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http://dx.doi.org/10.5139/JKSAS.2006.34.10.071

Effect of Swirl Injector with Multi-Stage Tangential Entry on Acoustic Damping in Liquid Rocket Engine  

Bazarov, V. G. (서울대학교)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.34, no.10, 2006 , pp. 71-79 More about this Journal
Abstract
Swirl injector with multi-stage tangential entry was analyzed to suppress high-frequency combustion instability in Liquid Rocket Engines. In order to analyze the effect of swirl injector as an acoustic absorber, swirl injector was regarded as a quarter-wave resonator and it's damping capacity is verified in atmospheric temperature. It has a finite mode of vibration and natural frequencies which can be tuned to the natural frequencies of a model combustion chamber. The interior air core shape of injector is more stable in the case of using the swirl injector with multi-stage entry than with single-stage entry. Also, when the swirl injector with multi-stage entry is used, tuned-injector length for unstable mode is well agreed with the calculated length. From the experimental data, it is proved that if the interior air core shape of swirl injector is stable, the fine tuned swirl injector can decrease the unstable mode of model chamber effectively and increase the damping rate.
Keywords
Swirl Injector; Multi-stage Tangential Entry; Resonant Frequency; Acoustic Damper; Combustion Instability;
Citations & Related Records
Times Cited By KSCI : 1  (Citation Analysis)
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