Academic Journals Database
Disseminating quality controlled scientific knowledge

NUMERICAL SIMULATION OF COMBUSTION CHAMBER WITHOUT CAVITY AT MACH 3.12

ADD TO MY LIST
 
Author(s): K.M. Pandey | A.P. Singh

Journal: International Journal of Soft Computing & Engineering
ISSN 2231-2307

Volume: 2;
Issue: 1;
Start page: 134;
Date: 2012;
VIEW PDF   PDF DOWNLOAD PDF   Download PDF Original page

Keywords: Hydrogen | Shear layers | Stabilization | stagnation temperature | Supersonic combustion

ABSTRACT
In this Simulation, supersonic combustion of hydrogen at Mach 3.12 has been presented. The combustor has a single fuel injection perpendicular to the main flow from the base. Finite rate chemistry model with K-ε model have been used for modeling of supersonic combustion. The pressure rise due to the combustion is not very high on account of global equivalence ratio being quite low. Within the inlet the shock-wave-boundary- layer interactions play a significant role. The combustor without cavity is found to enhance mixing and combustion while increasing the pressure loss, compared with the case without cavity to the experimental results. The OH mass fraction is less almost by an order to that of water mass fraction The OH mass fraction decreases as the gas expands around the injected jet and the local mixture temperature falls, However OH species are primarily produced in the hot separation region upstream of the jet exit and behind the bow shock and convected downstream with shear layer. The geometry results shows the better mixing in combustion chamber, caused by more extreme shear layers and stronger shocks are induced which leads loss in total pressure of the supersonic stream.
Affiliate Program      Why do you need a reservation system?