Development of a new conceptual atomization simulator for liquid rocket engines

喷雾燃烧是航天发动机不可缺少的技术。数值模拟方法正在被引入先进发动机的开发中。然而，目前的喷雾燃烧模拟器不能描述喷射的液体燃料的雾化，这是决定随后的燃烧性能的最重要的过程。本研究拓展了微重力实验中的雾化概念，以揭示高速液体射流的自失稳机理和湍流雾化的物理基础。利用这些新发现，我们首次成功地开发了一个湍流雾化亚网格模型，该模型可以集成到当前的喷雾燃烧模拟器中，以描述喷射液体燃料所经历的局部湍流雾化特征。

Spray combustion is an indispensable technology for aero-space engines. The numerical simulation method is now being introduced for the development of advanced engines. The current spray combustion simulators, however, cannot describe the atomization of injected liquid fuel which is the most important process determining the subsequent combustion performance. In the this study, the new atomization concept derived from microgravity experiment observations were extendedly developed to reveal the self-destabilizing mechanism of high-speed liquid jet and the underlying physics of turbulent atomization. Using the new findings, we for the first time succeeded in developing a turbulent atomization sub-grid model, which can be integrated into the current spray combustion simulators to describe the local turbulent atomization feature experienced by the injected liquid fuel.