Raghunathan S,Cooper R K,et al.Numerical simulation on flow field of the nature blockage thrust reverser .AIAA 2005-0631,2005.
[10]	Spalart P R,Allmaras S R.A one-equation turbulence model for aerodynamic flows .AIAA 1992-0439,1992.
[11]	左志成,钱瑞战.民机反推力装置对发动机进气口流场畸变影响数值模拟研究[J].飞机设计,2007,27(5):60-64. ZUO Zhicheng,QIAN Ruizhan.Numerical simulation investigation of effect of thrust-reverser operating on engine inlet flow distortion for civilian transport[J].Aircraft Design,2007,27(5):60-64.(in Chinese)
[12]	刘大响,叶培梁,胡俊,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.