Please use this identifier to cite or link to this item: http://hdl.handle.net/10397/44119
Title: Blowout limits of cavity-stabilized flame of supercritical kerosene in supersonic combustors
Authors: Zhang, T
Wang, J
Qi, L
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. 1161-1166 How to cite?
Journal: Journal of propulsion and power 
Abstract: Blowout limits of cavity-stabilized flame of supercritical kerosene were experimentally studiedbyusing Mach 2.5 and 3.0 direct-connect supersonic model combustors operated under various air and fuel conditions. Specifically, the effects of the stagnation temperature and the stagnation pressure on the blowout limits were investigated for supercritical kerosene injected from the wall upstream of a cavity flameholder in a Mach 2.5 combustor. Experiments were performed under the same conditions for supercritical keroseneinjected from the rearpartofthe cavity bottomtostudy the influence of the location of fuel injection. The blowout limits of supercritical kerosene injected from the wall upstream of the cavity were further investigated in a Mach 3.0 combustor. Besides the effects of the stagnation temperature and stagnation pressure, the effect of the divergence angle of the combustor on the lean-fuel blowout limit was studied. Results show that there exist two blowout limits corresponding to the lean- and rich-fuel conditions for a given stagnation temperature. The location of fuel injection has substantial influence on the blowout limits, whereas the influenceof the stagnation pressure and the divergence angle of the combustor can be neglected in the range of interest.
URI: http://hdl.handle.net/10397/44119
ISSN: 0748-4658
DOI: 10.2514/1.B35120
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