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소형로켓엔진에 적용된 스월 동축형 인젝터의 형상변수와 기체-액체 운동량 플럭스 비에 따른 분무특성
안현종(Hyun Jong Ahn),강윤형(Yun Hyeong Kang),김정수(Jeong Soo Kim) 한국추진공학회 2023 한국추진공학회지 Vol.27 No.1
To understand the atomization performance in gas-liquid swirl-coaxial injector applied to a small rocket engine, a cold-flow test was performed by varying the design parameters and supply condition of propellants. As the swirl-chamber diameter and the angle of the convergent section, which are design parameters of injector increased, the spray performance of the injector improved by increasing the swirl strength. In addition, as the gas-liquid momentum-flux ratio increased, the gas flow separated some of the droplets from the liquid film, and a gas-droplet mixture core was formed in the center of the spray sheet.
Slit-jet 노즐을 통과한 초음파 무화 에어로졸 화염에 정상초음파가 미치는 영향
안현종(Hyun Jong Ahn),강윤형(Yun Hyeong Kang),김정수(Jeong Soo Kim) 한국추진공학회 2020 한국추진공학회지 Vol.24 No.6
In liquid-fuel spray combustion, an experimental study was conducted to observe the effect of ultrasonic excitation on the ultrasonically-atomized liquid fuel flame by controlling pressure field through an ultrasonic standing wave. Flame of the ultrasonically-atomized kerosene aerosol was visualized by using a high speed camera, DSLR, and Schlieren photography. The amount of fuel consumed was obtained by a precise flow-rate measurement technique during combustion, through which the ratio of carrier gas (air) to fuel mass was able to be obtained, too. As a result, it could be found that the combustion reaction-rate of the liquid-fuel aerosol was increased by applying an ultrasonic standing wave to the secondary flame zone of the flame.
전단압과 배압 변화에 따른 캐비테이션 벤츄리 성능의 실험적 연구
안현종(Hyun Jong Ahn),강윤형(Yun Hyeong Kang),김정수(Jeong Soo Kim) 한국추진공학회 2021 한국추진공학회지 Vol.25 No.6
An experimental study was performed for a cavitating venturi supplying a constant rate of flow independent of downstream pressure fluctuations when providing liquid propellant. The venturi was designed and manufactured in order to figure out the performance of the cavitating venturi. Effects of the rear-end shape, upstream pressure, and back pressure on the ratio of downstream to upstream pressure of the venturi as well as the flow-rate were observed. As a result, critical pressure ratio of the venturi, which generally depends only on the configuration of the venturi, was kept at 0.74 regardless of the rear-end shape and the upstream pressure of the venturi.
특성길이 변화에 따른 200 N급 기체메탄-액체산소 소형로켓엔진의 성능 비교 분석
강윤형(Yun Hyeong Kang),안현종(Hyun Jong Ahn),김정수(Jeong Soo Kim) 한국추진공학회 2020 한국추진공학회지 Vol.24 No.6
Ground hot-firing tests were conducted to analyze the combustion performance according to the characteristic lengths 1.37 m, 1.71 m, and 2.06 m of the combustion chamber in 200 N-class GCH₄-LOx small rocket engine. Thrust, specific impulse, and characteristic velocity at the steady-state could be obtained as the key performance parameters of the rocket engine. The performance characteristics acquired through the test were compared and analyzed with the theoretical performance calculated from CEA analysis. Observation of the influence of characteristic length on the combustion performance indicates that an optimal characteristic length shall remain between 1.71 m and 2.06 m.