Impact of parametric variation on combustion characteristics of hydrogen‐fueled strut based scramjet combustor at supersonic speed

Abstract

Supersonic combustion ramjet engine is more fascinating among all the airbreathing engines. Due to its higher thrust to weight ratio, researchers are more interested to get the superior combustion performance at the optimum boundary conditions. The flow field characteristics and combustion performance have been analysed with the help of Ansys 14.0 software. Generic scramjet combustor of German Aerospace Center (DLR) has been taken into consideration for comparison purpose and off design analysis has been conducted to investigate and analyse the changes. Two dimensional compressible Reynolds Averaged Navier-Stokes (RANS) turbulence model has been opted with the finite-rate/eddy-dissipation reaction model. K-ε two equation turbulence model has been selected to reach up to reasonable accuracy. Validation of the present work has been done with the help of both non-reacting and reacting type data from open literature. To choose the appropriate meshing of the computational model three different types of mesh elements, that is, coarse, medium and fine has been analysed and also grid independence analysis is performed. The present article objective is to get optimum boundary condition by changing the incoming air temperature and pressure at constant Mach number to connect the bridge between incoming air temperature and pressure to the change in velocity throughout the combustion chamber. The detailed understanding and explanation have been done by varying the temperature range of incoming air because of its major impact on combustion performance. Nonetheless, a small variation of air pressure will also discuss to observe the parameters which majorly influence while doing performance analysis. At the end the Optimum boundary condition for the present computation work is observed to be at 833 K temperature with 115 299 Pa pressure.

Numerical investigations on the influence of double ramps in a strut based scramjet combustor

“…Compared to the single strut combustor, a maximum improvement of 33.86% in combustion efficiency is obtained. According to Ambe Verma et al's 34 research on parametric change on the combustion parameters of a hydrogen-fueled strut-based scramjet combustor with an incoming air temperature of 833 K and a pressure of 115,299 Pa, combustion efficiency of 93.03% is achieved.…”