全部 标题 作者
关键词 摘要

OALib Journal期刊
ISSN: 2333-9721
费用:99美元

查看量下载量

相关文章

更多...
航空学报  2013 

二元非对称喷管可调方案试验研究

DOI: 10.7527/S1000-6893.2013.0136, PP. 772-778

Keywords: 二元非对称喷管,可调,数值模拟,风洞试验,推力性能

Full-Text   Cite this paper   Add to My Lib

Abstract:

针对某二元非对称喷管提出了两种可调方式(方案A和方案B),开展了不同落压比(NPR)的喷管风洞试验,获得了喷管壁面压力分布和流场纹影。根据风洞试验条件,进行了详细的三维数值模拟研究,并与试验结果进行对比,两者吻合良好,验证了本文所采用的数值模拟方法的可靠性。根据数值模拟与试验结果,得出了两种方案推力性能的差异。其中,方案B(喉道和出口面积均可调节)较方案A(仅喉道面积可调节)面积膨胀比更接近喷管理想膨胀比,因此方案B推力性能较好。在落压比为3.8时,方案B较方案A推力系数提高了8%。

References

[1]  徐惊雷,张艳慧,张堃元,超燃冲压发动机非对称喷管非设计状态性能计算[J].推进技术,第28卷,第3期,2007年6月
[2]  ZHANG Yanhui,XU Jinglei,ZHANG Kunyuan, Numerical simulation of single expansion ramp nozzle for scramjet on the designing point[J], JOURNAL OF PROPULSION TECHNOLOGY,Vol.28,No.3,June 2001(in Chinese)
[3]  张堃元,张荣学,徐辉。非对称大膨胀比喷管研究[J]. 推进技术.Vol.22,No.5,2001年10月.
[4]  ZHANG Kunyuan , ZHANG Rongxue , XU Hui, Investigation of single expansion ramp nozzle[J],JOURNAL OF PROPULSION TECHNOLOGY,Vol.22,No.5,October 2001(in Chinese)
[5]  葛建辉,徐惊雷,王明涛,等.非对称喷管流动分离的预测[J].航空学报, 2012, 33
[6]  Ge Jianhui, Xu Jinglei, Wang Mingtao, et al. The Prediction of Flow Separation in SERN[J]. Acta Aeronautica et Astronautica Sinica,2012, 33(in Chinese)
[7]  Jinglei Xu, Jiang Sha, Kunyuan Zhang, et al. Numerical Study of Improving the Performance of the Overexpanded SERN by Using SJA[R], AIAA 2010-6790
[8]  Karen A. Deere, Scott C. Asbury, Experimental and Computational Investigation of a Translating-Throat,Single-Expansion-Ramp Nozzle[R], NASA/TP-1999-209138
[9]  郝东兴,王占学,下斜板可调的单膨胀斜面喷管型面设计和流场模拟[J],机械设计与制造第12 期,2009 年12 月
[10]  HAO Dongxing,WANG Zhanxue,The design and flow field simulation of single expansion ramp nozzle with variable flaps[J],Machinery Design & Manufacture,No.12,Dec.2009(in Chinese)
[11]  Takayuki Kojima,Hiroaki Kobayashi,Design and Fabrication of Variable Nozzle for Precooled Turbojet Engine[R],AIAA 2009-7312
[12]  Hideyuki TAGUCHI,DESIGN STUDY ON HYPERSONIC ENGINE COMPONENTS FOR TBCC SPACE PLANES[R],AIAA 2003-7006
[13]  Paul A.Bartolotta and Nancy B.Mcnelis,High Speed Turbines:Development of a Turbine Accelerator(RTA)for Space Access[R],AIAA 2003-6943
[14]  Eric Gamble, Dan Haid,IMPROVING OFF-DESIGN NOZZLE PERFORMANCE USING FLUIDIC INJECTION[R], AIAA 2004-1206
[15]  H.Miyagi and H.Miyagawa,Combined Cycle Engine Research in Japanese HYPR Project[R], AIAA 95-2751
[16]  H.Miyagi,H. Miyagawa,Combined Cycle Engine Research in Japanese HYPR Project[R], AIAA 95-2751
[17]  ING CHANG, OVER-UNDER NOZZLE CFD AND COMPARISION WITH DATA[R],AIAA 94-2939
[18]  Jianwei Mo Jinglei Xu,Liuhuan Zhang, Kunyuan Zhang,The Experimental and Numerical Study of the Over-Under TBCC Exhaust System[R], AIAA 2011-2234
[19]  计算方法引用:李 念, 张元, 徐惊雷,二维非对称喷管数值模拟与验证[J],航空动力学报,第19 卷,第6 期,2004 年12 月
[20]  LI Nian, ZHANG Kunyuan, XU Jinglei,Simulation and Experiment Validation of a Two Dimensional Asymmetric Ramp Nozzle,Vol. 19 No. 6,Dec. 2004(in Chinese)

Full-Text

Contact Us

service@oalib.com

QQ:3279437679

WhatsApp +8615387084133