Please use this identifier to cite or link to this item: http://buratest.brunel.ac.uk/handle/2438/15444
Title: Modelling of Supersonic Combustion Systems for Sustained Hypersonic Flight
Authors: Neill, S
Pesiridis, A
Keywords: Supersonic combustion;Hypersonic;Scramjet;Propulsion;Fuel injection;Fuel injection fluid dynamics
Issue Date: 2017
Publisher: MDPI
Citation: Energies,(2017)
Abstract: Through Computational Fluid Dynamics and validation, an optimal scramjet combustor has been designed based on twin-strut Hydrogen injection to sustain flight at a desired speed of Mach 8. An investigation undertaken into the efficacy of supersonic combustion through various means of injection saw promising results for Hydrogen-based systems, whereby strut-style injectors were selected over transverse injectors based on their pressure recovery performance and combustive efficiency. The final configuration of twin-strut injectors provided robust combustion and a stable region of net thrust (1873 kN) in the nozzle. Using fixed combustor inlet parameters and injection equivalence ratio, the finalized injection method advanced to the early stages of two-dimensional (2-D) and three-dimensional (3-D) scramjet engine integration. The overall investigation provided a feasible supersonic combustion system, such that Mach 8 sustained cruise could be achieved by the aircraft concept in a computational design domain.
URI: http://bura.brunel.ac.uk/handle/2438/15444
ISSN: 1996-1073
Appears in Collections:Dept of Mechanical Aerospace and Civil Engineering Research Papers

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