Abstract
The present work focused on improving the engine performance with different fuel equivalence ratios and fuel injections. A scramjet model with strut/cavity integrated configurations was tested under Mach 5.8 flows. The results showed that the strut may sreve as an effective tool in a kerosene-fueled scramjet. The integration of strut/cavities also had great effect on stablizing the combustion in a wide range of fuel equivalence ratio. The one-sdimensional analysis method was used to analyze the main characteristics of the model. The two-stage fuel injection should have better performance in increasing the chemical reaction rate in the first cavity region.
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References
McClinton C R, Rausch V L, Nguyen L T, et al. Preliminary X-43 flight test results. Acta Astronaut, 2005, 57: 266–276
Smart M K, Hass N E, Paul A. Flight data analysis of the hyshot 2 scramjet flight experiment. AIAA J, 2006, 44: 2366–2375
Bertin J J, Cummings R M. Fifty years of hypersonics: Where we have been, where we are going. Prog Aerosp Sci, 2003, 39: 511–536
Petrova M V, Williams F A. A small detailed chemical-kinetic mechanism for hydrocarbon combustion. Combust Flame, 2006, 144: 526–544
Simmie J M. Detailed chemical kinetic models for the combustion of hydrocarbon fuels. Prog Energ Combust, 2003, 29: 599–634
Vinogradov V A, Kobigsky S A, Petrov M D. Experimental investigation of kerosene fuel combustion in supersonic-flow. J Propul Power, 1995, 11: 130–134
Yu G, Li J G, Chang X Y, et al. Fuel injection and flame stabilization in a liquid-kerosene-fueled supersonic combustor. J Propul Power, 2003, 19: 885–893
Yu G, Li J G, Zhang X Y, et al. Experimental investigation on flameholding mechanism and combustion performance in hydrogen-fueled supersonic combustors. Combust Sci Tech, 2002, 174: 1–27
Ben-Yakar A, Hanson R K. Cavity flame-holders for ignition and flame stabilization in scramjets: An overview. J Propul Power, 2001, 17: 869–877
Gruber M R, Baurle R A, Mathur T, et al. Fundamental studies of cavity-based flameholder concepts for supersonic combustors. J Propul Power, 2001, 17: 146–153
Gruber M R, Donbar J M, Carter C D. Mixing and combustion studies using cavity-based flameholders in a supersonic flow. J Propul Power, 2004, 20: 769–778
Hermanson J C, Papas P, Kay I W. Structure and penetration of a supercritical-fluid jet in supersonic-flow. J Propul Power, 1994, 10: 387–394
Mitani T, Kouchi T. Flame structures and combustion efficiency computed for a Mach 6 scramjet engine. Combust Flame, 2005, 142: 187–196
Kobayashi K, Tomioka S, Kato K, et al. Performance of a dual-mode combustor with multistaged fuel injection. J Propul Power, 2006, 22: 518–526
Tomioka S, Kobayashi K, Kudo K, et al. Performance of supersonic combustors with fuel injection in diverging section. J Propul Power, 2006, 22: 111–119
Billig F S. Research on supersonic combustion. J Propul Power, 1993, 9: 499–514
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Supported by the National Natural Science Foundation of China (Grant Nos. 90305022, 10525212)
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Gu, H., Chen, L. & Chang, X. Experimental investigation on the cavity-based scramjet model. Chin. Sci. Bull. 54, 2794–2799 (2009). https://doi.org/10.1007/s11434-009-0460-4
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DOI: https://doi.org/10.1007/s11434-009-0460-4