Numerical Study on Shock-Induced Combustion of a Blunt Projectile via an Adaptive Mesh Program

doi:10.13675/j.cnki.tjjs.200748

Journal of Propulsion Technology ›› 2021, Vol. 42 ›› Issue (4): 776-785.DOI: 10.13675/j.cnki.tjjs.200748

• Basic Mechanism of Detonation • Previous Articles Next Articles

Numerical Study on Shock-Induced Combustion of a Blunt Projectile via an Adaptive Mesh Program

Science and Technology on Scramjet Laboratory，China Aerodynamics Research and Development Center， Mianyang 621000，China

Online:2021-04-15 Published:2021-04-15

基于自适应网格的钝头体激波诱导燃烧现象数值模拟研究

陈伟强，刘彧，王兰，肖保国

中国空气动力研究与发展中心高超声速冲压发动机技术重点实验室，四川绵阳 621000

作者简介:陈伟强，博士，助理研究员，研究领域为爆震燃烧。E-mail：wqchancn@163.com
基金资助:
国家自然科学基金（11702316；91941301；91841303）；国家重点研发计划项目（2017YFB0202404）；国家科技重大专项（2017-I-0004-0004）。

Abstract

Abstract: Shock-induced combustion of a blunt projectile is a basic problem in detonation research. Numerical simulations were conducted to study the shock-induced combustion phenomenon of a stoichiometric H₂/Air mixture at the flow Mach numbers of 4.79 and 6.46. The block-structured adaptive mesh refinement program AMROC based on the finite volume method was adopted to solve the axisymmetric Euler equations with chemical reaction source terms， and the influence of some important factors such as the form of the MUSCL reconstruction， the slope limiter types， and the chemical reaction mechanisms were investigated. The results show that， based on the mesh adaption flag parameters， the program can realize adaptive mesh refinement efficiently. The comparisons with experimental results show that the accuracy of the unsteady shock-induced combustion simulation depends not only on the chemical reaction mechanism， but also on the form of the limiter. Adopting two different forms of the MUSCL reconstruction format acquires almost the same oscillating frequencies， which is 1.17% and 0.97% different from the result obtained in the experiment， respectively. Numerical study is conducted for comparing the classic Jachimowski mechanism with several newly developed pressure-dependent hydrogen/oxygen reaction mechanisms. It is shown that， in the unsteady shock-induced combustion case at Ma=4.79， the classic Jachimowski mechanism is still the most suitable mechanism to obtain the closest oscillating frequency to the experimental result. While in the steady shock-induced combustion case at Ma=6.46， all of the given mechanisms can give results that are in good agreements with the experiment.

Key words: Adaptive mesh refinement;Shock-induced combustion;Detonation;Slope limiter;Chemical reaction mechanisms

摘要： 钝头体激波诱导燃烧是爆震研究的一个基本问题。针对化学恰当量比的H₂/Air预混气体在Ma=4.79和Ma=6.46时的激波诱导燃烧现象开展数值研究，采用基于有限体积法的块结构自适应网格加密程序AMROC，对带化学反应源项的轴对称Euler方程解耦求解，考察了数值模拟中不同形式的MUSCL重构格式、限制器类型以及化学反应机理等重要因素对模拟结果的影响。结果表明，程序能够根据设定的加密判据较好地实现网格自适应加密，减小总网格量，实现高效数值模拟。与实验数据的对比表明，非定常激波诱导燃烧算例的准确程度不仅取决于化学反应机理，也取决于限制器类型，而采用两种不同形式的MUSCL重构格式获得的振荡频率则几乎一致，与试验结果的误差分别为1.17%和0.97%。模拟对比经典的Jachimowski机理和近年来新发展的几种包含压力相关反应步的氢/氧反应机理，模拟结果表明：对于Ma=4.79时的非定常激波诱导燃烧模拟，经典的Jachimowski机理仍然是能够给出与实验结果最接近的反应机理；而对于Ma=6.46时的定常激波诱导燃烧模拟，几种反应机理均能给出与实验吻合较好的结果。

关键词: 自适应网格加密;激波诱导燃烧;爆震;限制器;化学反应机理

CHEN Wei-qiang, LIU Yu, WANG Lan, XIAO Bao-guo. Numerical Study on Shock-Induced Combustion of a Blunt Projectile via an Adaptive Mesh Program[J]. Journal of Propulsion Technology, 2021, 42(4): 776-785.

陈伟强，刘彧，王兰，肖保国. 基于自适应网格的钝头体激波诱导燃烧现象数值模拟研究[J]. 推进技术, 2021, 42(4): 776-785.

References

[1] Wolanski P. Detonative Propulsion［J］. Proceedings of the Combustion Institute， 2013， 34： 125-158.
[2] 鲁唯，范玮，王可，等. 无阀式煤油脉冲爆震火箭发动机工作循环特性研究［J］. 推进技术， 2018， 39（5）： 971-978.
[3] Lu W， Fan W， Wang K， et al. Operation of A Liquid-Fueled and Valveless Pulse Detonation Rocket Engine at High Frequency［J］. Proceedings of the Combustion Institute， 2017， 36 （2）： 2657-2664.
[4] 夏镇娟，张义宁，马虎，等. 点火位置对圆盘结构下旋转爆震波起爆过程的影响［J］. 推进技术， 2020， DOI： 10.13675/j.cnki.tjjs.200123.
[5] Zhang H， Liu W， Liu S. Effects of Inner Cylinder Length on H₂/Air Rotating Detonation［J］. International Journal of Hydrogen Energy， 2016， 41 （30）： 13281-13293.
[6] Wang Y， Wang J， Li Y， et al. Induction for Multiple Rotating Detonation Waves in the Hydrogen-Oxygen Mixture with Tangential Flow［J］. International Journal of Hydrogen Energy， 2014， 39 （22）： 11792-11797.
[7] 杨鹏飞，牟乾辉，滕宏辉，等. 旋转爆轰波中多波流动模式的数值研究［J］. 推进技术， 2019， 40（2）： 398-406.
[8] Teng H， Ng H D， Li K， et al. Evolution of Cellular Structures on Oblique Detonation Surfaces［J］. Combustion and Flame， 2015， 162 （2）： 470-477.
[9] 韩旭，周进，林志勇，等. 超声速预混气的热射流起爆过程数值模拟［J］. 推进技术， 2012， 33（4）： 650-656.
[10] 滕宏辉，姜宗林. 斜爆轰的多波结构及其稳定性研究进展［J］. 力学进展， 2020， 50（1）.
[11] Teng H， Yang P， Zhang Y， et al. Flow and Combustion Mechanism of Oblique Detonation Engines［J］. Scientia Sinica Physica， Mechanica & Astronomica， 2020， 50 （9）.
[12] Deiterding R. Parallel Adaptive Simulation of Multi-Dimensional Detonation Structures［D］. Cottbus： Brandenburgischen Technischen Universit?t， 2003.
[13] Cai X， Deiterding R， Liang J， et al. Diffusion and Mixing Effects in Hot Jet Initiation and Propagation of Hydrogen Detonations［J］. Journal of Fluid Mechanics， 2018， 836： 324-351.
[14] Cai X， Liang J， Deiterding R， et al. Experimental and Numerical Investigations on Propagating Modes of Detonations： Detonation Wave/Boundary Layer Interaction［J］. Combustion and Flame， 2018， 190： 201-215.
[15] 陈伟强，梁剑寒，林志勇，等. 超声速预混气扩张流道热射流起爆研究［J］. 推进技术， 2015， 36（12）： 1761-1767.
[16] Liu Y， Wang L， Xiao B， et al. Hysteresis Phenomenon of the Oblique Detonation Wave［J］. Combustion and Flame， 2018， 192： 170-179.
[17] Eude Y， Davidenko D， Falempin F， et al. Use of the Adaptive Mesh Refinement for 3D Simulations of a CDWRE （Continuous Detonation Wave Rocket Engine）［R］. AIAA 2011-2236.
[18] Yuan X， Zhou Jin， Lin Z， et al. Numerical Study of Detonation Diffraction Through 90-Degree Curved Channels to Expansion Area［J］. International Journal of Hydrogen Energy， 2017， 42 （10）： 7045-7059.
[19] Lehr H F. Experiments on Shock Induced Combustion［J］. Astronautica Acta， 1972， 17 （4）： 589-597.
[20] 刘瑜. 化学非平衡流的计算方法研究及其在激波诱导燃烧现象模拟中的应用［D］. 长沙：国防科学技术大学， 2008.
[21] 刘世杰，孙明波，林志勇，等. 钝头体激波诱导振荡燃烧现象的数值模拟［J］. 力学学报， 2010， 42（4）： 1-10.
[22] Wilson G J， Sussman M A. Computation of Unsteady Shock-Induced Combustion Using Logarithmic Species Conservation Equations［J］. AIAA Journal， 1993， 31（2）： 294-301.
[23] Hosangadi A， York B J， Sinha N， et al. Progress in Transient Interior Ballistic Flowfield Simulations Using Multi-Dimensional Upwind/Implicit Numerics［R］. AIAA 93-1915.
[24] Choi J Y， Jeung I S， Yoon Y. Computational Fluid Dynamics Algorithms for Unsteady Shock-Induced Combustion， Part I： Validation［J］. AIAA Journal， 2000， 38（7）： 1179-1187.
[25] Yungster S， Radhakrishnan K. A Fully Implicit Time Accurate Method for Hypersonic Combustion： Application to Shock-Induced Combustion Instability［R］. AIAA 94-2965.
[26] Matsuo A， Fujii K， Fujiwara T. Flow Features of Shock-Induced Combustion Around Projectile Traveling at Hypervelocities［J］. AIAA Journal， 1995， 33（6）： 1056-1063.
[27] Stull D R， Prophet H. JANAF Thermodynamic Tables ［R］. NSRDS-NBS 37， 1971.
[28] Keromnes A， Metcalfe W K， Heufer K A， et al. An Experimental and Detailed Chemical Kinetic Modeling Study of Hydrogen and Syngas Mixture Oxidation at Elevated Pressures［J］. Combustion and Flame， 2013， 160： 995-1011.
[29] Smith G P， Tao Y， Wang H. Foundational Fuel Chemistry Model Version 1.0 （FFCM-1）［EB/OL］. http：//web.stanford.edu/group/haiwanglab/FFCM-1/index.html，2016-07-15.
[30] Burke M P， Chaos M， Ju Y， et al. Comprehensive H₂/O₂ Kinetic Model for High-Pressure Combustion［J］. International Journal of Chemical Kinetics， 2012， 44（7）： 445-474.
[31] Hashemi H， Christensen J M， Gersen S， et al. Hydrogen Oxidation at High Pressure and Intermediate Temperatures： Experiments and Kinetic Modeling［J］. Proceedings of the Combustion Institute， 2015， 35（1）： 553-560.
[32] Berger M. Adaptive Mesh Refinement for Hyperbolic Partial Differential Equations［R］. STAN-CS-82-924， 1982.
[33] Grossmann B， Cinnella P. Flux-Split Algorithms for Flows with Non-Equilibrium Chemistry and Vibrational Relaxation［J］. Journal of Computational Physics， 1990， 88： 131-168.
[34] Sanders R， Morano E， Druguet M C. Multidimensional Dissipation for Upwind Schemes： Stability and Applications to Gas Dynamics［J］. Journal of Computational Physics， 1998， 145： 511-537.
[35] Deiterding R. Numerical Simulation of Transient Detonation Structures in H₂-O₂ Mixtures in Smooth Pipe Bends［C］. Poitiers： 21st International Colloquium on the Dynamics of Explosions and Reactive Systems， 2007.
[36] Anderson W K， Thomas J L， Van Leer B. Comparison of Finite Volume Flux Vector Splittings for the Euler equations［J］. AIAA Journal， 1986， 24（9）： 1453-1460.
[37] Fedkiw R P， Aslam T， Merriman B， et al. A Non-Oscillatory Eulerian Approach to Interfaces in Multimaterial Flows （the Ghost Fluid Method）［J］. Journal of Computational Physics， 1999， 152： 457-492.

Numerical Study on Shock-Induced Combustion of a Blunt Projectile via an Adaptive Mesh Program

基于自适应网格的钝头体激波诱导燃烧现象数值模拟研究

PDF

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 0

Recommended Articles

Metrics

Comments