Mixing In Scramjet Combustor Research Articles

Computational Analysis of Mixing in Scramjet Combustor using Cross Flow Injection Technique

The prime issue in supersonic combustion is proper mixing within short duration of time. Computational study has been performed to analyse the mixing of air and fuel using cross flow injection technique. Cross flow injection is performed by placing the fuel injectors on the walls of the scramjet engine which is perpendicular to the flow. To enhance the mixing of fuel and air, cavities were introduced. The flow recirculation inside the cavity will enhance the mixing and combustion. The fuel injectors were placed just upstream of the cavity. Analyses were done by changing the injection angles. The air is allowed to enter at different Mach numbers and the changes were analysed using ANSYS software. The roles of cavity cross flow injection, pressure, temperature, velocity and Mach number variation were examined in this study and the obtained results were compared between various configurations.

Computational Analysis of Mixing in Scramjet Combustor using Cross Flow Injection Technique

Computational Analysis of Mixing in Scramjet Combustor using Cross Flow Injection Technique

19 ランプ型噴射方式による超音速空力混合の研究

Numerical approach for supersonic mixing flow field with the ramp injection is examined. It is said that ramp injector configurations can enhance mixing efficiency in combustor of ram/scram jet engine, by use of the formation of axial vortex. One of ramp injector types, which consists of alternate compression ramps and expansion troughs, has been studied by I.A. Waitz et al.. Calculation is conducted comparing with the result of the experimental study and calculated flow field was visualized by using particle traces.As a result of this numerical simulation, it was observed that the pattern of shock wave obtained by calculation agreed with experimental results. The formation of a counter-rotaing streamwise vortex pair and vortical roll-up of the jet were captured clearly as same as experimental observation. According to these results, it can be said that the CFD code used in this study has an ability to capture vortex structure formed by ramp injector and that the streamwise vortex generated by the injector is the one of key factors for enhancement of fuel-air mixing in scramjet combustor.