基于超大涡模拟的燃烧室气动性能仿真研究进展

航空发动机燃烧室涉及旋流、雾化蒸发、掺混、化学反应、湍流与火焰相互作用等多尺度强耦合物理化学过程，相关的高精度建模和数值模拟面临极大的挑战。超大涡模拟是近些年发展的兼顾计算精度、计算效率和强鲁棒性的数值模拟新方法，具备试验室尺度和复杂工程应用场景下湍流流动与燃烧仿真能力。针对航空发动机燃烧室相关流动与燃烧基本特征，阐述了超大涡模拟的理论方法及特点，从旋流流动、湍流燃烧、液雾雾化、碳烟生成、燃烧不稳定等典型多物理过程，以及双旋流模型燃烧室和高温升燃烧室气动性能集成仿真等方面介绍了超大涡模拟的研究进展，对涉及的物理机制进行了分析，为超大涡模拟在航空发动机燃烧室中规模化工程应用提供了坚实支撑。超大涡模拟在较低的计算资源消耗下具备与传统大涡模拟相当的计算精度，是一种经济可承受的燃烧室高精度气动性能仿真新方法。

Progress of Combustor Aerodynamic Performance Simulation Based on Very Large Eddy Simulation

The turbulent flow and combustion in the combustor of aeroengines involved multi-scale strongly-coupled physicochemicalprocesses such as swirling flow, atomization evaporation, mixing, chemical reaction, turbulence-flame interactions, etc. The relevant high-fidelity modeling and numerical simulation face with great challenges. Very Large Eddy Simulation Method, i.e. VLES, was a newly-devel-oped numerical method in recent years with a good balance in robustness, computational accuracy, and efficiency. It has the ability to simu-late complex turbulent flow and combustion from laboratory scale to complex engineering application scenarios. According to the character-istics of flow and combustion in the chamber, the fundamental theoretical framework and characteristics of VLES method are presented, andthe research progress of high-fidelity numerical simulation application of VLES is introduced from typical multi-scale physicochemicalprocesses including swirling flow, turbulent combustion, liquid atomization, soot, combustion instability, etc. and integrated aerodynamicperformance simulations of double-swirl model combustors as well as high-temperature-rise combustors. The physical mechanism in-volved is analyzed, which provides solid support for the large-scale engineering application of VLES technology for aeroengine combustors.The VLES method has a comparable simulation accuracy as the traditional large eddy simulation method under the condition of low compu-tational resource consumption. Thus, it is an economically affordable new method for high-fidelity numerical simulation for the aerodynam-ic performance of combustors.