• Journal of the Korean Society of Propulsion Engineers
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• v.17 no.3
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• pp.9-14
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• 2013

Combustion tests were conducted for a hydrogen-fueled Mach 5 scramjet engine model using a blow-down facility. No fuel and two fuel flow rate cases were tested for two different model configurations. Time history of the wall static pressures inside the model and their time-averaged spatial distribution were used for the analysis of the flow and combustion characteristics. For shorter model, supersonic combustion was occurred for both of the fuel flow rate cases. For longer model, supersonic combustion was occurred for less fuel case, whereas thermal choking and subsonic combustion were occurred for more fuel case. Intake started even for this subsonic combustion case.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.129-132
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• 2012

In this study, combustion performance tests of a multi coaxial-swirl injector engine using hydrogen peroxide and kerosene as propellants were performed to evaluate combustion characteristic according to mixture ratio between 6.0 and 9.0 by criterion of designed(7.6). Combustion characteristics were evaluated by calculated characteristic exhaust velocity($c^*$) and pressure fluctuation. Test results showed that the combustion efficiency was over 90% and the pressure fluctuation was within 1%.

• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.1
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• pp.29-41
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• 2021

The PID controller with fin angle and thrust as control input was designed based on the aerodynamic data of scramjet system. Flight simulation following a given trajectory which strike the target point after climb and cruise with constant dynamic pressure was conducted. After that, the required thrust for the climb and cruise was calculated and the required fuel flow rate for the hydrogen fuel dual mode scramjet combustor was analyzed. The combustor analysis of this study which conducted on integrated model of independently developed inlet, combustor, nozzles and external aerodynamic models, laying the foundation for the integrated design of the air breathing hypersonic system.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.4
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• pp.26-33
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• 2006

The use of high-density propellants can provide performance advantages in space launch vehicles by allowing an improved structural ratio due to smaller propellants tanks. The Jet A-1 fuel is currently used in Korean space launch vehicle development and it has lower density than other advanced hydrocarbon fuels such as RP-1 or RG-1. In this paper, the results of hydraulic and combustion tests conducted for the two newly developed densified hydrocarbon fuels are presented and they are compared with the results of Jet A-1. Conclusively, the two densified hydrocarbon fuels presented equivalent or even higher combustion performance compared to the Jet A-1 and the performance difference was found to be more obvious in the injector of external mixing.

• Journal of the Korean Society of Propulsion Engineers
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• v.20 no.6
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• pp.1-10
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• 2016

For the active control of a combustion instability, a change should be made in pressure fluctuation or heat release fluctuation using an acoustic driver or a secondary fuel injection. Also, to determine the location and timing of a secondary fuel injection, one needs to know the distribution of heat release fluctuation under combustion instability. In the present research, the distribution of heat release fluctuation has been experimentally measured by changing hydrocarbon fuel, inlet velocity, equivalence ratio, and acoustic forcing condition. It was confirmed that heat release fluctuation with regards to vortex shedding was significantly affected by the $Damk{\ddot{o}}hler$ number. Under the cases of the $Damk{\ddot{o}}hler$ number above approximately 4 - 5, hot spot region was generated in the leading edge of vortex and cold spot region was in the trailing edge. On the contrary, the cases of the $Damk{\ddot{o}}hler$ number below 3 showed the opposite trend.

• Journal of the Korean Institute of Gas
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• v.17 no.5
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• pp.8-14
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• 2013

Hydrogen-natural gas blends(HCNG) engine is optimizing technology of performance and emission characteristics with use of hydrogen's fast flame speed and wide flammability limit. As lean-burn limit is extended, the improvement in thermal efficiency and harmful emissions can be achieved. However, the extension of lean-burn limit under a wide open throttle operation point could be realized with the increase in boosting capacity in a lean-burn engine with turbo-charging system. In the present study, the power output characteristics of HCNG engine with turbo-charger change is assessed and feasibility of the increase in boosting capacity is evaluated. The turbo-charger design with high efficiency at higher flow rate rather than higher boosting pressure makes efficient operation possible at relatively rich mixture condition.

• 한국연소학회:학술대회논문집
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• 1997.06a
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• pp.77-87
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• 1997

The axisymmetric Navier-Stokes model together with detailed chemical kinetics and variable transport properties has been applied to analyze the effects of the multidimensional flow on the flame characteristics in the nitrogen-diluted hydrogen counterflow nonpremixed flame. Computations are performed for two nozzle exit area-averaged velocities. Effects of multidimensional flow and strain rate on the near-extinction structure of the highly diluted hydrogen flames are discussed in detail.

• Proceedings of the Korea Air Pollution Research Association Conference
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• 2003.11a
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• pp.339-340
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• 2003

최근 들어서 환경유해물질이 인체에 미치는 영향에 대한 관심이 커지고 있다. 특히 환경 중에 존재하는 발암성 물질에 대한 연구가 활발히 진행되면서 이들 물질이 인체에 미치는 위해성이 밝혀지고 있다. 다환방향족탄화수소(Polycyclic Aromatic Hydrocarbons, PAHs) 는 환경에 존재하는 중요한 발암물질이자 돌연변이 유도체이다. PAHs는 화석연료의 불완전 연소 등에 의해 발생되고, 대표적인 오염원으로는 석탄 연소, 자동차, 가정 난방 등이 있다. (중략)

• Proceedings of the Korea Society for Energy Engineering kosee Conference
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• 2003.05a
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• pp.627-631
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• 2003

본 연구는 폐기물로부터 CO와 H$_2$가 주성분인 합성 가스를 얻는 방법에 대한 것으로, 주요 반응으로는, 폐기물 내의 탄소, 수소 성분과 외부에서 공급된 산소와의 발열반응인 부분연소 반응과 부분 연소 반응에 의해 생성된 이산화탄소와 물이 미 반응 탄소와의 흡열 반응인 가스화 반응으로 구성된다.(중략)

• Journal of ILASS-Korea
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• v.7 no.3
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• pp.7-11
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• 2002

Comparison of the combustion characteristics of methane-air and gasoline-air mixtures has been conducted experimentally by a spherical bomb technique. The results indicate 1) the burning velocity of gasoline is slightly higher than that of methane, but their basic behavior of combustion characteristics, positive dependence on temperature and negative one on pressure, are the same, and 2) 20 vol.% addition of hydrogen to methane enhances the burning velocity by about 30%, but does not come to reverse the tendency of pressure dependence to that of pure hydrogen.