搭建了由13个波瓣喷嘴采用5?5叉排方式布置的航空发动机分级燃烧室水模型实验台，通过改变各喷嘴的分级喷射方式实现不同的工作载荷。对30%及巡航两种载荷下的模型燃烧室，分别采用2级和3级两种燃烧组织方式下的空气动力学流场特性进行了水模拟示踪实验和数值模拟研究。对两种分级燃烧方式，通过实验和数值模拟研究了改变两种载荷下的油气比时，各级波瓣喷嘴所诱发的复杂涡系结构和涡量的大小、形态、相互作用和演变规律等气动特性。结果表明，两种分级喷射方式的涡系结构均可分为初始段、过渡段和发展段；各涡系之间历经了从独立到合并重组、再变成新涡系等演变和相互作用过程；增加油气比对两种分级喷射的过渡段影响均较大。空气模型、水模型流场的计算结果与实验结果吻合良好，验证了研究结果的可行性和可信度。

A 13 lobe nozzles with a 5×5 fork row aero-engine staged combustion chamber water model test bench was set up to achieve different working loads by changing the staged injection mode of each nozzle. The aerodynamic flow field characteristics of the model combustion chamber under two kinds of loads, such as 30% and cruise, were studied by water simulation tracer experiments and mathematical modeling under the two-stage and three-stage combustion organization modes. The aerodynamic characteristics of complex vortex structure and vorticity induced by each level of flap nozzle in size, shape, interaction and evolution were studied by experiments and numerical simulation for the two fractional combustions when the oil and gas ratio under the two loads was changed. The results showed that the vortex structure of the two kinds of staged injection modes can be divided into initial section, transition section and development section. The vortex systems have undergone evolution and interaction from independence to merger and reorganization, and then evolve into new vortex systems. When the oil?gas ratio increased, it had a greater impact on the transition of the two kinds of staged injections. The calculation results of the air and water model flow fields were consistent with the experimental results, which verified the feasibility and credibility of the research results.