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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。
The particle field pulsed laser holography was used to measure the atomization field in the combustion chamber of aeroengine. The spatial distribution of the diameter of the fuel droplets in the combustion chamber was obtained, and the atomization process in the combustion chamber was studied. Independently developed and completed a three-dimensional two-phase numerical calculation platform applicable to the combustion chamber of an aero-engine, established the first atomization model and the second atomization model. Based on LISA model and KH-RT model, the first atomization process and the second atomization process in the combustion chamber were numerically simulated, and the spatial distribution of liquid mist in the combustion chamber was obtained. By comparing the calculated results with the experimental results, it is shown that the developed atomization model can well simulate the entire spray atomization process of aeroengine combustors under high temperature and high pressure and strong swirl flow conditions.