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http://dx.doi.org/10.6108/KSPE.2019.23.6.001

Evaluation of Nozzle's Combustion Instability Suppression Effect by Linearized Euler Equation  

Kim, Junseong (Satellite System Team, Korea Aerospace Industries)
Moon, Heejang (School of Aerospace and Mechanical Engineering, Korea Aerospace University)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.23, no.6, 2019 , pp. 1-10 More about this Journal
Abstract
The wave motion inside the nozzle is known as one of the major damping elements of the rocket's combustion instability by it's aeroacoustic effects that result from the flow passage through the nozzle throat. These effects can be quantitatively evaluated by the nozzle admittance. In this study, one-dimensional linearized Euler equation was adopted to calculate the nozzle admittance, and trend analysis was performed depending on the nozzle's main design variables. As a result, when nozzle converging part shortens, it is verified that the frequency dependency of the nozzle admittance is decreased due to the widened frequency range with lowered longitudinal nozzle admittance. Also, admittance estimation using the short nozzle theory is not appropriate when the first tangential mode of the pressure perturbation arises.
Keywords
Combustion Instability; Nozzle Admittance; Nozzle Damping; Linearized Euler Equation;
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