Please use this identifier to cite or link to this item: http://hdl.handle.net/10397/44118
Title: Combustion of vaporized kerosene in supersonic model combustors with dislocated dual cavities
Authors: Zhang, T
Wang, J
Fan, X
Zhang, P 
Issue Date: 2014
Publisher: American Institute of Aeronautics and Astronautics Inc.
Source: Journal of propulsion and power, 2014, v. 30, no. 5, p. 1152-1160 How to cite?
Journal: Journal of propulsion and power 
Abstract: Supersonic combustion of vaporized kerosene in a Mach 2.5 model combustor with a total temperature of 1500 K and a total pressure of 1.3 MPa was experimentally investigated for an optimal integration of the cavity-based flameholder and the fuel injection scheme. Anovel design of a supersonic model combustor consistingof atwo-staged fuel injection system and dislocated dual cavities was proposed to improve the combustor performance, including the combustion efficiency, flame stabilization, combustor "unstart," and heat release distribution. Specifically, a large number of experiments were performed to systematically investigate the effects of fuel injection distribution, which is controlled by varying the injector spacing and the fuel equivalence ratio, on the static pressure distribution, thrust increment, lean blowoutlimit, wall temperature distribution, and combustor unstart characteristics. The results show that there exists an optimal range of injector spacing to obtain enhanced combustion performance while avoiding the combustion unstart. Furthermore, the equal fuel injection withan overall equivalence ratio of 0.5 for the two injectors was found to result in the optimal static pressure distribution and hence the largest thrust increment.
URI: http://hdl.handle.net/10397/44118
ISSN: 0748-4658
DOI: 10.2514/1.B35096
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