首页|Effect of kerosene injection states on mixing and combustion characteristics in a cavity-based supersonic combustor

Effect of kerosene injection states on mixing and combustion characteristics in a cavity-based supersonic combustor

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It has been found that the static pressure distribution along the axial direction of liquid kerosene is lower than that of the gaseous kerosene under the same flow condition and overall equivalent ratio from previous studies.To further investigate this phenomenon,a compressible two-phase parallel simulation method is utilized to analyze the mixing and combustion character-istics of gaseous and liquid kerosene jets in a cavity-based supersonic combustor.The numerical results are consistent with the experiments and demonstrate that gaseous injection leads to a cavity shear layer that dives deeper into the cavity,forming two recirculation zones in the front and rear of the cavity.In contrast,the cavity shear layer is closer to the mainstream during liquid injection,and only a large recirculation zone is formed in the rear of the cavity.As a result of the cavity shear layer and the recirculating flow,the fuel vapor of gaseous injection accumulates in the front of the cavity,while for the liquid injection,the fuel vapor disperses in the cavity,cavity shear layer,and the region above,and the rear of the cavity has a higher fuel vapor concentration than the front.This unique fuel distribution causes the combustion area to be concentrated in the cavity during the gaseous injection but dispersed inside and downstream of the cavity during the liquid injection.As a result,forming a thermal throat under the same conditions is more challenging during liquid injection,and the generated static pressure distribution is lower than that during the gaseous injection.

Gaseous injectionLiquid injectionMixing processCombustionSupersonic flow

Xu LIU、Peibo LI、Fei LI、Hongbo WANG、Mingbo SUN、Chao WANG、Yixin YANG、Dapeng XIONG、Yanan WANG

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Science and Technology on Scramjet Laboratory,College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China

国家自然科学基金国家自然科学基金国家自然科学基金国家自然科学基金

9225220611925207T222100212102472

2024

中国航空学报(英文版)
中国航空学会

中国航空学报(英文版)

CSTPCDEI
影响因子:0.847
ISSN:1000-9361
年,卷(期):2024.37(4)
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