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Effects of Mean Flow and Nozzle Damping on Acoustic Tuning of a Resonator in a Rocket Combustor  

Sohn, Chae-Hoon (조선대학교 항공우주공학과)
Park, I-Sun (조선대학교 대학원 항공우주공학과)
Kim, Seong-Ku (한국항공우주연구원 연소기그룹)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.10, no.3, 2006 , pp. 41-47 More about this Journal
Abstract
Effects of mean flow and nozzle damping on acoustic tuning of a gas-liquid scheme coaxial injector are investigated numerically adopting a linear acoustic analysis. The injector plays a role as a half-wave acoustic resonator for acoustic damping in a combustion chamber of a liquid rocket engine. As Mach number of mean flow in a chamber increases, the resonant frequency of the first tangential mode decreases slightly and the optimum injector tuning length varies negligibly. Nozzle damping affects neither the resonant frequency nor the optimum length. From these numerical results, effects of mean flow and nozzle damping on acoustic tuning of a resonator are negligible. As open area of the injectors increases, the acoustic amplitude decreases, but new injector-coupled modes appear.
Keywords
Acoustic Tuning; Half-Wave Resonator; Acoustic Damping; Injector Tuning Length;
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Times Cited By KSCI : 2  (Citation Analysis)
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