航空发动机燃油雾化特性研究进展

从实验、理论和数值模拟三个方面对航空发动机内的燃油雾化问题研究进展进行了综述。实验方面,通过雾化实验,可定性分析喷注参数及环境条件等因素对雾化效果的影响,测量技术是影响实验精度的关键;雾化理论对液膜形状及破碎特性的预测值与实验还存在一定误差,复杂气动条件下的雾化理论还较为缺乏;雾化数值模拟可以获得不同形式燃油雾化的某些典型变化过程,复杂多过程、多因素影响的雾化模拟还较难开展。总体上看,航空发动机燃油雾化机理还未能完全揭示。

Review on Fuel Atomization in Aeroengine

In order to reduce the pressure loss during radial air entrainment of compressor, based on the design of the new fins element structure, the effects of new fins element structure on radial air entrainment pressure loss were studied. Numerical study was carried out on the de-swirl system of different rotational speed and new fins structure. The structure of radial air entrainment and pressure loss distribution curve of compressor co-rotating cavity under different working conditions were obtained. The results show that the new fins element structure can restrain the swirl ratio of air flow and reduce the loss of air entrainment pressure, and that the fins element channel width and height have the best value to make the vortex reducer drag reducing effect better. The drag reduction effect is 86.5% higher than that of the simple cavity model under the optimal structure, which the fins element channel width is L=0.78 and the channel height is R₃=0.97. The high and low fins structure can play a better drag reduction effect. With the increase of one side fin height, the drag reduction effect is better when the height increased L₁=0.3, and the drag reduction benefit is the same when the A side or B side fin increases. On the one hand, the drag reduction performance of the optimal high and low fins structure is 87.5%, 29% and 7.8% higher than that of the simple cavity model, the typical fins vortex reducer model and the fins element channel with L=0.78 and R₃=0.97, respectively; on the other hand, the optimal high and low fins structure can reduce the quality of the fins element and has high engineering application value.