OH PLIF imaging of supersonic combustion using cavity injection

O’Byrne, Sean, Stotz, Ingo, Neely, Andrew J., Boyce, Russell R., Mudford, Neil R. and Houwing, A. F. P. (2005). OH PLIF imaging of supersonic combustion using cavity injection. In: A Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference. AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference, Capua, Italy, (1466-1477). 16-20 May 2005.


Author O’Byrne, Sean
Stotz, Ingo
Neely, Andrew J.
Boyce, Russell R.
Mudford, Neil R.
Houwing, A. F. P.
Title of paper OH PLIF imaging of supersonic combustion using cavity injection
Conference name AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference
Conference location Capua, Italy
Conference dates 16-20 May 2005
Proceedings title A Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference
Journal name A Collection of Technical Papers - 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference
Place of Publication Reston, VA, United States
Publisher AIAA
Publication Year 2005
Sub-type Fully published paper
ISBN 1563477297
9781563477294
Volume 3
Start page 1466
End page 1477
Total pages 12
Language eng
Abstract/Summary Planar laser-induced fluorescence of the hydroxyl radical is used to investigate a cavitybased fuel injection system for scramjet operation at a flight Mach number of 11.5. Hydrogen and ethylene fuels are compared over a range of fuel-lean global equivalence ratios. Both fuels show evidence of combustion at each fuel injection pressure. Hydrogen burns diffusively in the shear layer and further downstream, with penetration distance increasing linearly with injection pressure. The combustion in the cavity shear layer sheds regular vortices. Ethylene behaves similarly to hydrogen at the lower equivalence ratios but shows evidence of intense, localized combustion at the highest equivalence ratio. In all cases combustion occurs in the shear layer above the cavity rather than in the recirculating cavity flow.
Subjects 090107 Hypersonic Propulsion and Hypersonic Aerodynamics
Q-Index Code E1
Institutional Status Non-UQ
Additional Notes AIAA 2005-3357

 
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Created: Thu, 19 Mar 2009, 14:59:32 EST by Ms Sarada Rao on behalf of School of Mechanical and Mining Engineering