Please use this identifier to cite or link to this item:
http://bura.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 and Aerospace Engineering Research Papers |
Files in This Item:
File | Description | Size | Format | |
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Fulltext.pdf | 2.24 MB | Adobe PDF | View/Open |
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