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采用试验研究方法初步探索了一种超声波/离心组合喷嘴应用于航空发动机燃烧室的可行性.对该组合喷嘴开展冷态试验,得到了其流量特性和雾化特性(包括油雾索太尔平均直径(SMD)和雾化锥角),设计加工了横截面尺寸为117mm×60mm的单头部矩形燃烧室模型,并在不同进口条件下开展了相关的燃烧性能试验.结果表明:在冷态情况下,喷嘴流量特性符合传统离心喷嘴的流量特性,流量与供油压差呈二次函数关系;喷嘴雾化细度较好,无气状态下,油雾SMD在38～45μm之间变化,在满足产生超声波要求的气压条件范围内油雾SMD在8～12μm之间变化;喷雾锥角主要受供气条件影响,供油压力对喷雾锥角基本无影响;装有该喷嘴的模型燃烧室在所有试验工况下均可以稳定燃烧,燃烧效率最高达到99%.
The feasibility of applying a combination of ultrasonic / centrifugal nozzle to aeroengine combustor has been tentatively explored by means of experimental research.The cold flow test of the combined nozzle was carried out and its flow characteristics and atomization characteristics Diameter and atomizer taper angle), a single head rectangular combustion chamber model with a cross section of 117mm × 60mm was designed and manufactured, and the relevant combustion performance tests were carried out under different inlet conditions.The results showed that in the cold state The flow characteristics of the nozzle meet the flow characteristics of the traditional centrifugal nozzle, the flow and supply pressure showed a quadratic function; atomization fineness of the nozzle is better, no gas, the oil mist SMD changes between 38 ~ 45μm, The oil mist SMD varied from 8μm to 12μm within the range of atmospheric pressure to meet the ultrasonic requirements. The spray cone angle was mainly affected by the gas supply condition. The supply pressure had no effect on the spray cone angle. The model combustion chamber In all test conditions can be stable combustion, combustion efficiency up to 99%.