航空燃气轮机超紧凑燃烧室所产生的超重力旋转流能极大强化传热传质和燃烧化学反应速率，而超重力旋转流特性对强化热质传递过程和燃烧稳定性有重要影响。以试验室 UCC 燃烧室的设计模型为研究对象，用 Realizable k -ε湍流模型模拟高速旋转湍流。改变周向布置的二次空气射流条件，采用数值仿真研究了超紧凑型燃烧室旋转流动的流速分布、超重力效应、湍流动能局部突变效应、轴向加速效应、和速度径向迁移效应等气动性能和雾化燃油颗粒行为。二次射流对UCC 凹腔内涡轮间通道内的气动性能影响较大，但不在同工况下有各自的相似性。二次射流对涡轮间径向速度影响不大。燃油液雾散布具有环带形的斜向高斯分布特性。研究结果与相关试验有相同规律，对 UCC 燃烧室的设计分析和应用有参考价值。%High G-loaded rotational flow from aero turbine UCC(Ultra-Compact Combustors)may greatly strengthen heat mass transfer and combustion chemical reaction rates,and high G-load rotational flow is more important influential characteristics in heat mass transfer strengthening process and combustion stabilization. Taking the testing designed UCC model as the study object and using realizable k-ε turbulent model,high G-loaded rotational flow characteristics in UCC such as velocity distribution,high G-load effect,local mutation effect of turbulent energy,axial acceleration effect,velocity radial migration effect,and the fuel particle be-haviors are CFD numerical simulated by changing second air injection conditions of circumferential uniform arrangement. The second injection has greatly affected aerodynamics performance among turbine alleyways in UCC,but which has their respective similarity. The effects of second flow on radial velocity among alley-ways is few. Fuel spray dispersion has annular and declining Gaussian distribution characteristics. The study results have the same regular pattern with the test,and have reference value to UCC design,analysis and ap-plication.
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