Full Text:   <300>

Summary:  <215>

CLC number: V22

On-line Access: 2018-06-04

Received: 2017-11-17

Revision Accepted: 2018-03-07

Crosschecked: 2018-05-09

Cited: 0

Clicked: 777

Citations:  Bibtex RefMan EndNote GB/T7714


Wei Huang


-   Go to

Article info.
Open peer comments

Journal of Zhejiang University SCIENCE A 2018 Vol.19 No.6 P.431-451


Mode transition process in a typical strut-based scramjet combustor based on a parametric study

Author(s):  Lei Liao, Li Yan, Wei Huang, Lang-quan Li

Affiliation(s):  Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China

Corresponding email(s):   gladrain2001@163.com

Key Words:  Scramjet, Mode transition, Strut, Cavity, Combustion performance

Lei Liao, Li Yan, Wei Huang, Lang-quan Li. Mode transition process in a typical strut-based scramjet combustor based on a parametric study[J]. Journal of Zhejiang University Science A, 2018, 19(6): 431-451.

@article{title="Mode transition process in a typical strut-based scramjet combustor based on a parametric study",
author="Lei Liao, Li Yan, Wei Huang, Lang-quan Li",
journal="Journal of Zhejiang University Science A",
publisher="Zhejiang University Press & Springer",

%0 Journal Article
%T Mode transition process in a typical strut-based scramjet combustor based on a parametric study
%A Lei Liao
%A Li Yan
%A Wei Huang
%A Lang-quan Li
%J Journal of Zhejiang University SCIENCE A
%V 19
%N 6
%P 431-451
%@ 1673-565X
%D 2018
%I Zhejiang University Press & Springer
%DOI 10.1631/jzus.A1700617

T1 - Mode transition process in a typical strut-based scramjet combustor based on a parametric study
A1 - Lei Liao
A1 - Li Yan
A1 - Wei Huang
A1 - Lang-quan Li
J0 - Journal of Zhejiang University Science A
VL - 19
IS - 6
SP - 431
EP - 451
%@ 1673-565X
Y1 - 2018
PB - Zhejiang University Press & Springer
ER -
DOI - 10.1631/jzus.A1700617

The combustion performance of hydrogen fuel in a scramjet combustor has been a popular focus for scholars all over the world. In this study, the influence of the jet-to-crossflow pressure ratio on combustion performance in a scramjet combustor was investigated numerically, and the influence of a wall-mounted cavity was evaluated. The simulations were conducted using the Reynolds-averaged Navier-Stokes (RANS) equations coupled with the renormalization group (RNG) k-ε turbulence model and the single-step chemical reaction mechanism. This numerical approach was validated by comparing predicted results with published experimental shadowgraphs and velocity and temperature measurements. When the pressure of the wall-injector increases, the performance of the combustor decreases. At the same inflow condition, this may lead to a scram-to-ram mode transition. The cavity adopted in this study would prevent pre-combustion shock waves from pushing out of the isolator and help to stabilize the flow field, but it would decrease the mixing and combustion efficiencies.


目的:超燃冲压发动机燃烧室中氢气的燃烧性能引起了研究者的广泛兴趣. 本文旨在探讨不同压比下超燃冲压发动机燃烧室的燃烧性能以及壁面凹腔的影响,为双模态超燃冲压发动机燃烧室设计提供参考.
创新点:1. 研究压比变化过程中超燃向亚燃的转换过程; 2. 研究壁面凹腔设置对模态转换过程的影响.
结论:1. 壁面喷注压强对流场结构影响很大,特别是对于亚燃到超燃的模态转换过程和燃烧性能,当壁面喷注压强大约为支板喷注压强一半时,效果最好; 2. 壁面凹腔能帮助稳定流场,但也会带来一定的混合效率和燃烧效率损失,同时壁面凹腔能帮助延迟从超燃模态向亚燃模态的转换时间,这也从一定程度上说明带凹腔的燃烧室更加适合于超燃模态.


Darkslateblue:Affiliate; Royal Blue:Author; Turquoise:Article


[1]Cao RF, Chang JT, Tang JF, et al., 2014. Study on combustion mode transition of hydrogen fueled dual-mode scramjet engine based on thermodynamic cycle analysis. International Journal of Hydrogen Energy, 39(36):21251-21258.

[2]Choubey G, Pandey KM, 2016. Investigation on the effects of operating variables on the performance of two-strut scramjet combustor. International Journal of Hydrogen Energy, 41(45):20753-20770.

[3]Choudhuri AR, Gollahalli SR, 2000. Combustion characteristics of hydrogen-hydrocarbon hybrid fuels. International Journal of Hydrogen Energy, 25(5):451-462.

[4]Curran ET, 2001. Scramjet engines: the first forty years. Journal of Propulsion and Power, 17(6):1138-1148.

[5]Fluent, 2006. Fluent 6.3 User’s Guide. Fluent, Inc., Lebanon, USA.

[6]Fureby C, Nordin-Bates K, Petterson K, et al., 2015. A computational study of supersonic combustion in strut injector and hypermixer flow fields. Proceedings of the Combustion Institute, 35(2):2127-2135.

[7]Gang Q, Zhou LY, Qin Z, et al., 2011. Experimental investigation of strut-cavity flameholder technology in liquid hydrocarbon fueled scramjet combustor. Journal of Propulsion Technology, 32:680-683 (in Chinese).

[8]Gruber MR, 2004. Mixing and combustion studies using cavity-based flameholders in a supersonic flow. Journal of Propulsion and Power, 20(5):769-778.

[9]Guerra R, Waidmann W, Laible C, 1991. An experimental investigation of the combustion of a hydrogen jet injected parallel in a supersonic air stream. AIAA 3rd International Aerospace Planes Conference, AIAA Paper 91-5102.

[10]Huang W, 2015. Investigation on the effect of strut configurations and locations on the combustion performance of a typical scramjet combustor. Journal of Mechanical Science and Technology, 29(12):5485-5496.

[11]Huang W, 2016. Transverse jet in supersonic crossflows. Aerospace Science and Technology, 50:183-195.

[12]Huang W, Yan L, 2013. Progress in research on mixing techniques for transverse injection flow fields in supersonic crossflows. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 14(8):554-564.

[13]Huang W, Yan L, 2016. Numerical investigation on the ram-scram transition mechanism in a strut-based dual-mode scramjet combustor. International Journal of Hydrogen Energy, 41(8):4799-4807.

[14]Huang W, Wang ZG, Jin L, et al., 2011a. Effect of cavity location on combustion flow field of integrated hypersonic vehicle in near space. Journal of Visualization, 14(4):339-351.

[15]Huang W, Wang ZG, Pourkashanian M, et al., 2011b. Numerical investigation on the shock wave transition in a three-dimensional scramjet isolator. Acta Astronautica, 68(11-12):1669-1675.

[16]Huang W, Wang ZG, Luo SB, et al., 2011c. Parametric effects on the combustion flow field of a typical strut-based scramjet combustor. Chinese Science Bulletin, 56(35):3871-3877.

[17]Huang W, Pourkashanian M, Ma L, et al., 2012a. Effect of geometric parameters on the drag of the cavity fameholder based on the variance analysis method. Aerospace Science and Technology, 21(1):24-30.

[18]Huang W, Ma L, Pourkashanian M, et al., 2012b. Flow-field analysis of a typical hydrogen-fueled dual-mode scramjet combustor. Journal of Aerospace Engineering, 25(3):336-346.

[19]Huang W, Liu WD, Li SB, et al., 2012c. Influences of the turbulence model and the slot width on the transverse slot injection flow field in supersonic flows. Acta Astronautica, 73:1-9.

[20]Huang W, Wang ZG, Yan L, et al., 2012d. Numerical validation and parametric investigation on the cold flow field of a typical cavity-based scramjet combustor. Acta Astronautica, 80:132-140.

[21]Huang W, Li SB, Yan L, et al., 2013. Performance evaluation and parametric analysis on cantilevered ramp injector in supersonic flows. Acta Astronautica, 84:141-152.

[22]Huang W, Jin L, Yan L, et al., 2014a. Influence of jet-to-crossflow pressure ratio on nonreacting and reacting processes in a scramjet combustor with backward-facing steps. International Journal of Hydrogen Energy, 39: 21242-21250.

[23]Huang W, Yan L, Tan JG, 2014b. Survey on the mode transition technique in combined cycle propulsion systems. Aerospace Science and Technology, 39:685-691.

[24]Huang W, Li SB, Yan L, et al., 2015. Multiobjective design optimization of a cantilevered ramp injector using the surrogate-assisted evolutionary algorithm. Journal of Aerospace Engineering, 28:04014138.

[25]Huang W, Li MH, Yan L, 2016a. Mixing augmentation mechanism induced by the pseudo shock wave in transverse gaseous injection flow fields. International Journal of Hydrogen Energy, 41:10961-10968.

[26]Huang W, Li LQ, Yan L, et al., 2016b. Numerical exploration of mixing and combustion in a dual-mode combustor with backward-facing steps. Acta Astronautica, 127:572-578.

[27]Huang W, Li MH, Ding F, 2016c. Supersonic mixing augmentation mechanism induced by a wall-mounted cavity configuration. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 17(1):45-53.

[28]Kim CH, Jeung IS, Choi B, et al., 2011. Effect of fuel injection location on a plasma jet assisted combustion with a backward-facing step. Proceedings of the Combustion Institute, 33:2375-2382.

[29]Kummitha OR, Pandey KM, Gupta R, 2018. CFD analysis of a scramjet combustor with cavity based flame holders. Acta Astronautica, 144:244-253.

[30]Mahto NK, Choubey G, Suneetha L, et al., 2016. Effect of variation of length-to-depth ratio and Mach number on the performance of a typical double cavity scramjet combustor. Acta Astronautica, 128:540-550.

[31]Micka DJ, Driscoll JF, 2009. Combustion characteristics of a dual-mode scramjet combustor with cavity flameholder. Proceedings of the Combustion Institute, 32(2):2397-2404.

[32]Oevermann M, 2000. Numerical investigation of turbulent hydrogen combustion in a SCRAMJET using flamelet modeling. Aerospace Science Technology, 4(7):463-480.

[33]Ogawa H, 2016. Effects of injection angle and pressure on mixing performance of fuel injection via various geometries for upstream-fuel-injected scramjets. Acta Astronautica, 128:485-498.

[34]Qin J, Bao W, Zhou WX, et al., 2010. Flow and heat transfer characteristics in fuel cooling channels of a recooling cycle. International Journal of Hydrogen Energy, 35(19):10589-10598.

[35]Segal C, 2009. The Scramjet Engine Processes and Characteristics. Cambridge University Press, UK.

[36]Smirnov NN, Nikitin VF, 2014. Modeling and simulation of hydrogen combustion in engines. International Journal of Hydrogen Energy, 39(2):1122-1136.

[37]Smirnov NN, Nikitin VF, Phylippov YG, 2010. Deflagration to detonation transition in gases in tubes with cavities. Journal of Engineering Physics and Thermophysics, 83(6):1287-1316.

[38]Smirnov NN, Betelin VB, Nikitin VF, et al., 2015. Accumulation of errors in numerical simulations of chemically reacting gas dynamics. Acta Astronautica, 117:338-355.

[39]Tian Y, Xiao BG, Zhang SP, et al., 2015. Experimental and computational study on combustion performance of a kerosene fueled dual-mode scramjet engine. Aerospace Science and Technology, 46:451-458.

[40]Turner JC, Smart MK, 2010. Application of inlet injection to a three-dimensional scramjet at Mach 8. AIAA Journal, 48(4):829-838.

[41]Yan L, Liao L, Huang W, et al., 2018. Nonlinear process in the mode transition in typical strut-based and cavity-strut based scramjet combustors. Acta Astronautica, 145:250-262.

[42]Zhang Y, Zhu SH, Chen B, et al., 2016. Hysteresis of mode transition in a dual-struts based scramjet. Acta Astronautica, 128:147-159.

Open peer comments: Debate/Discuss/Question/Opinion


Please provide your name, email address and a comment

Journal of Zhejiang University-SCIENCE, 38 Zheda Road, Hangzhou 310027, China
Tel: +86-571-87952783; E-mail: cjzhang@zju.edu.cn
Copyright © 2000 - Journal of Zhejiang University-SCIENCE