Modeling of Supersonic Combustion Systems for Sustained Hypersonic Flight

Energies

Stephen M. Neill¹  Apostolos Pesyridis² 

[1] Aerospace Engineering Graduate, College of Engineering and Design, Brunel University London, Uxbridge UB8 3PN, UK;Metapulsion Engineering Ltd, 2C Eastbury Avenue, Northwood HA6 3LG, UK;

关键词: supersonic combustion;    hypersonic;    scramjet;    propulsion;    fuel injection;    computational fluid dynamics;   

DOI  :  10.3390/en10111900

来源: DOAJ

【 摘 要 】

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.

【 授权许可】

Unknown