Girish Barpande

Bio: Girish Barpande is an academic researcher from Vishwakarma Institute of Technology. The author has contributed to research in topic(s): Static pressure & Hydrogen fuel enhancement. The author has an hindex of 1, co-authored 1 publication(s) receiving 1 citation(s).

Using numerical simulation to investigate the effect of injection configurations over the scramjet performance

Abstract: Achieving combustion in the available residence time by efficient mixing of the injected fuel has been a challenge for scramjet designers since years. Design of the injection configuration do affect the patterns of mixing and in turn the rate of heat release for a given combustor geometry. The presented work attempts to investigate the effect of inclined injection configurations on the performance of a scramjet for a typical combustor geometry having intrusive fuel injection using strut. Over a decades of literature points towards the fact that numerical simulations are widely being accepted as promising method of investigation of flow inside a scramjet. Reacting simulations of hydrogen injection in an inlet air stream of Mach 2.5 are done with various fuel injection configurations. After validation of simulation results with the available experimental Sadatake Tomioka et al. (2001) results, different injection configurations were simulated for a constant equivalence ratio. The maximum combustion, mixing and heating was observed in near the strut surface, hence flow fields of these configurations are studied near the strut to understand the mechanism of mixing. Observations on performance parameters like total pressure loss, maximum top wall static pressure, flow enthalpy etc. are made to compare these configurations.

Experimental study on the influence of the injection structure on solid scramjet performance

Abstract: Injection structures can affect the ignition and combustion of fuel and supersonic air in scramjets, strongly impacting their performance. The influence of three different injection structures on the performance of a solid scramjet was investigated using direct-connect tests. The experiment employed a boron-based fuel-rich propellant and simulated a flight Mach number 5.6 at 25 km. The results show that, compared to a circular nozzle (test no.1), the elliptical nozzle (test no.2) can significantly improve the ignition and combustion of the fuel-rich mixture produced in the gas generator. This improvement is even more significant when a two-stage elliptical nozzle is adopted (test no. 3). The combustion of the fuel-rich mixture presents the typical cycle of establishment, development, maintenance, and decay. The wall ablation area and particle deposition distribution, show that the gaseous components in the fuel-rich mixture burn rapidly, and that particles deposition increases when an elliptical nozzle is used. The combustion efficiency of test no.3 reached 0.60, which is larger than the 0.48 obtained during test no.1. The low particle combustion efficiency is a key factor limiting solid scramjets performance.