• 한국대기환경학회지
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• 제34권5호
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• pp.651-658
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• 2018

Particulate matter (PM) emitted from fossil fuel-combustion facilities can be classified as either filterable or condensable PM. The U.S. Environmental Protection Agency (EPA) defined condensable PM as material that is in the phase of vapor at the stack temperature of the sampling location which condenses, reacts upon cooling and dilution in the ambient air to form solid or liquid in a few second after the discharge from the stack. Condensable PM passed through the filter media and it is typically ignored. But condensable PM was defined as a component of primary PM. This study investigates the change of condensable PM according to the variation in the sulfur dioxide of combustion gas. Domestic oil boilers were used as the source of emission ($SO_2$) and the level of $SO_2$ concentration (0, 50, 80, and 120 ppm) was adjusted by diluting general light oil and marine gas oil (MGO) that contains sulfur less than 0.5%. Condensable PM was measured as 2.72, 6.10, 8.38, and $13.34mg/m^3$ when $SO_2$ concentration in combustion gas were 0, 50, 80, and 120 ppm respectively. The condensable PM tended to increase as the concentration of $SO_2$ increased. Some of the gaseous air pollutants emitted from the stack should be considered precursors of condensable PM. The gas phase pollutants which converted into condensable PM should reduced for condensable PM control.

• 한국연소학회:학술대회논문집
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• 한국연소학회 2006년도 제33회 KOSCO SYMPOSIUM 논문집
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• pp.202-208
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• 2006

The purpose of this research is to model numerically the turbulent gas-particle flows in a rectangular chamber using Eulerian-Eulerian Method. A computer code using the ${\kappa}-{\varepsilon}-Ap$ two-phase turbulence model is developed for the numerical study. This code and the Eulerian multiphase model in FLUENT were used for the numerical simulations of the two-phase flow in a rectangular chamber. The numerical results calculated by the two different turbulent gas-particle codes have shown that the ${\kappa}-{\varepsilon}-Ap$ model results in a stronger diffusion of the flow momentum in the gas-particle turbulence interaction than the Eulerian multiphase model in FLUENT.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2011년도 제37회 추계학술대회논문집
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• pp.763-768
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• 2011

최근 대두되고 있는 바이오가스(Biogas)를 이중 희박 예혼합 가스터빈 연소기에 적용하기 위한 연구로써, 기존 개발된 실물형 이중 희박 예혼합 연소기 버너헤드에 바이오가스 조성을 모사한 $CO_2$ 희석 연료를 사용하여, 가스터빈 연소기의 연소불안정에 미치는 영향을 연구하였다. 이중 스월이 적용된 이중화염에서 연료분배율(Pilot fuel mass fraction)에 따라 화염구조가 상이하며 이에 따라 연소장의 온도분포와 연소불안정 특성이 결정된다. 동압신호와 phase-resolved $OH^*$ 이미지를 통해 연료분배율 변화와 $CO_2$ 희석률 증가에 따른 연소불안정 크기 감소와 그 경향을 알 수 있었다. $CO_2$ 희석에 의해 열방출 섭동의 크기가 감소하고 화염속도가 감소하며 이에 따라 화염면의 팽창 즉, 체적의 증가로 인해 연소불안정이 감소되는 것을 실험을 통해 확인하였다.

• 한국연소학회:학술대회논문집
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• 한국연소학회 제26회 KOSCO SYMPOSIUM 논문집
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• pp.27-32
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• 2003

Diesel-Fueled HCCI(Homogeneous Charge Compression Ignition) Engine is an advanced combustion process explained as a premixed charge of diesel fuel and air is admitted into the cylinder and compression ignited. It has possibility to reduce NOx by spontaneous auto-ignition at multiple points that allows very lean combustion resulting in low combustion temperatures. Also PM could be reduced by the premixed combustion and no fuel-rich zones. But HCCI couldn't be realized because of the difficulties in vaporizing the diesel, control of combustion phase directly. To solve these problems, new fuel injection strategy, explained as the pilot fuel injection to promote ignition near TDC following the main fuel injection at the extremely advanced timing, is applied during the compression ratio is varied from 18.9:1 to 27.7:1 This is not a pilot fuel to promote the ignition but also the direct control method of the combustion phase. Experimental result shows the pilot fuel injection promote the ignition and the compression ignition of the HCCI engine is achieved as compression ratio becomes higher. Also there is an optimal pilot fuel injection timing for the HCCI combustion. NOx is reduced more than 90% compared to DI-Diesel case but PM and THC emission needs more investigation.

• 대한기계학회논문집B
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• 제22권7호
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• pp.1022-1029
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• 1998

The relation of the inlet fuel distribution, velocity, and overall equivalence ratio to the stability of a lean burning no-swirl dump combustor was examined. Premixed or partially premixed natural gas was introduced into the air stream, which flowed to the dump region through an annular inlet pipe. Inlet air was preheated upto 400 deg.C. Combustion instability was observed to occur at higher value of equivalence ratio (> 0.6) as the degree of unpremixedness was increased. Instabilities exhibited a dominant frequency of ~ 500 Hz, which corresponded to a half wave mode of combustor. CH chemiluminescence and pressure fluctuations were in-phase when combustion instabilities occurred. Acetone LIF images revealed that there was a strong fuel concentration gradient across the inlet annulus. Phase resolved OH LIF images showed that inlet fuel distribution was affected by the combustion instabilities.

• Journal of Mechanical Science and Technology
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• 제18권7호
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• pp.1246-1257
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• 2004

The objective of this paper is to characterize dynamic pressure traces measured at self-excited combustion instabilities occurring in two combustion systems of different hardware. One system is a model lean premixed gas turbine combustor and the other a fullscale bipropellant liquid rocket thrust chamber. It is commonly observed in both systems that low frequency waves at around 300㎐ are first excited at the onset of combustion instabilities and after a short duration, the instability mode becomes coupled to the resonant acoustic modes of the combustion chamber, the first longitudinal mode for the lean premixed combustor and the first tangential mode for the rocket thrust chamber. Low frequency waves seem to get excited at first since flame shows the higher heat release response on the lower frequency perturbations with the smaller phase differences between heat release and pressure fluctuations. Nonlinear time series analysis of pressure traces reveals that even stable combustion might have chaotic behavior with the positive maximum Lyapunov exponent. Also, pressure fluctuations under combustion instabilities reach a limit cycle or quasi-periodic oscillations at the very similar run conditions, which manifest that a self-excited high frequency instability has strong nonlinear characteristics.

• 한국자동차공학회논문집
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• 제9권4호
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• pp.18-26
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• 2001

OSKA engine was developed to remove the dense core of injection sprays. The engine uses impinging spray on a small pip, which spray after impinging is broken into smaller drops and disperses into fee space in chamber. In this paper the pip size is analyzed to give more dispersion of spray and fuel vapor. The gas phase is modelled by the Eulerian continuum conservation equations of mass, momentum, energy and fuel vapour fraction. The liquid phase is modelled following the discrete droplet model approach in Lagrangian form, and the droplet wall interaction is modelled as a function of the velocity normal to impaction lands. The droplet distributions, vapor fractions and gas flows are analyzed for various injection pressure cases. Numerical results indicate that the land diameter of 5.6mm has the best performance of spray dynamics and vaporization in the test sizes.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2011년도 제37회 추계학술대회논문집
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• pp.293-298
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• 2011

덕티드로켓 추진기관에 사용되는 불완전연소 가스발생기 및 유량조절시스템을 설계/제작하고 연소시험을 수행하여 유량조절특성을 분석하였다. 추진시스템 설계요구조건을 바탕으로 가스발생기를 설계하고 불완전연소용 고체연료 조성을 개발하여 연소시험을 수행, 일반적인 고체추진기관 해석모델을 통한 예측결과와 상당한 차이의 실험결과로부터 불완전 연소가스를 위한 별도의 해석모델이 요구됨을 확인하였다. 유량조절 시험을 통해 밸브각도에 따른 가스발생기 압력변화 특성을 확인하였고, 출구면적에 따라 유일하게 결정되는 유출계수로부터 가스발생기 압력을 예측하는 방법을 도출하였다.

• 한국추진공학회지
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• 제14권2호
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• pp.46-53
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• 2010

본 연구에서는 하이브리드 추진 연소에서 산화제의 상(Phase)에 따른 연소특성 변화를 연구하였다. 산화제는 $GN_2O$와 $LN_2O$를 사용하고 고체연료는 HDPE(High Density PolyEthlene)를 적용하여 연소실험을 수행하였고, 상에 따른 고체연료의 후퇴율과 압력선도, 연소효율의 변화 등을 조사하였다. $LN_2O$를 적용할 경우 액체 산화제의 기화에 필요한 잠열이 화염에서 발생되는 연소에너지에 비해 무시할 정도로 작아 $GN_2O$를 산화제로 사용했을 때의 고체연료 후퇴율과는 큰 차이가 없었지만, 추진 성능효율이 낮아짐을 확인하였고, 액체 산화제의 유량이 증가할수록 산화제의 기화에 필요한 열전달 증가로 인 해 연소 불안정성이 커짐을 확인하였다.

• 한국가스학회:학술대회논문집
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• 한국가스학회 2005년도 춘계학술대회 및 특별심포지움
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• pp.228-228
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• 2005