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http://dx.doi.org/10.5139/JKSAS.2015.43.9.838

Study on Acoustic Attenuation due to Particles and Flow Turning in Rocket Motors  

Kim, Taejin (Department of Mechanical Engineering, Hanbat National University)
Sung, Hong-Gye (School of Aerospace and Mechanical Engineering, Korea Aerospace University)
Seo, Seonghyeon (Department of Mechanical Engineering, Hanbat National University)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.43, no.9, 2015 , pp. 838-844 More about this Journal
Abstract
This paper includes summarization and analysis of previous research results on acoustic attenuation due to particles and flow turning in rocket motors among various damping parameters. Particle damping is the most effective mechanism in suppressing high-frequency combustion instabilities occurring in rocket combustion chambers, which is dependent on the size and the mass fraction of particles. Relatively weak attenuation by flow turning compared to particle damping depends on the geometry of propellant and a combustion chamber. Pumping driving effects need to be taken into account when realizing vorticity generation on the propellant surface. However, its driving effects become cancelled out by flow turning loss when the propellant geometry is cylindrical.
Keywords
Combustion Instability; Linear Stability; Particle Damping; Flow Turning Loss; Pumping Driving;
Citations & Related Records
Times Cited By KSCI : 1  (Citation Analysis)
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