航天推进技术研究院主办
[1]周思引,聂万胜,车学科.凹腔前后缘圆弧对流场干扰的数值研究[J].火箭推进,2013,39(01):24-28.
ZHOU Si-yin,NIE Wan-sheng,CHE Xue-ke.Numerical study on effect of arc leading edge and trailing edge of cavity on flow field[J].Journal of Rocket Propulsion,2013,39(01):24-28.
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ZHOU Si-yin,NIE Wan-sheng,CHE Xue-ke.Numerical study on effect of arc leading edge and trailing edge of cavity on flow field[J].Journal of Rocket Propulsion,2013,39(01):24-28.
凹腔前后缘圆弧对流场干扰的数值研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
39
期数:
2013年01期
页码:
24-28
栏目:
研究与设计
出版日期:
2013-02-28
- Title:
- Numerical study on effect of arc leading edge and trailing edge of cavity on flow field
- Keywords:
- numerical simulation; leading edge and trailing edge; arc; flow field
- 分类号:
- V439-34
- 文献标志码:
- A
- 摘要:
- 基于两方程k-ω SST模型，对不同半径前后缘圆弧凹腔构型的超声速流场进行了二维仿真，获得了相应的流场特征参数。结果表明，与直角前后缘相比，采用圆弧构型时凹腔后壁的激波得到增强；随着圆弧半径的增加，凹腔内部的速度有所增大，而温度、涡量则呈递减趋势，从稳焰、助燃的角度看，后壁上端压力增大可以促进质量交换，同时降低回流区温度。综合考虑凹腔的稳焰和助燃作用，提出了一个适当的圆弧半径范围。
- Abstract:
- The two-dimensional simulation for the supersonic flow field of concave-cavity architectures with different radius arc leading and trailing edges was carried out based on k-ω SST model. The corresponding flow field feature parameters were obtained. The simulation results show that, compared with the right angle leading and trailing edges, the shock wave was strengthened near the trailing edges when using the arc edges. By contrast, cavities with different arc radius were considered when the velocity, temperature and vorticity were calculated. It demonstrates that, with the increase of arc radius, the velocity inside the cavity increases, and temperature and vorticity magnitudes appears a decline trend. As viewed from flame stabilization and combustion-supporting, the pressure increase at the upper end of back wall can promote the mass exchange and at the same time, can lower the temperature in recirculation zone. A proper limit of the arc radius is proposed in overall consideration of flame stabilization and combustion-supporting effect of concave-cavity.
参考文献/References:
[1]MATHUR T, GRUBER M, JACKSON K, et al. Supersonic combustion experiments with a cavity-based fuel injector[J]. Journal of Propulsion and Power, 2011, 17(1): 146-155.
[2]MATHUR T, LIN K C, KENNEDY P, et al. Liquid JP-7 combustion in a scramjet combustor, AIAA 2000-3581[R]. USA: AIAA, 2001.
[3]BAURLE R A, TAM C J, DASGUPTA S. Analysis of un- steady flows for scramjet applications, AIAA 2000-3617[R]. USA: AIAA, 2000.
[4]GRUBER M R. Fundamental investigations of an integra ted fuel injector/flame-holder concept for supersonic com- bustion, ADA356336[R]. [S.l.]: ADA, 1998.
[5]钟萍, 苏冯念. 超燃冲压发动机发展与地面试验研究综述[J]. 靶场试验与管理, 2003, 7(5): 2-5.
[6]翁世修, 吴振华. 机械制造技术基础[M]. 上海: 上海交通大学出版社, 1999.
[7]SETTLES G S, WILLIANS D R, BACA B K, et al. Reat- tachment of a compressible turbulent free shear layer[J]. AIAA Journal, 1982, 20(1): 60-67.
[8]潘余. 超燃冲压发动机多凹腔燃烧室燃烧与流动过程研究[D]. 长沙: 国防科技大学研究生院, 2007.
[9]吴子牛. 空气动力学[M]. 北京: 清华大学出版社, 2007.
[10]韩省思. 超声速燃烧中湍流模型的研究[D]. 合肥: 中国科学技术大学, 2010.
[11]MENTER F R. Two-equation eddy-viscosity turbulence models for engineering applications[J]. AIAA Journal, 1994, 32(8): 1598-1605.
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备注/Memo
收稿日期：2012-05-22；修回日期：2012-08-21 基金项目：国家自然科学基金（11205244） 作者简介：周思引（1988—），男，硕士研究生，研究领域为高超声速推进技术
更新日期/Last Update:
1900-01-01