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http://dx.doi.org/10.5139/JKSAS.2021.49.2.139

Controlling Low Frequency Instability in Hybrid Rocket Combustion With Swirl Injection and Fuel Insert  

Hyun, Wonjeong (Department of Aerospace Engineering, Konkuk University)
Lee, Chanjin (Department of Aerospace Engineering, Konkuk University)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.49, no.2, 2021 , pp. 139-146 More about this Journal
Abstract
In hybrid rocket combustion, the oxidizer swirl injection is frequently used to stabilize the combustion as the rotational velocity component affects the boundary layer flow. However, as the swirl strength increases, a problem arises where the combustion performance changes too much. Thus, this study attempts to control the low frequency instability while minimizing the change in combustion performance by adapting attenuated swirl injection with fuel insert used in reference [7]. To this end, a series of experimental tests were performed by varying swirl intensity and the location of the fuel insert. In the tests, the occurrence of combustion instability and combustion performance were closely monitored. The results confirmed that combustion instability was successfully suppressed at the condition of the swirl angle 6 degree and the location of fuel insert 310 mm. And, the changes in combustion pressure, O/F ratio, and fuel regression rate were found as minimal compared to the baseline case. Also the results reconfirmed that the formation of positive coupling between two high frequency oscillations in 500 Hz band, combustion pressure(p') and heat release oscillation(q'), is the necessary and sufficient condition of the occurrence of low frequency instability.
Keywords
Hybrid Rocket; Low Frequency Instability; Fuel Insert; Swirl Injection; Coupling Status;
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Times Cited By KSCI : 1  (Citation Analysis)
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