喷口尺寸对高温升燃烧室副喷嘴性能影响

Effect of Orifice Size on the Pilot Nozzle Performance of High Temperature Rise Combustor

为了获得某高温升燃烧室副喷嘴性能及其与喷口尺寸的相互关系,通过试验研究了供油压力和离心喷嘴的关键结构参数对燃油流量、喷雾锥角和雾化性能的影响。研究的关键参数有喷口长度与喷口直径,采用3维相位多普勒粒子分析仪测量了某一直线上各点的数密度分布,以及R-R(Rosin-Rammler)分布的特征直径D和均匀度指数N。结果表明:在供油压力为164~3350 kPa的条件下,燃油流量和喷雾锥角随喷口长径比(旋流室与喷口直径比不变)和旋流室与喷口直径比(喷口长径比不变)的增大而减小,增大喷口长径比和减小旋流室与喷口直径比可改善雾化效果。研究获得的规律为三旋流高温升燃烧室喷嘴优化设计提供了重要的理论依据。

In order to obtain the pilot nozzle performance of a high temperature rise combustor and its relationship with the orifice size,the effects of fuel supply pressure and the key structural parameters of centrifugal nozzle on fuel flow rate,spray cone angle and atomization performance were studied by test.The key parameters were orifice length and orifice diameter.The density distribution of each point on a straight line and the characteristic diameter D and evenness index N of Rosin-Rammler distribution were measured by 3D Phase Doppler Particle Analyzer.The results show that the fuel flow rate and spray cone angle decrease with the increase of orifice length-to-diameter ratio(the ratio of swirl chamber to orifice diameter is constant)and the ratio of swirl chamber diameter to orifice diameter(the ratio of orifice length-to-diameter is constant)under the 164~3350 kPa of the fuel supply pressure.Increasing the ratio of orifice length-to-diameter and decreasing the ratio of swirl chamber diameter to nozzle diameter can improve atomization effect.The study provides an important theoretical basis for the optimization design of the triple swirler high temperature rise combustor nozzle.