Experimental Investigation of Self-Excited Combustion Instabilities in a LOX/LNG Rocket Combustor
نویسندگان
چکیده
Two types of combustion instabilities were observed in a multi-injector research combustor with liquid oxygen and liquefied natural gas (LOX/LNG) propellants operating at conditions similar to an upper stage rocket engine. The first was identified as excited tangential acoustic mode the chamber can be explained by coupling LOX injectors, mechanism previously tests propellants. other type is characterized longitudinal oscillations peak-to-peak amplitudes least 40% mean pressure. Analysis test data suggests that sudden upstream displacement lifted flame may trigger for second instabilities.
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ژورنال
عنوان ژورنال: Journal of Propulsion and Power
سال: 2021
ISSN: ['1533-3876', '0748-4658']
DOI: https://doi.org/10.2514/1.b38289