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This work is licensed under a Creative Commons Attribution-NonCommercial 4.0 International License
Article
Author(s)
Lukas Werling, Felix Lauck, Dominic Freudenmann, Nicole Röcke, Helmut Ciezki and Stefan Schlechtriem
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DOI:10.17265/1934-8975/2017.12.001
Affiliation(s)
German Aerospace Center (DLR), Institute of Space Propulsion, Im Langen Grund, Hardthausen 74239, Germany
ABSTRACT
Regarding the research on alternatives
for monopropellant hydrazine, several so called green propellants are currently under investigation
or qualification. Aside others, the DLR Institute of Space Propulsion investigates a N2O/C2H4 premixed green propellant. During the research activities, flashback from the rocket combustion chamber into
the feeding system has been identified as a major challenge when using the propellant mixture. This paper shows
the results of ignition experiments conducted in a cylindrical, optical accessible ignition chamber.
During the ignition and flame propagation process, pressure, temperature and high-speed video data
were collected. The high speed video data were used to analyze the flame propagation speed. The obtained
propagation speed was about 20 m/s at ignition, while during further propagation
of the flame speeds of up to 120 m/s were measured. Additionally, two different porous materials
as flame arresting elements were tested:
Porous stainless steel and porous bronze material. For
both materials Peclet numbers for flashback
were derived. The critical Peclet number for the sintered bronze material was around
20, while for the sintered stainless steel the critical Peclet number seems to be
larger than 40. Due
to the test results, sintered porous materials seem to be suitable as flashback arresters.
KEYWORDS
Green rocket propellants, ignition, flame flashback, N2O, C2H4, premixed gases, flashback arresters, porous materials.
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