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Article Dans Une Revue Acta Astronautica Année : 2008

Experimental investigation of high-frequency combustion instabilities in liquid rocket engine.

Résumé

High-frequency instabilities in liquid propellant rocket engines are experimentally investigated in a model scale research facility. Liquid oxygen and gaseous methane are injected in the combustion chamber at 0.9 MPa through three coaxial injectors vertically aligned. High-amplitude transverse pressure fluctuations are generated in the chamber at frequencies above 1 kHz by a rotating toothed wheel actuator which periodically blocks an auxiliary lateral nozzle. The chamber eigenmodes are identified in a first stage by examining the response of the system to a linear frequency sweep. In a second stage the chamber is excited at the frequency corresponding to the first transverse (1T) mode. The effect of the pressure mode on combustion is observed with intensified and high-speed cameras. Photo-multipliers and pressure sensors are also used to characterize the system behavior and examine phase relations between the corresponding signals. Flame structure modifications observed for specific injection conditions correspond to a strong coupling between acoustics and combustion which notably modifies the flow dynamics, augments the flame expansion rate and enhances heat transfer to the wall.

Dates et versions

hal-00497225 , version 1 (02-07-2010)

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Franck Richecoeur, S. Ducruix, P. Scouflaire, S. Candel. Experimental investigation of high-frequency combustion instabilities in liquid rocket engine.. Acta Astronautica, 2008, 62, pp.18-27. ⟨10.1016/j.actaastro.2006.12.034⟩. ⟨hal-00497225⟩
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