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Simulation of Two-Dimensional Scramjet Combustor Reacting Flow Field Using Reynolds Averaged Navier-Stokes WENO Solver

Part of: Reaction effects in flows

Published online by Cambridge University Press:  15 October 2015

Juan-Chen Huang ,
Yu-Hsuan Lai ,
Jeng-Shan Guo  and
Jaw-Yen Yang
Juan-Chen Huang
Affiliation:
Department of Merchant Marine, National Taiwan Ocean University, Keelung 20224, Taiwan
Yu-Hsuan Lai
Affiliation:
Department of Merchant Marine, National Taiwan Ocean University, Keelung 20224, Taiwan
Jeng-Shan Guo
Affiliation:
Chung-Shan Institute of Science and Technology, Longtan, Taoyuan, Taiwan
Jaw-Yen Yang*
Affiliation:
Institute of Applied Mechanics, National Taiwan University, Taipei 10764, Taiwan Center for Advanced Study in Theoretical Sciences, National Taiwan University, Taipei 10764, Taiwan
*
*Corresponding author. Email addresses: [email protected] (J.-C. Huang), [email protected] (J.-Y. Yang), [email protected] (Y.-H. Lai), [email protected] (J.-S. Guo)
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Abstract

The non-equilibrium chemical reacting combustion flows of a proposed long slender scramjet system were numerically studied by solving the turbulent Reynolds averaged Navier-Stokes (RANS) equations. The Spalart-Allmaras one equation turbulence model is used which produces better results for near wall and boundary layer flow field problems. The lower-upper symmetric Gauss-Seidel implicit scheme, which enables results converge efficiently under steady state condition, is combined with the weighted essentially non-oscillatory (WENO) scheme to yield an accurate simulation tool for scramjet combustion flow field analysis. Using the WENO schemes high-order accuracy and its non-oscillatory solution at flow discontinuities, better resolution of the hypersonic flow problems involving complex shock-shock/shock-boundary layer interactions inside the flow path, can be achieved. Two types of scramjet combustor with cavity-based and strut-based fuel injector were considered as the testing models. The flow characteristics with and without combustion reactions of the two types combustor model were studied with a transient hydrogen/oxygen combustion model. The detailed results of aerodynamic data are obtained and discussed, moreover, the combustion properties of varying the equivalent ratio of hydrogen, including the concentration of reacting species, hydrogen and oxygen, and the reacting products, water, are demonstrated to study the combustion process and performance of the combustor. The comparisons of flow field structures, pressure on wall and velocity profiles between the experimental data and the solutions of the present algorithms, showed qualitatively as well as the quantitatively in good agreement, and validated the adequacy of the present simulation tool for hypersonic scramjet reacting flow analysis.

Keywords

Scramjet combustionstrut injectorcavity-based injectorWENO schemeReynolds averaged Navier-Stokes equations

MSC classification

Secondary: 76V05: Reaction effects in flows
Type
Research Article
Information
Communications in Computational Physics , Volume 18 , Issue 4 , October 2015 , pp. 1181 - 1210
Copyright
Copyright © Global-Science Press 2015 

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