Initiation of Detonation Combustion and Determination of Specific Impulse during Combustion of a Kerosene - Air Mixture in a Vortex Radial Chamber
F. A. Bykovsky, S. A. Zhdan, E. F. Vedernikov
Lavrentyev Institute of Hydrodynamics, Siberian Branch, Russian Academy of Sciences, Novosibirsk, Russia
Keywords: continuous spin detonation, pulsating detonation, vortex radial combustion chamber, aviation kerosene, air, flow structure, specific impulse
Abstract
Detonation combustion modes of a two-phase mixture of TS-1 aviation kerosene and air in a 500 mm diameter radial vortex chamber with a center-facing outlet, a nozzle, and axial baffles equalizing the product flow in the axial direction were implemented and studied. Continuous spin and pulsating detonation modes were achieved with strong (detonation wave) and weak (with combustion transition to detonation) initiation. It was found that with weak initiation, continuous spin detonation with a single transverse detonation wave was always achieved upon reaching the maximum specific impulse in this experimental setup - Isp,ƒ,max ≈ 1 600 s. A comparison was made between the specific impulses of this radial combustion chamber and chambers with annular cylindrical geometry, in which kerosene was burned in continuous multifront detonation modes. It was found that during detonation combustion of kerosene in cold air, the specific impulse values in annular cylindrical combustion chambers are higher than in radial combustion chambers. At hydrogen and air flow rates close to stoichiometry at the start of the combustion, autoignition followed by a transition to continuous spin detonation was observed. The transition time was reduced to 10 ms by forced (spark) initiation of the hydrogen-air mixture.
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