Mixing and combustion characteristics in a cavity-based supersonic combustor with different injection schemes

Mixing and combustion characteristics in an ethylene fueled cavity-based scramjet combustor with different injection schemes are investigated experimentally and numerically in low equivalence ratio conditions, with inflow conditions of Ma = 2.52, stagnation pressure P0 = 1.65 MPa and stagnation temp...

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Bibliographic Details
Published in:Acta astronautica 2019-06, Vol.159, p.584-592
Main Authors: Song, Xiliang, Wang, Hongbo, Sun, Mingbo, Cai, Zun, Liu, Chaoyang, Yu, Jiangfei
Format: Article
Language:English
Subjects:
Combustion
Combustion chambers
Computer simulation
Equivalence ratio
Flamebase oscillations
Inflow
Injection
Injection schemes
Numerical simulations
Orifices
Shear layers
Stagnation pressure
Stagnation temperature
Supersonic combustion ramjet engines
Supersonic flow
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Summary:Mixing and combustion characteristics in an ethylene fueled cavity-based scramjet combustor with different injection schemes are investigated experimentally and numerically in low equivalence ratio conditions, with inflow conditions of Ma = 2.52, stagnation pressure P0 = 1.65 MPa and stagnation temperature T0 = 1600 K. The wall-pressure distributions obtained by numerical simulations are in fairly good agreement with the experimental data. The numerical results also indicate that multiple-orifice cases have higher mixing efficiencies and combustion efficiencies than single-orifice cases. In addition, it is observed in the experiments that flamebases are not stabilized in a fixed position. In single-orifice cases, the flamebases oscillate dramatically between the cavity leading edge and trailing edge, and the oscillations are similar for different injection pressures. In multiple-orifice cases, the flamebases oscillate slightly in the cavity shear layer just downstream of the leading edge and the amplitudes with lower injection pressure are larger than those with higher injection pressure. •Low equivalence ratio cavity flames in a supersonic flow are studied.•Parallel multiple-orifices injections are compared with single-orifice injections.•Flamebase oscillations with different injection schemes are firstly studied.
ISSN:0094-5765
1879-2030
DOI:10.1016/j.actaastro.2019.02.012