Insight in the Performance of Scramjet Combustor Based on Orthogonal Experimental Design

Abstract:

A numerical insight was accomplished to optimize the scramjet combustor configuration based on orthogonal experimental design. Parametric modeling of combustor configurations was performed by the orthogonal array with 13 factors at 3 levels. Numerical simulations were proceeded by k-ε standard turbulence model and eddy-dissipation model in the combustion process. The performance indexes of combustion efficiency, total pressure recovery coefficient and thrust gain coefficient were evaluated. Detailed comparison with the effect of the factors on the performance was also carried out to demonstrate the main factors and determine the optimal configuration. The analysis of the extreme differences of the factors indicates that the main factors affecting combustion efficiency were the length of the wedge, the length depth ratio of the cavity, the depth of the cavity, and the length of the expanding section; The main factors affecting total pressure recovery coefficient are the angle of the primary combustor, the length of the expanding section, and the thickness of the strut; The main factors affecting thrust gain coefficient are the thickness of the strut, the length of the expanding section, and the angle of the secondary combustor. Validation of the optimal configuration is then confirmed that its performance is higher than the rest of the configurations, with the combustion efficiency of 0.915 and the total pressure recovery coefficient of 0.486, which are 31.5% and 65.9% higher than the experimental results, respectively.

• Periodical: Advanced Materials Research (Volume 705)
• Pages: 463-467
• DOI: https://doi.org/10.4028/www.scientific.net/AMR.705.463
• Online since: June 2013
• Authors: Wen Qiang Cheng, Jing Yuan Liu, Rakesh Shrestha
• Keywords: Combustion Efficiency, Combustor, Numerical Simulation, Orthogonal Experimental Design, Scramjet, Thrust Gain Coefficient, Total Pressure Recovery Coefficient

References

[1] A.A. Taha, Supersonic combustion and mixing characteristics of hydrocarbon fuels in scramjet engines, Old Dominion University, Norfolk, VA, 2002.

[2] X. Wu, X. Li, M. Ding, W. Liu, Z. Wang, Effects of the configuration and fuel injection on scramjet combustor performance, AIAA-2007-5421 (2007)

[3] R.A. Baurle, D.R. Eklund, Analysis of dual-mode hydrocarbon scramjet operation at mach 4-6.5, Journal of Propulsion and Power. 18 (2002) 990-1002.

DOI: 10.2514/2.6047

[4] L. H. Chen, H.B. Gu, X.Y. Zhang, Experimental study on scramjet with strut/cavity configuration, Journal of Engineering Thermophysics. 28 (2007) 743-751

[5] X. Cao, K. Zhang, X. Fang, Experimental investigation for short isolator with swept ramp under asymmetric incoming flow, Journal of Astronautics. 32 (2011) 629-632

[6] Y. Hu, O. Liu, Y. Cai, Three-dimensional numerical analysis on Supersonic combustion of liquid kerosene, Journal of Combustion Science and Technology. 13 (2007) (In Chinese)

[7] M.J. Olynciw, T.O. Mohieldin, C.R. McClinton and S. Tiwari, Effects of scaling on numerical modeling of a transverse jet into supersonic cross flows, AIAA 99-3368 (1999)

DOI: 10.2514/6.1999-3368

[8] S.A. Rowan, A. Paul, Performance of a scramjet combustor with combined normal and tangential fuel injection, Journal of Propulsion and Power. 22 (2006) 1334-1338.

DOI: 10.2514/1.18744

[9] M.G. Owens, S. Tehranian and C. Segal, Flame holding configurations for combustion in Mach 1.8 of airflow, Journal of Propulsion and Power. 14 (1998) 456-461

DOI: 10.2514/2.5322

[10] J.H. Kim, Y. Yoon, I.S. Jeung, and H. Huh, Numerical study of mixing enhancement by shock waves in model scramjet engine, AIAA Journal. 41 (2003) 1074-1080

DOI: 10.2514/2.2047

[11] S. Akmandor, U. Arkun, Numerical simulation of ramjet and scramjet combustion using two- dimensional Euler equations with finite rate chemistry, ISABE 93-7083 (1993)