Performance Analysis of Supersonic Combustion Chamber using Planar-Shaped Strut Injector

Abstract

Significant researches have been enthusiastic throughout the last centuries for supersonic and hypersonic flight conditions for enabling flights many times faster than sound. This current work presents the performance analysis of supersonic combustor interface and flow construction through a scramjet engine with a Planar-shaped strut injector (PSSI) at the supersonic Mach. An important aspect of this study is the discovery of the fuel mixing mechanism inside the combustion chamber with PSSI. Mixing and combustion performance can be enhanced by the novel PSSI configuration. The scramjet configuration is incorporated with the supersonic inlet air temperature of 1250 K, where the vitiated air follows at Mach 3, and this technique is based on a high accelerating effect of scramjet propulsion mechanism. Scramjet engines can maintain a naturalistic high enthalpy conditions in minimum durations. It is observed that the maximum temperature of 3510 K is attained at the recirculating zones that are produced because of undulation enlargement and therefore the fuel jet losses concentration whereas the maximum combustion efficiency of 86% is investigated from the current research work.