双旋流燃烧室两相喷雾试验和数值研究

采用粒子场脉冲激光全息技术对航空发动机燃烧室中的雾化场进行了测量，得到了燃烧室中燃油液滴直径的空间分布，从而对燃烧室中的雾化过程进行了研究。自主开发完成了适用于航空发动机燃烧室的三维两相数值计算平台，建立了首次雾化模型和二次雾化模型。基于LISA模型和KH-RT模型，对燃烧室中的首次雾化过程和二次雾化过程进行了数值模拟，得到了燃烧室中液雾的空间分布。通过将计算结果与试验结果进行对比，显示开发完成的雾化模型能很好的模拟高温高压，强旋流条件下航空发动机燃烧室的整个喷雾雾化过程。

Experimental and numerical study on spray atomization in a double-swirler combustor

Using the particle field pulsed laser holography imaging technique, the spatial distribution of droplet diameter in an aeroengine combustor is measured, the atomization process is studied, and the spatial distribution of droplets diameter in the combustor is obtained too. The numerical sprays models of the primary and secondary atomization are established, and a numerical software for the three-dimensional two-phase combustion in the aeroengine combustor is developed. Based on the LISA atomization model and KH-RT breakup model, the primary atomization process and secondary atomization process in the combustor are simulated numerically, obtaining the distribution of fuel spray droplets in the combustor. The simulation results are compared with experiments. The result indicate that the atomization models developed in this work can properly simulate the whole process of spray atomization under the conditions of high temperature, high pressure and strong swirling in aeroengine combustors.