Damping Decrements in the Combustion Chambers of Liquid-Propellant Rocket Engines

Abstract

The damping decrements of pressure fluctuations in the combustion chambers of liquid-propellant rocket engines may be estimated on the basis of hard excitation of acoustic vibrations of a specific mode. A device for hard excitation of high-frequency pressure fluctuations has been developed. This device prevents damage to the components of the combustion chamber by flying metal fragments. Recommendations are made regarding the calculation of the acoustic characteristics for complex channels.