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길태옥(Taeock Khil),임지혁(Ji-Hyuk Im),윤영빈(Youngbin Yoon) 한국추진공학회 2007 한국추진공학회지 Vol.11 No.1
The review of the liquid propellant rocket engine is presented. The combustion instabilities which were discovered on solid and liquid propellant rocket engines in 1930, have occurred on propulsion devices, such as gas turbine, ramjet, scramjet and rocket, and thus a study on the combustion instability became necessary. However, this problem has not been solved yet. Therefore, we investigated causes and mechanisms of the combustion instability and surveyed the efforts of solving combustion instability in various countries for developing stable liquid propellant rocket engines.
알루미늄(Al) 금속연료 조성의 추진제를 이용한 무노즐 부스터 개발
길태옥(Taeock Khil),정은희(Eunhee Jung),이기연(Kiyeon Lee),류태하(Taeha Ryu),이형진(Hyoungjin Lee) 한국추진공학회 2017 한국추진공학회지 Vol.21 No.4
The study for the performance characteristics of the nozzleless booster used in ramjet booster was carried out. Performances related to pressure and thrust for nozzleless booster are lower than classical motor those because of absence of convergent and divergent sections of nozzle. To solve this problem, it developed a high-performance propellant with maximum impulse density included Al as metal fuel. Using the nozzleless booster casted the propellant, ground test of it was carried out by varying the length-to-diameter ratio (L/D ratio) of the propellant. Specific impulse of nozzleless booster was limited to about 75 percents of its value compared with that of classical motor adapted nozzle in the same propellant and propellant length and will be estimated approximately 85 percents of its value compared with that of classical motor at same average pressure in terms of the curve fitting by our test results.
저주파 압력섭동 범위 내에서의 단일 스월 인젝터의 진폭-위상 특성 연구
길태옥(Taeock Khil),정연재(Yunjae Chung),윤영빈(Youngbin Yoon) 한국추진공학회 2010 한국추진공학회지 Vol.14 No.2
Generally, combustion instability is generated by the mutual coupling between the heat release and the acoustic pressure in the combustor. On the occasion, the acoustic pressure generates the oscillation of the mass flow rate of propellant injected from injector, and this oscillation again affects combustion in the combustor. So, the dynamic characteristics of the injector have been studied to control combustion instability using injector itself in Russia from 1970’s. In order to study injector dynamics, a mechanical pulsator for forced pressure pulsation is produced and the method to quantify the mass flow rate of the propellant that is oscillating at the exit of the injector is developed. With the pulsator and the method, pulsating values of the mass flow rate, pressure, liquid film thickness, and axial velocity generated at the exit of the simplex swirl injector are measured in real time. And phase-amplitude characteristics of each parameter are analyzed using these pulsating values acquired at the exit of the simplex swirl injector.
조성호(Seongho Cho),길태옥(Taeock Khil),박구정(Gujeong Park),윤영빈(Youngbin Yoon) 한국추진공학회 2010 한국추진공학회 학술대회논문집 Vol.2010 No.11
극저온 액체 질소 제트 유동의 아임계 및 초임계 특성을 파악하기 위한 실험을 수행하였다. 단일 제트 분사기를 고압 챔버 내에 장착하여 제트의 주위기체압력, 분사기 형상 및 유동 조건의 영향을 조사하였다. 실험 결과로부터 아임계 조건과 초임계 조건에서의 제트의 특성 변화를 관찰하였으며, 주위기체압력이 대기압일 경우 유동 내에 섭동이 발생함을 파악하였다. 분사기 형상에 따른 유동 변화 또한 파악하였다. Cold flow injection test was conducted to investigate the characteristics of cryogenic liquid nitrogen jet at sub to supercritical condition. Single jet injector element was installed in high pressure chamber to investigate the effect of ambient pressure around the jet, injector geometry and flow conditions. Experimental results showed obvious differences between jet characteristics under subcritical and supercritical condition. Effect of injector inlet shape also was investigated.
김경무(Kyungmoo Kim),길태옥(Taeock Khil),홍명표(Myungpyo Hong),도은성(Yeunsung Doh) 한국추진공학회 2016 한국추진공학회지 Vol.20 No.1
The propellant mixer for charging of solid rocket motors is one of the most important equipments. For the propellant mixer is export control item, it’s hard to purchase it directly from abroad. The Mixer was developed locally to overcome export control which precludes us from import. This paper includes the introduction for general mixers and the process of mixer development progressed by LIGNex1. Finally, The mixer is verified the performance using measurements of clearance between blade-blade and blade-bowl and flow simulation with ADINA.
스월 인젝터에서 접선방향 유입구 조건이 내부유동의 안정성에 미치는 영향에 대한 연구
김성혁(Sunghyuk Kim),길태옥(Taeock Khil),조성호(Seongho Cho),윤영빈(Youngbin Yoon) 한국추진공학회 2008 한국추진공학회지 Vol.12 No.6
Many theoretical and experimental studies have been conducted to investigate elements of swirl injector hydrodynamics, such as variations in liquid film thickness or air core diameter. From these studies, some theoretical relationships have been established through an approximate analytical solution of flow hydrodynamics in a swirl nozzle. However, experimental studies on elements such as the stability of internal flow have not produced conclusive results. In this study, the stability of the internal flow under tangential entry conditions was examined by visualizing the formation of the air core in the swirl chamber and measuring the liquid film thickness in the orifice.
김경무(Kyungmoo Kim),길태옥(Taeock Khil),류태하(Taeha Ryu) 한국추진공학회 2017 한국추진공학회지 Vol.21 No.2
Nozzleless booster is one of the applicable components for integral rocket ramjet (IRR). In order to predict nozzleless solid booster performance, the simplified theoretical analysis was applied for L/D=5, 6, 7, 9, 11, and 13. Al-HTPB and Zr-HTPB propellant with a high metal content were used to increase the hardness because of the combustion gas flow effect. It was found that the trends between the simplified theoretical analysis and experiments were similar.