Investigation Of Flow And Mixing Properties Of A Supersonic Combustor Holding Flame In Central

Scramjet is a new aspirated propulsion device as the research peak of modern propulsion, which can achieves hypersonic flight in the atmosphere. And supersonic combustion technology is the key of those study. In this paper, we put forward a new concept of supersonic combustor holding flame in central, and accomplish the design of the corresponding dimensional model. Then, we conduct a series of studies of the model. The main work and conclusions are summarized as follows:First, we put forward a two-struts dimensional partition and a multi-struts combustion chamber design schemes, and investigated the cold flow field and the mixing of the fuel and the airflow. Numerical simulation results indicate that, the trailing edge of the struts in a multi-struts combustor may form recirculation zones, and the interaction between the struts can also form low Mach number zones, which are both beneficial to ignition and flame stabilizing. Fuel mainly concentrated in the combustion chamber center, and with no fuel near the wall. Central burning may realize in this combustion chamber. And the structure of the flow field and fuel mixing field in a multi-struts combustor are more reasonable than those in a two-struts dimensional partition combustor. And the fuel-mixing field in a three-struts combustor is slightly superior to that in a five-sturts combustor.Secondly, we select three-struts combustion chamber scheme, and improve it by changing the size of the struts and the distance bwteen the struts. Results show that when the distance between the struts before and after is X = 40 mm, and the distance between the double sturts is Y = 10 mm, with the thick of the double struts is 6 mm, the combustion chamber can form a stable and reasonable recirculation zones and low Mach number area, which can ensure a low total pressure loss at the same time.Finally, We study the influence of the combustion performance when changing the injection method. and calculate the combustion efficiency of the combustor. The study found that, when the fuel flow rate is 0.5 kg/s, at which time ER = 0.5, the combustor can burn sustaining with larger heat release and smaller losses.The study above indicate that the supersonic combustor holding flame in central is a kind of reasonable, efficient and steady supersonic combustion device. The research result has great guidance for the subsequent experiment study on the scramjet.