Effect of Variation of Free Stream Boundary Conditions on Flow Characteristics of Transverse Injection-Based Scramjet Combustor Equipped with Shock Generators
Authors :- Yadav, P.M., Bhojani, K., Choubey, G.
Publication :- Advances in Thermal Sciences Select Proceedings of ICFAMMT 2022, Lecture Notes in Mechanical Engineering, Springer
Scramjets are very useful, in clocking supersonic speeds or greater and, as a superior alternative for turbo engines due to the absence of moving parts in them. Current work involves the study of the effect of variation in Mach number and temperature of inlet air stream on the flow dynamics and working of the scramjet combustor enhanced with dual shock generator. This is a numerical study conducted using Ansys Fluent software for executing the simulations. The 2D study involves a solver setup based on 2D coupled implicit RANS equations and standard k-ɛ turbulence model for a better comprehension of the flow characteristics and interactions between the air and the fuel. Due to its wide flammability characteristics and efficient combustion, hydrogen was chosen as fuel for the current study. By the research done previously on the usage of shock generators in the combustor of a scramjet engine, a 2D geometry with dual shock generators suggested by the study was used for the current work due to the merits in mixing and penetration of fuel. To justify the credibility of the solver, simulations were performed of the experimental work conducted by Weidner and Drummond and compared, and it was observed that the results from the simulations were in proper concurrence with experimental findings.