为解决油气比变化时航空发动机燃烧稳定性问题，针对某型航空发动机短环形燃烧室在不同油气比下进行试验研究，利用PIV测速仪对不同油气比下燃烧室内液雾燃烧流场进行测量；利用温度传感器对燃烧室出口温度分布进行测量，分析了油气比对燃烧室内燃烧流场和出口温度分布影响规律。研究结果表明：随着油气比的增加，燃烧室回流区长度缩短，回流区涡心分别向火焰筒上下壁面靠拢，涡心距离增大；燃烧室内气流紊流度增大，速度轴向分量U rms增大；燃烧室出口各点的温度T相应升高。油气比靠近熄火边界时，燃烧流场稳定性减弱。

In order to solve the problem of combustion stability of aeroengine when the oilgas ratio changes, the short annular combustion chamber of a certain aeroengine under different oilgas ratios were studied experimentally. The PIV velocimeter was used to measure the liquid mist combustion flow field in the combustion chamber under different oilgas ratios; temperature sensors were used to measure the temperature distribution at the combustion chamber outlet, and the influence of the oilgas ratio on the combustion flow field and outlet temperature distribution in the combustion chamber was analyzed. The results show that with the increase of oilgas ratio, the length of the reflux zone of the combustion chamber is shortened, the vortex center of the reflux zone is closer to the upper and lower walls of the flame tube, and the vortex center distance increases; the turbulence degree of airflow in the combustion chamber increases, and the velocity axial component Urms increases; the temperature T at each point of the combustion chamber outlet increases accordingly. When the oilgas ratio is close to the flameout boundary, the stability of the combustion flow field weakens.

V231.2

安徽省高校自然科学研究项目资助项目（KJ2021A1610）;江西省高等教学改革研究资助项目（JXJG22861）