Abstract Hydrogen being an ecological fuel is very attractive now for rocket engines designers. However, peculiarities of hydrogen combustion kinetics, the presence of zones of inverse dependence of reaction rate on pressure, etc. prevents from using hydrogen engines in all stages not being supported by other types of engines, which often brings the ecological gains back to zero from using hydrogen. Computer aided design of new effective and clean hydrogen engines needs mathematical tools for supercomputer modeling of hydrogen–oxygen components mixing and combustion in rocket engines. The paper presents the results of developing verification and validation of mathematical model making it possible to simulate unsteady processes of ignition and combustion in rocket engines.
Highlights Slow diffusion and kinetic combustion modes, as well as onset of detonation were modeled. Anomalous behavior of ignition delay versus pressure for hydrogen–oxygen mixtures was studied. Ignition delay time increases for both rich and lean mixtures as compared with stoicheometric ones Detonation initiation by local energy release was simulated numerically. In rocket engines burning begins like diffusion flame near injector, but deeper switches to kinetic regime.
Supercomputer modeling of hydrogen combustion in rocket engines
Acta Astronautica ; 89 ; 46-59
2013-03-01
14 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Supercomputer modeling of hydrogen combustion in rocket engines
Online Contents | 2013
|Combustion chambers for rocket engines
Engineering Index Backfile | 1956
|Combustion chambers for rocket engines
Engineering Index Backfile | 1956
|Combustion in solid-propellant rocket engines
NTRS | 1968
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