基于火焰面/进度变量模型的超声速燃烧IDDES模拟

推进技术 ›› 2015, Vol. 36 ›› Issue (3): 321-327.

• 总体与系统 • 下一篇

基于火焰面/进度变量模型的超声速燃烧IDDES模拟

王浩苏,单繁立,牛健,朴英

清华大学航天航空学院，北京 100084,清华大学航天航空学院，北京 100084,清华大学航天航空学院，北京 100084,清华大学航天航空学院，北京 100084

发布日期:2021-08-15
作者简介:王浩苏(1988—)，男，博士生，研究领域为超声速燃烧数值模拟。

IDDES Simulation of Supersonic Combustion Based on Flamelet/Progress Variable Model

School of Aerospace，Tsinghua University，Beijing 100084，China,School of Aerospace，Tsinghua University，Beijing 100084，China,School of Aerospace，Tsinghua University，Beijing 100084，China and School of Aerospace，Tsinghua University，Beijing 100084，China

Published:2021-08-15

摘要/Abstract

摘要： 为了清晰地描述超声速条件下的复杂流动与燃烧过程，建立了基于IDDES模型和火焰面/进度变量模型的湍流燃烧数值模拟方法，并应用于德国宇航中心(DLR)超燃冲压发动机的数值模拟。计算结果与实验数据符合良好，表明该方法可以较为准确地描述超声速湍流燃烧过程，也验证了经过可压缩性修正的火焰面/进度变量模型适用于超声速燃烧问题的求解。同时，利用k-ω SST模型对同一算例进行了计算，发现其对物理量分布的计算精度要低于IDDES模型，说明湍流输运过程的描述对火焰面/进度变量模型的计算精度有重要影响。

关键词: 超燃冲压发动机；湍流燃烧；火焰面/进度变量模型； IDDES模型

Abstract: In order to clarify complex processes of turbulent combustion in supersonic flows，a method combining IDDES model and flamelet/progress variable model is developed and then applied in the simulation of the German Aerospace Center(DLR)scramjet engine. The results show good agreements with experimental data，indicating that this method is able to predict supersonic turbulent combustion process accurately. The results also suggest that flamelet/progress variable model，with compressibility correction，is applicable in supersonic combustion modeling. As a comparison，k-ω SST model combined with flamelet/progress variable model is applied in the same case. It is found that the application of k-ω SST model leads to larger deviations compared with that of IDDES model，suggesting that the prediction of turbulent transport process has a significant effect on the precision of flamelet/progress variable model.

Key words: Scramjet engine；Turbulent combustion；Flamelet/progress variable model；Improved delayed detached eddy simulation

王浩苏,单繁立,牛健,朴英. 基于火焰面/进度变量模型的超声速燃烧IDDES模拟[J]. 推进技术, 2015, 36(3): 321-327.

WANG Hao-su,SHAN Fan-li,NIU Jian,PIAO Ying. IDDES Simulation of Supersonic Combustion Based on Flamelet/Progress Variable Model[J]. Journal of Propulsion Technology, 2015, 36(3): 321-327.

参考文献

[1] 范周琴. 超声速湍流燃烧火焰面模型判别建模及应用研究[D]. 长沙:国防科学技术大学, 2011.
[2] Gerlinger P. Investigation of an Assumed PDF Approach for Finite-Rate Chemistry[R]. AIAA 2002-0166.
[3] Cao R, Pope S B. Numerical Integration of Stochastic Differential Equations: Weak Second-Order Mid-Point Scheme for Application in the Composition PDF Method [J]. Journal of Computational Physics, 2003, 185(1): 194-212.
[4] Peters N. Laminar Diffusion Flamelet Models in Non-Premixed Turbulent Combustion[J]. Progress in Energy and Combustion Science, 1984, 10(3): 319-339.
[5] Pierce C D. Progress-Variable Approach for Large-Eddy Simulation of Turbulent Combustion[D]. Stanford: Stanford University, 2001.
[6] Pierce C D, Moin P. Progress-Variable Approach for Large-Eddy Simulation of Non-Premixed Turbulent Combustion[J]. Journal of Fluid Mechanics, 2004, 504: 73-97.
[7] Ihme M, Pitsch H. Prediction of Extinction and Reignition in Nonpremixed Turbulent Flames Using a Flamelet/Progress Variable Model 2. Application in LES of Sandia Flames D and E[J]. Combustion and Flame, 2008, 115: 90-107.
[8] Law C K. Combustion Physics[M]. New York: Cambridge University Press, 2006.
[9] Sabel’nikov V, Deshaies B, Da Silva L F F. Revisited Flamelet Model for Nonpremixed Combustion in Supersonic Turbulent Flows[J]. Combustion and Flame, 1998, 114(3-4): 577-584.
[10] Ladeinde F. A Critical Review of Scramjet Combustion Simulation[R]. AIAA 2009-0127.
[11] Oevermann M. Numerical Investigation of Turbulent Hydrogen Combustion in a Scramjet Using Flamelet Modeling[J]. Aerospace Science and Technology, 2000, 4(7): 463-480.
[12] Shur M L, Spalart P R, Strelets M K, et al. A Hybrid RANS-LES Approach with Delayed-DES and Wall-Modelled LES Capabilities[J]. International Journal of Heat and Fluid Flow, 2008, 29(6): 1638-1649.
[13] Menter F R. Two-Equation Eddy-Viscosity Turbulence Models for Engineering Applications[J]. AIAA Journal, 32(8): 1598-1605.
[14] 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, 2009.
[15] Kazolea M, Delis A I, Nikolos I K, et al. An Unstructured Finite Volume Numerical Scheme for Extended 2D Boussinesq-Type Equations[J]. Coastal Engineering, 2012, 69: 42–66.
[16] Liou M S. Ten Years in the Making-AUSM-Family[R].AIAA 2001-2521.
[17] Terrapon V E, Ham F, Pecnik R, et al. A Flamelet-Based Model for Supersonic Combustion[R]. NASA Center for Turbulence Research,Annual Research Briefs, 2009.
[18] Ihme M, See Y C. Prediction of Autoignition in a Lifted Methane/Air Flame Using an Unsteady Flamelet/Progress Variable Model[J]. Combustion and Flame, 2010, 157(10): 1850-1862.
[19] 杨阳, 邢建文, 乐嘉陵, 等. 湍流燃烧模型对氢燃料超燃室流场模拟的影响[J]. 航空动力学报, 2008, 23(4): 605-610.
[20] Choi J Y, Jeung I S, Yoon Y. Computational Fluid Dynamics Algorithms for Unsteady Shock-Induced Combustion, Part 1: Validation[J]. AIAA Journal, 2000, 38(7): 1179-1187.(编辑:张荣莉)　　收稿日期:2014-02-24；修订日期:2014-03-26。作者简介:王浩苏(1988—),男,博士生,研究领域为超声速燃烧数值模拟。E-mail: wanghaosu.max@gmail.com

基于火焰面/进度变量模型的超声速燃烧IDDES模拟

IDDES Simulation of Supersonic Combustion Based on Flamelet/Progress Variable Model

PDF

可视化

被引次数

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 0

编辑推荐

Metrics

本文评价