一体化加力燃烧室热态流场与特性数值研究

In order to meet the high thrust-to-weight ratio requirements of the new generation of aero-engines，a scheme of integrated afterburner with strut and mixer was proposed. The numerical simulation method was used to compare and analyze the influence of inlet Mach number（0.3~0.45），bypass ratio（0.25~0.37）and different flight heights H（0~20 km）on the combustion flow field and characteristics of the afterburner. The results show that within the range of research parameters，as the inlet Mach number increases，the gas temperature in the recirculation zone and downstream area of the wall stabilizer is affected，the gas temperature in the region gradually increases，the radial temperature non-uniformity along the path gradually decreases，the total pressure loss increases，and the combustion efficiency gradually decreases，but the outlet combustion efficiency is still basically higher than 0.90. With the increase of the inlet bypass ratio，the gas temperature at the downstream of the wall stabilizer and the central cone axis begins to decrease，the total pressure loss of the gas along the path increases，and the combustion efficiency increases. When bypass ratio increases from 0.25 to 0.28，the combustion efficiency increases greatly，and continue to increase the bypass ratio，the combustion efficiency increases less. As the flight altitude increases，the overall combustion efficiency gradually decreases. The combustion efficiency decreases less between 0 km and 11 km flight altitudes，while it decreases significantly at 20 km flight altitude.