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Amarjit Singh

Bio: Amarjit Singh is an academic researcher from PEC University of Technology. The author has contributed to research in topics: Deflagration to detonation transition & Static pressure. The author has an hindex of 1, co-authored 2 publications receiving 1 citations.

Papers
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Journal ArticleDOI
TL;DR: In this article, the effect of inclined injection configurations on the performance of a scramjet for a typical combustor geometry having intrusive fuel injection using strut is investigated, and the maximum combustion, mixing and heating was observed in near the strut surface.

1 citations

Book ChapterDOI
01 Nov 2019
TL;DR: In this paper, homogeneous hydrogen-air mixture is numerically investigated in a tube of 1 m length and 50 mm diameter with obstacles by solving two-dimensional compressible Reynolds averaged Navier-Stokes equation with reaction modelling of hydrogen air combustion, using open-source deflagration to detonation solverddtFoam.
Abstract: In this study, homogeneous hydrogen-air mixture is numerically investigated in a tube of 1 m length and 50 mm diameter with obstacles by solving two-dimensional compressible Reynolds averaged Navier–Stokes equation with reaction modelling of hydrogen-air combustion, using open-source deflagration to detonation solver ‘ddtFoam’ at OpenFoam platform. Deflagration to detonation transition is observed in the tube at various time and locations depending on obstacle configuration namely the blockage ratio and pitch. Turbulence offered by obstacles result in faster transition from deflagration to detonation. Suitable boundary conditions are assigned, and 2D and axisymmetric numerical simulations are performed and compared. Pressure, temperature, and flame tip location vs. time plots are plotted, and it has been observed that in 2D simulations, lower pitch of the obstacle system results in earlier deflagration to detonation transition, and detonation occurs earlier in axisymmetric simulations than 2D simulations for same configuration of blockages.

Cited by
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Journal ArticleDOI
TL;DR: In this paper, the influence of three different injection structures on the performance of a solid scramjet was investigated using direct-connect tests using a boron-based fuel-rich propellant and simulated a flight Mach number 5.6 at 25 km.

8 citations