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http://dx.doi.org/10.5139/JKSAS.2019.47.10.720

Oscillating Boundary Layer Flow and Low Frequency Instability in Hybrid Rocket Combustion  

Kim, Jina (Department of Aerospace Engineering, Konkuk University)
Lee, Changjin (Department of Aerospace Engineering, Konkuk University)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.47, no.10, 2019 , pp. 720-727 More about this Journal
Abstract
Resonating thermal lags of solid fuel with heat transfer oscillations generated by boundary layer oscillation is the primary mechanism of the occurrence of the LFI (Low Frequency Combustion Instability) in hybrid rocket combustion. This study was experimentally attempted to confirm that how the boundary layer was perturbed and led to the LFI. Special attention was also made on oxidizer swirl injection to investigate the contribution to combustion stabilization. Also the overall behavior of fluctuating boundary layer flow and the occurrence of the LFI was monitored as swirl intensity increased. Fluctuating boundary layer was successfully monitored by the captured image and POD (Proper Orthogonal Decomposition) analysis. In the results, oscillating boundary layer became stabilized as the swirl intensity increases. And the coupling strength between high frequency p', q' diminished and periodical amplification of RI (Rayleigh Index) with similar frequency band of thermal lag was also decreased. Thus, results confirmed that oscillating axial boundary layer triggered by periodic coupling of high frequency p', q' is the primary mechanism to excite thermal resonance with thermal lag characteristics of solid fuel.
Keywords
Hybrid Rocket Combustion; Low Frequency Instability; Boundary Layer Oscillation; Proper Orthogonal Decomposition(POD); Rayleigh Index;
Citations & Related Records
Times Cited By KSCI : 2  (Citation Analysis)
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