Numerical Investigations on Development of Scramjet Combustor
Publication: Journal of Aerospace Engineering
Volume 28, Issue 5
Abstract
Numerical investigation of flow phenomena in a scramjet combustor has been performed for different geometric and operating parameters. The present investigation aims to find the optimal geometric parameters for a better fuel injection system with maximum combustion efficiency. Two-dimensional unsteady equations governing the compressible, turbulent reacting flow are solved using a commercial CFD solver. A combination of eddy dissipation (ED) and finite rate chemistry (FRC) models are used to model the combustion. The effect of divergence angles and scaling on the performance of a scramjet combustor is reported here. The effect of shocks generated by the strut and inlet conditions of a scramjet combustor on combustion efficiency has been reported. Present results show that the divergence angle and inlet conditions of combustors have significant effects on performance. A multiple-strut combustor has shown higher efficiency than a single-strut combustor. The modifications that improved the combustion efficiency of a DLR combustor are reported. The present simulation results match well with the experimental results available from the literature.
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Published In
Journal of Aerospace Engineering
Volume 28 • Issue 5 • September 2015
Copyright
© 2014 American Society of Civil Engineers.
History
Received: Jan 18, 2014
Accepted: Aug 5, 2014
Published online: Sep 16, 2014
Discussion open until: Feb 16, 2015
Published in print: Sep 1, 2015
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