Experimental Investigation of Transient Injection Phenomena in Rocket Combusters at Vacuum with Cryogenic Flash Boiling

نویسندگان

چکیده

Abstract The substitution of the toxic hydrazine in current high-altitude rocket engines like upper stages or reaction control thrusters by green propellants is a major key driver technology development propulsion systems. Operating these kind at leads to sudden pressure drop liquid during their injection into combustion chamber with near-vacuum atmosphere prior ignition. resulting superheated thermodynamic state causes fast and eruptive evaporation which called flash boiling. degree atomisation important for successful ignition secure operation engine. cryogenic test bench DLR Lampoldshausen enables systematical experimental characterization boiling due its ability adjust parameters temperature, geometry. Several campaigns nitrogen (LN2) were performed using two optical diagnostic methods: First, LN2 spray patterns visualised means high-speed shadowgraphy and, secondly, we determined droplet size velocity distributions strongly sprays help laser-based Phase Doppler system (PDA). data generated within measurement provide defined boundary conditions as well broad base numerical modelling e.g. publications [8, 9].

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ژورنال

عنوان ژورنال: Fluid mechanics and its applications

سال: 2022

ISSN: ['0926-5112', '2215-0056']

DOI: https://doi.org/10.1007/978-3-031-09008-0_11