액체 로켓 인젝터 내부 압력 보상을 위한 Effervescent 노즐의 설계 인자 및 분사 조건 연구

초록

This study investigates the application of effervescent nozzles to liquid rockets using a laboratory-scale twin fluids spray test system. Typically, rocket engines using a single liquid propellant control thrust by adjusting the mass flow rate, which is influenced by the spray differential pressure between the fluid pressure at the injector front and atmospheric pressure. As the differential pressure decreases, uneven atomization and combustion instability can occur. To address this issue, this research explores an effervescent nozzle that mixes gaseous and liquid propellants to maintain injection pressure. Experiments were conducted on eight different nozzle types with varying orifice and aerator sizes. The experimental results demonstrated internal pressure variations and differences in spray characteristics based on nozzle design, which were analyzed and discussed. if these injection characteristics are applied in the future, it is expected that they could also be utilized in eco-friendly alternative fuels such as Sustainable Aviation Fuel (SAF).

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