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CFD Analysis of Scramjet Combustor Using Strut With Circular and Planer Injector

[+] Author Affiliations
K. M. Pandey, Sivasakthivel Thangavel

National Institute of Technology Silchar, Silchar, AS, India

Paper No. IMECE2011-62310, pp. 1521-1529; 9 pages
doi:10.1115/IMECE2011-62310
From:
  • ASME 2011 International Mechanical Engineering Congress and Exposition
  • Volume 4: Energy Systems Analysis, Thermodynamics and Sustainability; Combustion Science and Engineering; Nanoengineering for Energy, Parts A and B
  • Denver, Colorado, USA, November 11–17, 2011
  • Conference Sponsors: ASME
  • ISBN: 978-0-7918-5490-7
  • Copyright © 2011 by ASME

abstract

The simulation of a supersonic reactive flow is an important tool for the investigation and development of Scramjet engines. Numerical investigations have become less expensive than experiments. In this research work mixing and combustion for different type of strut injector is studied especially for strut with circular injector and strut with planer injector, in this work DLR scramjet combustor model is used, it having length of 340mm, width of 40mm, inlet entry height of 50mm and exit height of the combustor is 62mm. In this combustor strut is placed at the distance of 77mm from the inlet. Total length of the strut is 32mm. Air entry Mach number is 2, temperature and pressure of the air is 340k and 1 bar, at the base of the strut hydrogen will be injected at a Mach number of 1, temperature and pressure of the Hydrogen is 250k and 1 bar. Combustion will be initiated using pre burning of small amount of hydrogen and oxygen. In this CFD analysis two-dimensional coupled implicit NS equation, the standard k-ε turbulence model and the finite-rate/eddy-dissipation reaction model have been applied to numerically simulate the flow field of the hydrogen fuelled scramjet combustor. From analysis it is found that strut with planer injector giving good mixing efficiency, combustion efficiency and total pressure loss is less as compared to strut with circular injector. In both cases subsonic regions at the channel symmetry axis are responsible for flame holding. If the combustor geometry is chosen in a favourable way these subsonic zones may be kept small. Moreover, the flames are away from solid walls thus minimizing the wall heat load.

Copyright © 2011 by ASME

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