Numerical Study on Supersonic Combustor with an Allotype Cavity

Abstract:

The three-dimensional coupled explicit Reynolds Averaged Navier–Stokes (RANS) equations and the two equation shear-stress transport k-w (SST k-w) model has been employed to numerically simulate the cold flow field in a special-shaped cavity-based supersonic combustor. In a cross-section shaped rectangular, hypersonic inlet with airflow at Mach 2.0 chamber, shock structures and flow characteristics of a herringbone-shaped boss and a herringbone-shaped cavity models were discussed, respectively. The results indicate: Firstly, according to the similarities of bevel-cutting shock characteristics between the boss case and the cavity case, the boss structure can serve as an ideal alternative model for shear-layer. Secondly, the eddies within cavity are composed of herringbone-spanwise vortexes, columnar vortices in the front and main-spanwise vortexes in the rear, featuring tilting, twisting and stretching. Thirdly, the simulated bottom-flow of cavity is in good agreement with experimental result, while the reverse flow-entrainment resulting from herringbone geometry and pressure gradient. However, the herringbone-shaped cavity has a better performance in fuel-mixing.

• Periodical: Applied Mechanics and Materials (Volume 694)
• Pages: 187-192
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.694.187
• Online since: November 2014
• Authors: Jin Xiang Wu*, Jian Sun, Xiang Gou, Lian Sheng Liu
• Keywords: Bevel-Cutting Shock, Herringbone-Shaped Boss, Herringbone-Shaped Cavity, Vortexes

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