燃油雾化在航空发动机预混燃烧过程中起着至关重要的作用.为提高某航空燃油喷嘴的雾化特性,改进和优化其结构参数,采用流体体积(VOF)界面捕捉算法和正交试验设计相结合的方法, 研究了喷嘴的内部流动及结构参数(扩张角、直线段长度、旋流槽升角、旋流槽个数)对雾化特性的影响规律.结果表明:旋流槽上的局部漩涡影响喷嘴内部燃油流动,通过改变旋流槽入口的结构形式消除局部压力损失;旋流槽个数对索特尔平均直径(SMD)的影响最为显著,扩张角是影响雾化锥角最大的因素,存在一个最优的旋流槽升角使油膜厚度最小,直线段长度对雾化特性的影响相对较小;当扩张角为60°、直线段长度为0.25 mm、旋流槽升角为45°、旋流槽个数为2时,优化效果最佳.优化后的喷嘴油膜厚度减小了43.68%,雾化锥角增加了3.70%,SMD减小了14.79%.

Fuel atomization plays an important role in premixed combustion of aero-engine. In order to improve the atomization characteristics of an aviation fuel nozzle and optimize its structural parameters, the volume of fluid (VOF) interface capture algorithm and orthogonal experimental design were used to study the influence of internal flow and structural parameters (expansion angle, length of straight section, rise angle of swirl groove, and number of swirl groove) on the atomization characteristics. The results show that the local vortex on the swirl groove affects the fuel flow in the nozzle, and the local pressure loss can be eliminated by changing the structure of the swirl groove inlet. The number of swirl grooves has the most significant effect on Sauter mean diameter (SMD), the expansion angle is the biggest factor affecting the atomization cone angle, there is an optimal swirl groove elevation angle to minimize the oil film thickness, and the length of straight section has relatively little effect on the atomization characteristics. When the expansion angle is 60°, the length of straight section is 0.25 mm, the rising angle of swirl groove is 45°, the number of swirl grooves is 2, and the optimization effect is the best. After optimization, the oil film thickness decreases by 43.68%, the atomization cone angle increases by 3.70%, and the SMD decreases by 14.79%.