【摘要】 航空发动机燃烧室是发动机的核心部件之一，它直接影响发动机的性能和可靠性，而其内部流场特征对燃烧室的设计起着至关重要作用。为了探究某型双头部回流燃烧室流场分布特性，本文采用实验与数值仿真方法针对该型燃烧室进行流场特性研究，得到了热态条件下火焰筒内部流场分布特性和燃烧室进/出口压差对其内部流场的影响规律。结果表明：进/出口压差分别为1 500、3 500、5 000 Pa工况时，双头部回流燃烧室内部流场分布特征相似，且燃烧室内部流场速度大小随进/出口压差的增加而增大；同一截面下，与实验条件下回流燃烧室内部流场分布特性相比，仿真条件下流场分布特征与其相似。上述研究成果为该型燃烧室火焰筒优化设计提供技术支撑。更多还原

【Abstract】 The combustion chamber is a critical component of an aeroengine, significantly influencing its performance and reliability. The characteristics of the internal flow field are fundamental to both the design and optimization of the combustion chamber. To investigate the flow field distribution characteristics of a double-head reflux combustor, this study both experimental and numerical simulation methods was utilized. The flow field characteristics inside the flame cylinder under hot conditions and the impact of varying inlet/outlet pressure differences on the internal flow field was focused. The results show that at inlet/outlet pressure differences of 1 500 Pa, 3 500 Pa, and 5 000 Pa, the flow field distribution characteristics inside the double-head reflux combustion chamber are similar. Additionally, the velocity within the combustion chamber increases as the inlet/outlet pressure difference increases. Under identical cross-sectional conditions, the flow field distribution characteristics in the simulation closely match those observed experimentally. The aforementioned research findings provide valuable technical support for the optimization design of the combustion chamber’s flame tube.更多还原