Abstract
AbstractAir breathing engines (Scramjet) are taking more attention in the current research era because of its weight to thrust ratio. Brayton cycle is used to complete the thermodynamic processes just like other gas turbine engines. The engine consumes atmospheric high speed air as oxidizer. Due to this restriction of the engine, it cannot work beyond the atmosphere. To comprehend the impact of innovative transverse fuel injector on the combustor wall has been introduced. Two distinct models are involved. Parallel fuel injection with wall fuel injection in DLR Scramjet model and one additional wall air injector ahead of the wall fuel injector in the same model have been introduced to compare and understand the greater performance. Moreover, distance between wall fuel and air injector has also been compared. Ansys 14.0 Fluent-based solver has been chosen to perform analysis on all the selected model. Two-dimensional computational combustor model is utilized to complete the analysis. DLR scramjet combustor dimensions are considered for the investigation. The present article analyzed all the cases and found that the mixing behavior of the fuel with incoming free stream air approaches toward 100% in all cases. The improved performance is achieved by introducing only wall air injector just after the wall fuel injector. The maximum combustion efficiency has been reached up to 93.1%. KeywordsTransverse fuel and air injection strategyParallel fuel injectionWedge shaped strutCombustor performanceDLR scramjet combustor
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