Effect of strut angle on performance of hydrogen multi-jets inside the cavity at combustion chamber

Mechanism study on drag reduction and thermal protection for the porous opposing jet in hypersonic flow

Investigation on the drag reduction and thermal protection properties of the porous opposing jet in the supersonic flow: A parametric study with constant mass flow rate

Parametric investigation on drag reduction and thermal protection characteristics of the porous opposing jet in the hypersonic flow

Fluid-thermo-structural response of actively cooled scramjet combustor in hypersonic accelerating-cruise flight

Study on the drag and heat reduction performance of porous opposing jet in hypersonic flow

To investigate the impact of combustor width on continuous rotating detonation (CRD) fueled by ethylene and air, a series of 3D simulations are conducted by changing the inner cylinder radius of an annular combustor while retaining the same outer cylinder radius. The results show that the CRD wave propagates more steadily and faster as the combustor width increases. The high-temperature zone at the backward-facing step preheats the propellants and contributes to the steady propagation of the CRD wave in 25- and 30-mm wide combustors. The highest and the lowest velocities are obtained in the 30- and 15-mm wide combustors at, respectively, 1880.27 and 1681.01 m/s. On the other hand, the average thrust decreases as the combustor width increases. The highest thrust is obtained in the 15-mm wide combustor while the lowest is in the 30-mm wide combustor, at 758.06 and 525.93 N, respectively. Nevertheless, the thrust is much more stable in the 25- and 30-mm wide combustors than in the 15- and 20-mm wide combustors.

Wei-jie Fan

Papers

Study on the drag and heat reduction performance of porous opposing jet in hypersonic flow

Numerical study on ethylene-air continuous rotating detonation in annular combustors with different widths

Erratum to: Effects of the geometrical parameters of the injection nozzle on ethylene-air continuous rotating detonation