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연료과농 조건에서의 기체메탄-기체산소 반응물의 연소특성
강윤형(Yun Hyeong Kang),안현종(Hyun Jong Ahn),배창한(Chang Han Bae),김정수(Jeong Soo Kim) 한국추진공학회 2021 한국추진공학회지 Vol.25 No.6
A hot-firing test was conducted using gaseous-methane and gaseous-oxygen under highly fuel-rich condition as a prior study for the development of a liquid propellant small rocket engine. To compare combustion characteristics for various equivalence ratios, the oxygen flow rate was set to 12 g/s and the methane flow rate was changed according to the equivalence ratio. As a result, it was observed that the steady-state characteristic velocity obtained during the hot-firing test steeply rose in the latter part of each test: the difference between the former and the latter steady value was enhanced overall in proportion to the equivalence ratio. Based on this, the equivalence ratio range depending on the variational characteristics of the characteristic velocity could be divided into three combustion regimes.
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.
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.