流路参数对收扩喷管内流特性影响的数值研究

邵万仁

流路参数对收扩喷管内流特性影响的数值研究

邵万仁

北京航空航天大学能源与动力工程学院,北京 100191;中国航空工业集团公司沈阳发动机设计研究所,沈阳 110015

计量
- 文章访问数: 1639
- HTML浏览量: 66
- PDF量: 524
- 被引次数: 0
出版历程
- 收稿日期: 2012-05-18
- 刊出日期: 2012-10-28

Computation of effect of different nozzle parameters on internal performance of convergent-divergent axisymmetric nozzle

SHAO Wan-ren

School of Jet Propulsion,Beijing University of Aeronautics and Astronautics, Beijing 100191,China;Shenyang Aeroengine Research Institute, Aviation Industry Corporation of China,Shenyang 110015,China

摘要

摘要: 用经冷态缩比模型内流特性试验验证的三维有黏定常程序,对某轴对称收扩喷管进行了收敛调节片长度、喉道圆弧半径、扩张调节片长度和喷管扩张面积比对内流特性影响规律的计算研究.研究结果表明:收敛调节片长度和喉道圆弧半径主要是对收敛半角较大工况的流量系数有一定的影响,可以在确保收敛半角小于45°前提下适当减小收敛调节片长度;扩张调节片长度和喷管扩张面积比主要是对推力系数影响较大,扩张调节片长度和喷管扩张面积比的选择应在确保扩张半角小于16°前提下力争气流完全膨胀.
- 航空、航天推进系统 /
- 轴对称收扩喷管 /
- 内流特性 /
- 流路参数 /
- 数值模拟
Abstract: The numerical simulation on convergent flap length, nozzle throat arc radius,divergent flap length and nozzle expansion ratio affecting the internal performance of an axisymmetric convergent-divergent nozzle was conducted by applying a three-dimensional(3-D) viscous flow program that the results of the simulation were compared with that of the scale model experiments.The investigation shows that:convergent flap length and nozzle throat arc radius have some effects on the flow coefficient under the condition of a big convergent half angle,and convergent flap length can be properly reduced on condition that convergent half angle is less than 45 degrees;divergent flap length and nozzle expansion ratio have big effect on the thrust coefficient,and selected divergent flap length and nozzle expansion ratio shall work hard for fully expanded nozzle flow on condition that divergent half angle is less than 16 degrees.
- aerospace propulsion system /
- axisymmetric convergent-divergent nozzle /
- internal performance /
- nozzle parameter /
- numerical simulation

HTML

参考文献(16)

[1]	Чепкин В М.Теория,расчет и проектирование авиационных двигателей и энергетических установок[M]. Москва:Издательство МАИ,2003.
[2]	Oates G C.飞机推进系统技术与设计[M].陈大光,张津,朱之丽,等,译.北京:航空工业出版社,1992.
[3]	刘大响.航空发动机设计手册:第7册[M].北京:航空工业出版社,2000.
[4]	Carson G T,Capone F J.Static internal performance of an axisymmetric nozzle with multiaxis thrust2vectoring capability .NASA Technical Memorandum 4237,1991.
[5]	金捷,赵景芸,张明恒,等.轴对称矢量喷管壁面静压分布的试验研究[J].航空动力学报,2000,15(3):314-316. JIN Jie,ZHAO Jingyun,ZHANG Mingheng,et al.Experimental investigation on AVEN wall static pressure distributions[J].Journal of Aerospace Power,2000,15(3):314-316.(in Chinese)
[6]	Burnes R,Carpenter T,Gerhardt J.Internal pressure distribution of a 20 degree thrust vectored axisymmetric nozzle .AIAA-2001-3887,2001.
[7]	金捷,赵景芸,张明恒,等.轴对称矢量喷管内流特性的模型试验[J].推进技术,2005,26(2):144-146. JIN Jie,ZHAO Jingyun,ZHANG Mingheng,et al.Experimental investigation of static internal performance for an axisymmetric vectoring thrust nozzle[J].Journal of Propulsion Technology,2005,26(2):144-146.(in Chinese)
[8]	Matesanz A,Velazquez A,Rodriguez M.Mach disk simulation in jets from convergent-divergent axisymmetric and thrust-vectoring nozzkes .AIAA-94-2328,1994.
[9]	Teryn D, Nicholas G,Dennis Y,et al.Computations of internal and external axisymmetric nozzkes aerodynamics at transonic speeds .NASA/TM-2003-212731,2003.
[10]	Teryn D,Nicholas G,Dennis Y,et al.Computational study of axisymmetric off-design nozzke flows .NASA/TM-2003-212876,2003.
[11]	Matesanz A,Velazquez A,Rodriguez M.Numerical study on some fluid dynamics aspects of axisymmetric thrust vectoring nozzkes .AIAA-94-3365,1994.
[12]	罗静,王强,额日其太.轴对称矢量喷管内流特性的不同湍流模型计算[J].航空动力学报,2003,24(4):327-340. LUO Jing,WANG Qiang,Eriqitai.Computation for the effect of turbulence models on internal performance for axisymmetric vectoring exhaust nozzles[J].Journal of Aerospace Power,2003,24(4):327-340.(in Chinese)
[13]	马会民,樊思齐,卢燕.分离流动对矢量喷管性能的影响[J].推进技术,2003,24(5):421-424. MA Huimin,FAN Siqi,LU Yan.Effects of flow separation on the performance of thrust-vectoring nozzle[J].Journal of Propulsion Technology,2003,24(5):421-424.(in Chinese)
[14]	张群锋,吕志咏.轴对称矢量喷管外流对内流干扰研究[J].航空动力学报,2003,18(3):322-326. ZHANG Qunfeng,LV Zhiyong.Effect of outer flow on internal performance for an axisymmetric vectoring nozzle[J].Journal of Aerospace Power,2003,18(3):322-326.(in Chinese)
[15]	邵万仁.基于数值模拟的轴对称矢量喷管内流特性研究[J].航空动力学报,2008,23(5):822-829. SHAO Wanren.Study of internal performance for an axisymmetric vectoring exhaust nozzle using numerical simulation[J].Journal of Aerospace Power,2008,23(5):822-829.(in Chinese)
[16]	金捷,王强.轴对称矢量喷管内流特性的数值模拟研究[J].航空动力学报,2001,16(4):394-397. JIN Jie,WANG Qiang.Numerical simulation of static internal performance for an axisymmetric vector -ing exhaust nozzle (AVEN)[J].Journal of Aerospace Power,2001,16(4):394-397.(in Chinese)