Supersonic combustion of aviation kerosene is investigated under the flight conditions of Mach number 5 and fuel-air equivalence ratio 0.551.The trajectories of the fuel droplets and the heat/mass transfer between the...Supersonic combustion of aviation kerosene is investigated under the flight conditions of Mach number 5 and fuel-air equivalence ratio 0.551.The trajectories of the fuel droplets and the heat/mass transfer between them are simulated by means of discrete phase model(DPM).The k-ω model is chosen for turbulence closure and the non-premixed probability density function(PDF)approach is used to calculate the turbulence-chemistry interaction.The calculated wall static pressure and the total pressure loss coefficient are very close to the experiment results.The strut and cavity devices significantly increase the combustion efficiency.展开更多
基金Sponsored by the National Natural Science Foundation of China(10702064)
文摘Supersonic combustion of aviation kerosene is investigated under the flight conditions of Mach number 5 and fuel-air equivalence ratio 0.551.The trajectories of the fuel droplets and the heat/mass transfer between them are simulated by means of discrete phase model(DPM).The k-ω model is chosen for turbulence closure and the non-premixed probability density function(PDF)approach is used to calculate the turbulence-chemistry interaction.The calculated wall static pressure and the total pressure loss coefficient are very close to the experiment results.The strut and cavity devices significantly increase the combustion efficiency.
