• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.10a
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• pp.54-54
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• 2002

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2001.11a
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• pp.70-72
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• 2001

• Proceedings of the Korea Air Pollution Research Association Conference
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• 1991.05a
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• pp.74-76
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• 1991

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2001.04a
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• pp.42-42
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• 2001

• Cement Symposium
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• s.49
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• pp.69-74
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• 2022

• The Inventors News
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• no.15
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• pp.5-6
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• 2003

한국직능단체총연합회 제3차 한$\cdot$중$\cdot$일 직능경제인 서울대회 개최 - 한국, 지식재산권 관련 국제기구 의장에 잇따라 진출 - 노벨상 시상식의 최연소 초대손님 - 특허출원에서의 무한동력 - 보성, 영광, 금산 등 일부 지역 상표 등록 길 열려 - 디지털 화상디자인 의장 출원 줄을 잇고있다

• Journal of the Korean Society of Combustion
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• v.7 no.3
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• pp.32-36
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• 2002

A numerical study was carried out to investigate combustion phenomena in a model Scramjet engine, which had been experimentally studied at the University of Tokyo using a high-enthalpy supersonic wind tunnel. The main airflow was Mach number 2.0 and the total temperature of hot flow was 1800K. Equivalence ratio was set to be 0.26 which is higher than that of experiment to investigate the effect of strong precombustion shock. The results showed that self-ignition occurred at the rear bottom wall of the combustor and combined with the shear layer flame between fuel jet and main airflow. Then, precombustion shock was generated at the step location and reversely enhanced the mixing and combustion process behind the shock. Due to the high equivalence ratio, the precombustion shock moved upstream of the step compared with that of experiment.

• Journal of the Korean Society of Combustion
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• v.12 no.2
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• pp.1-9
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• 2007

This paper describes numerical efforts to investigate combustion characteristics of HyShot scramjet combustor, where gaseous hydrogen is transversely injected into a supersonic cross flow. The corresponding altitude, angle of attack, and equivalence ratio are 35-23 km, $0^{\circ}$, and 0.426 respectively. Two-dimensional simulation reasonably predicts combustor inner pressure distribution and reveals periodic combustion characteristics of HyShot scramjet combustor. Altitude effects are also investigated and the strength of flow instability and subsonic boundary layer thickness affect the combustion efficiency according to altitudes. Frequency analyses provide the flow instability effects on the turbulent combustion in HyShot scramjet combustor.

• 한국연소학회:학술대회논문집
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• 2005.10a
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• pp.261-267
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• 2005

A comprehensive DES quality numerical analysis has been carried out for reacting flows in constant-area and divergent scramjet combustor configuration with and without a cavity. Transverse injection of hydrogen is considered over a broad range of injection pressure. The corresponding equivalence ratio of the overall fuel-air mixture ranges from 0.167 to 0.50. The work features detailed resolution of the flow and flame dynamics in the combustor, which was not typically available in most of the pervious studies. Much of the flow unsteadiness is related not only the cavity, but also to the intrinsic unsteadiness in the flowfield. The interactions between the unsteady flow and flame evolution may cause a large excursion of flow oscillation. The roles of the cavity, injection pressure, and heat release in determining the flow dynamics are examined systematically.

• 한국연소학회:학술대회논문집
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• 2005.10a
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• pp.156-161
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• 2005

Two and Three dimensional numerical simulations have been carried out to understand the combustion characteristics of LNG-fueled gas turbine combustor for power generation. Focus of the study was given to the influences of different fuel composition of imported and domestic natural gases with the flow conditions selected from the gas turbine operation data. Reacting flow characteristics of the swirl stabilized natural gas combustor were understood from the comparison of the two-dimensional and three-dimensional results. The thermal influences of different natural gases were very small and the fuel composition and flow rate were considered to be tuned well.