固冲发动机补燃室流场的实验校测

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

关键词:  固冲发动机  补燃室  数值仿真  实验校验

Key words:  Ducted rocket  Secondary combustor  Numerical simulation  Experimental validation

摘要:

发展了一种利用补燃室温度场测量对数值计算的有效性进行校测的方法,设计了实验发动机并开展了直连实验,对非壅塞式固冲发动机开展研究。根据测量的数据计算了燃气发生器和进气道的出口参数,并将之作为补燃室的入口边界条件开展数值模拟。实验获得的温度场和数值模拟获得的结果在一定程度上吻合较好,从一个侧面验证了数值方法的有效性。

Abstract:

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.