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http://dx.doi.org/10.6108/KSPE.2014.18.6.011

Visualization of Transient Ignition Flow-field in a 50 N Scale N2O/C2H5OH Thruster  

Kim, Dohun (Department of Aerospace and Mechanical Engineering, Graduate School of Korea Aerospace University)
Park, Jaehyeon (School of Aerospace and Mechanical Engineering, Korea Aerospace University)
Yu, Myunggon (School of Aerospace and Mechanical Engineering, Korea Aerospace University)
Lee, Kyungeun (School of Aerospace and Mechanical Engineering, Korea Aerospace University)
Koo, Jaye (School of Aerospace and Mechanical Engineering, Korea Aerospace University)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.18, no.6, 2014 , pp. 11-18 More about this Journal
Abstract
The combustion flowfield at the near-injector region of a 50 N scale $N_2O/C_2H_5OH$ thruster was visualized using shadowgraph technique. The explosive ignition was occurred at the design spray condition, and the expanding combustion gas quenched the flame immediately. Approximately after 83 ms from the initial ignition, the propellant spray was re-ignited, and the flame was stabilized after 23 ms elapsed. In the increased oxidizer flow rate condition, the transient pressure at the moment of ignition was smoother than explosive ignition, and the blow down phenomenon was not appeared in the same operating sequence. In addition, the flame was stabilized within 17 ms, and it is caused by improved propellants mixing before ignition.
Keywords
Combustion Flowfield; Visualization; Nitrous Oxide; Ethanol;
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