固冲发动机补燃室流场的实验校测

1引言目前数值模拟已广泛应用到火箭发动机的流场分析中,特别是固冲发动机补燃室的燃烧和流动1,2]。但是这种方法在固冲发动机补燃室应用的有效性还没有合适的实验验证。国外开展的补燃室流动实验大多以水为介质,用片光流动显示的方法观察流场的概貌,与真实发动机的流动之间存

Experimental validation of flow field in the secondary combustor of a subscale ducted rocket

Experimental validation method through temperature field measuring in the secondary combustor of ducted rocket was developed. A subscale ducted rocket motor and a thermo-rake were designed. Direct connection experiments were carried out using low combustion temperature solid propellant products as primary flow and air as secondary flow. The mass flow rate and pressure of air and hot gas at the entrance of secondary combustor were calculated based on the measured pressure and structural parameters, and were used as boundary condition in numerical simulation. The experimental results agree to a certain extent with the numerical simulation and it indicates that this validation method is effective, and the numerical simulation method is also effective.