ISSN:
1432-2153
Keywords:
Supersonic combustions
;
Oblique shocks
;
Oblique detonations
;
H2-Air combustion
;
Flame stability
Source:
Springer Online Journal Archives 1860-2000
Topics:
Physics
,
Technology
Notes:
Abstract In order to study the mechanisms of initiation and stabilization of H2-Air combustions (stoechiometric mixture initially atT 0=293 K andp 0=0.5 bar) in supersonic flow conditions behind an oblique shock wave (OSW), an original technique is used where OSW is generated in this mixture by the lateral expansion of the burnt gas behind a normal CJ gaseous detonation propagating into a bounding reactive mixture. Four Mach numberM of propagation of OSW are considered in the study, namelyM=7.7-6.1-4.4 and 3. Depending on the Mach numberM and inclinaison angleθ of OSW different regimes of combustion may occur in the driven mixture. For high values ofM (6.1 and 7.7) delayed steady overdriven oblique detonation waves (SODW) were obtained with a near CJ detonation wave as the critical regime. It was found that SODW obtained correspond quite well to prediction of the polar method. When thermal conditions behind the OSW are lower, either for high Mach number 6.1 and 7.7 for smaller angleθ than the previous case, or for lower Mach number, 4.4 and 3, the flame initiated at the apex is stabilized as a turbulent oblique flame behind the OSW. With much lower conditions, no combustion appears in the H2-Air mixture.
Type of Medium:
Electronic Resource
URL:
http://dx.doi.org/10.1007/BF01413876
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