Numerical Simulation Of The Combustor In Supersonic Combustion Engine

Sramjet engine was an new Propulsion Technology with the broad development prospects. In this article, the fuel mixture burning flow field carried on simulation and the research to the combustion chamber in supersonic inlet condition.Combustion chamber flow field was carried on numerical simulation in view of the approximate one-dimensional model analysis through one-dimensional procedure, the combustion chamber including the Isolator, the combustion chamber, the partial jet pipe. This article selects the equal pressure +equal Ma number+equal static temperature model. The conclusions were as follows: In the combustion chamber there was much total pressure lose, and the more import Mach the more total pressure loses. The boundary layer moved along with the heating quantity increase to the upstream in Isolator, finally may move to the inlet pipe and inlet.In this paper it may transform during different modes through changing burning exothermic for the fixed geometry throat model.In order to further study for the flow field characteristic, this article had research to the two-dimensional combustion chamber model separately in cold condition and burning condition, simultaneously has also studied the Isolator flow field and the function. In cold condition, firstly comparing several computational method for Numerical simulation result, and choosing the appropriate method to computer and analyse the model. The characteristic of resistance,total pressure,temperature is computed and analysed through the program code and Fluent soft, the model was advantageous to the fuel mix and burning. The conclusions were as follows: NND scheme was much effect at simulation shock wave characteristic, the MUSCL scheme was much effect at computation viscousness flows or burning flow.The cavity structure can effectively strengthen the fuel mixing and burning camparing the two-step structure.In the Isolator there was the separation of boundary-layer phenomenon obviously, simultaneously it appeared complex shock train structure with the boundary layer, this shock train can cushion influence for inlet pipe from the high back-pressure of burning, which can transform in different modes, but also should see: if the shock train was pushed to the Isolator, it will be able to cause the engine not to start.The step structure could hinder effectively burning high back-pressure to move to the upstream; The cold condition flow field and the burning condition flow field were much different, in cold condition flowing it had very strong shock-wave effect, thus the total pressure loses was much high, the resistance coefficient was much big. Contrarily in burning condition, in the cavity structure the speed of flow reduces for burning heating, the shock-wave effect was much weak.This article contrastly analyze several kind of cavity models and several injecting fuel way for the cavity, the best steady flame effect for fuel burning was summarized.The integrated analysis indicated that, cavity structure combustion chamber was possible to realize the fuel mixing and burning for scramjet, the one-dimensional model analysis can reflect the the parameter change rule intuitively for entire combustion chamber.The cavity structure was the steady flame ideal structure, and it had the extremely significance to supersonic burning.