Article ID | Journal | Published Year | Pages | File Type |
---|---|---|---|---|
8057604 | Aerospace Science and Technology | 2018 | 9 Pages |
Abstract
Solid-fuel scramjet combustor with cavity faces challenges of ignition and flame holding. In the current study, a novel concept, solid-fuel scramjet combustor with fuel-rich hot gas, is proposed. The Reynolds-average Navier-Stokes (RANS) equations coupled with the SST kâÏ turbulence model and the second-order spatially accurate upwind scheme are employed to calculate its flow field. The feasibility of the solid-fuel scramjet combustor with fuel-rich hot gas is studied based on the validation of numerical method. The comparison of the performance is made between the combustor with fuel-rich gas and the combustor with cavity. Various parameters, namely excess air coefficient of gas generator and mass flow rate of fuel-rich gas, are studied, and their effects on the combustion efficiency, total pressure recovery and fuel regression rate are analyzed. This is the basic study for experiments of a solid-fuel scramjet combustor with fuel-rich hot gas.
Keywords
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Physical Sciences and Engineering
Engineering
Aerospace Engineering
Authors
Xiang Zhao, Zhi-xun Xia, Bing Liu, Zhong Lv, Li-kun Ma,