• 대한기계학회논문집B
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• 제35권8호
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• pp.815-823
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• 2011

다공성 물질 내부의 연소 현상은 저발열량 연료의 연소 및 연소열의 재생을 위한 수단으로 다양한 형태로 산업현장에 응용되고 있다. 하지만 다공성 물질 내부에서의 연소 현상은 직접적인 관찰이 힘들다는 점과 다공성 물질의 복잡한 내부 구조로 인해 매우 제한적인 연구가 진행되어 왔다. 본 연구에서는 복잡한 다공성 물질의 구조 내부에서의 화염의 안정화 특성에 관한 이해를 위해 내부 관찰이 가능하도록 다수의 석영판으로 구성된 다중채널 형태의 모형 연소기를 제안하고 이를 이용한 간단한 실험 결과를 제시한다. 그리고 이러한 다중채널내부 화염의 안정화에 관한 간단한 기초해석 모델을 제안한다. 다수의 채널 내부에 형성된 화염은 채널간의 열전달에 의해 화염의 공간 분포가 변화하고 그 결과로 연소기 내부의 가연한계에 변화가 발생한다. 채널의 재료 특성 및 당량비에 따른 가연한계의 변화를 제시하였으며, 이 결과는 다공성 연소기 내부화염의 이해에 도움될 것이다.

• 한국연소학회:학술대회논문집
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• 대한연소학회 2003년도 제27회 KOSCO SYMPOSIUM 논문집
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• pp.287-298
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• 2003

A numerical investigation of a catalytically stabilized thermal (CST) combustor was conducted for a multi-channel catalyst bed, and both the catalyst bed and thermal combustor were simultaneously modeled. The numerical model handled the coupling of the surface and gas reaction in the catalyst bed as well as the gas reaction in the thermal combustor. The behavior of the catalyst bed was investigated at a variety of operating conditions, and location of the flame in the CST combustor was investigated via an analysis of the distribution of CO concentration. Through parametric analyses of the flame position, it was possible to derive a criterion to determine whether the flame is present in the catalyst bed or the thermal combustor for a given inlet condition. The results showed that the maximum inlet temperature at which the flame is located in the thermal combustor increased with increasing inlet velocity.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2011년도 제37회 추계학술대회논문집
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• pp.187-199
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• 2011

본 연구는 희박 예혼합 연소기에서 연소실과 연료-공기 혼합부의 공진모드의 관계가 연소불안정에 어떤 영향을 미치고 있는지에 대하여 실험적으로 확인한 연구이다. 다체널 동압측정을 통하여 각각 위치에서 동압의 모드와 각 센서들간의 phase를 분석하여 연소불안정의 원인을 규명할 수 있었다. 연소실의 길이와 혼합부의 길이를 음향학적 경계로 일치시켜 연소불안정 특성을 확인해 보았을 때 두가지 서로 다른 연소불안정 모드를 확인할 수 있었는데 저주파 연소불안정 특성은 화염의 열방출 섭동과 연소실의 공진모드에 기인하며, 고주파 영역대의 연소불안정 현상은 혼합부의 길이를 변경하였을 때 발생하는 또 다른 불안정 현상임을 실험적으로 확인할 수 있었다.

• 한국연소학회지
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• 제18권2호
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• pp.1-7
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• 2013

Flame stabilization characteristics of premixed flames in narrow annular coaxial tubes (NACT) were investigated experimentally. The NACT burner was proposed as a model of a cylindrical refractory burner, and it was made of quartz tubes. Flame stabilization conditions affected by the characteristic length of the burner was investigated with the variation of the equivalence ratio and the flow rates. Flame behaviors in narrow spaces could be directly observed. Conclusively, more wide flame stabilization conditions could be obtained at the case of the decreased channel scale. A flame instability, such as combustion noise was detected concerned with the flame oscillation observed at the surface of multi channel stage. Some flame propagation characteristics had complicated tendencies that may exist in practical porous-media combustors. Therefore, this NACT burner can be a basic configuration for the development of flame stabilization model in porous media combustor, and it will enhance our understanding about the behavior of flames in meso-scale combustion spaces.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2003년도 제20회 춘계학술대회 논문집
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• pp.91-93
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• 2003

A comprehensive numerical study is carried out to investigate for the understanding of the flow evolution and flame development in a supersonic combustor with normal injection of ncumally injecting hydrogen in airsupersonic flows. The formulation treats the complete conservation equations of mass, momentum, energy, and species concentration for a multi-component chemically reacting system. For the numerical simulation of supersonic combustion, multi-species Navier-Stokes equations and detailed chemistry of H2-Air is considered. It also accommodates a finite-rate chemical kinetics mechanism of hydrogen-air combustion GRI-Mech. 2.11[1], which consists of nine species and twenty-five reaction steps. Turbulence closure is achieved by means of a k-two-equation model (2). The governing equations are spatially discretized using a finite-volume approach, and temporally integrated by means of a second-order accurate implicit scheme (3-5).The supersonic combustor consists of a flat channel of 10 cm height and a fuel-injection slit of 0.1 cm width located at 10 cm downstream of the inlet. A cavity of 5 cm height and 20 cm width is installed at 15 cm downstream of the injection slit. A total of 936160 grids are used for the main-combustor flow passage, and 159161 grids for the cavity. The grids are clustered in the flow direction near the fuel injector and cavity, as well as in the vertical direction near the bottom wall. The no-slip and adiabatic conditions are assumed throughout the entire wall boundary. As a specific example, the inflow Mach number is assumed to be 3, and the temperature and pressure are 600 K and 0.1 MPa, respectively. Gaseous hydrogen at a temperature of 151.5 K is injected normal to the wall from a choked injector.A series of calculations were carried out by varying the fuel injection pressure from 0.5 to 1.5MPa. This amounts to changing the fuel mass flow rate or the overall equivalence ratio for different operating regimes. Figure 1 shows the instantaneous temperature fields in the supersonic combustor at four different conditions. The dark blue region represents the hot burned gases. At the fuel injection pressure of 0.5 MPa, the flame is stably anchored, but the flow field exhibits a high-amplitude oscillation. At the fuel injection pressure of 1.0 MPa, the Mach reflection occurs ahead of the injector. The interaction between the incoming air and the injection flow becomes much more complex, and the fuel/air mixing is strongly enhanced. The Mach reflection oscillates and results in a strong fluctuation in the combustor wall pressure. At the fuel injection pressure of 1.5MPa, the flow inside the combustor becomes nearly choked and the Mach reflection is displaced forward. The leading shock wave moves slowly toward the inlet, and eventually causes the combustor-upstart due to the thermal choking. The cavity appears to play a secondary role in driving the flow unsteadiness, in spite of its influence on the fuel/air mixing and flame evolution. Further investigation is necessary on this issue. The present study features detailed resolution of the flow and flame dynamics in the combustor, which was not typically available in most of the previous works. In particular, the oscillatory flow characteristics are captured at a scale sufficient to identify the underlying physical mechanisms. Much of the flow unsteadiness is not related to the cavity, but rather to the intrinsic unsteadiness in the flowfield, as also shown experimentally by Ben-Yakar et al. [6], The interactions between the unsteady flow and flame evolution may cause a large excursion of flow oscillation. The work appears to be the first of its kind in the numerical study of combustion oscillations in a supersonic combustor, although a similar phenomenon was previously reported experimentally. A more comprehensive discussion will be given in the final paper presented at the colloquium.

• 한국연소학회지
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• 제18권3호
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• pp.24-30
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• 2013

Flame stabilization characteristics of premixed flames in an annular coaxial 5-tubes burner (AC5TB) were investigated experimentally. The AC5TB was made of five quartz tubes, and the flame stabilization conditions in that burner were investigated with the variation of equivalence ratio and the flow velocities. Flame behaviors inside of narrow annular tubes could be observed directly. Overall flame stabilization conditions were similar to that of the previous study, while the flame behaviors and structures were different mainly due to the controlled uniform distribution of the velocities in channels. Flame flashback conditions were thought to be governed by the competition between heat release rate, heat loss and heat recirculation in each channel. Stationary flames at a fixed location were compared in its velocity distribution and burned gas temperature across the channel. This AC5TB can be a basic configuration for the development of flame stabilization model of porous media combustors, and it will help understand about the real behavior of flames in meso-scale combustion spaces.

• 대한기계학회논문집B
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• 제35권6호
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• pp.633-640
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• 2011

본 연구에서는 고온의 미소농도구배 조건에서의 에지화염의 안정화 및 화염 강도 변화를 실험적으로 관찰하였다. 실험 연소기는 크게 혼합기가 투입되는 슬롯과 석영 채널 및 채널 내부 가열을 위한 추가적인 예혼합 연소기로 구성되어 있다. 실험의 정확성을 위해 각 경계 조건에 대한 정량적인 검증 절차가 수행되었다. 결론적으로 연료 농도 구배의 정량적인 제어와 질소 희석비율을 조절하여 고온의 조건에서도 에지화염을 임의의 위치에 안정화 시킬 수 있었다. 에지화염 내부에 존재하는 확산화염의 화염 강도가 채널 내부의 온도증가에 따라 증가하고 질소의 희석비율 증가에 따라 감소하는 것을 보였다. 연료에 따른 화염 강도 변화를 살펴본 결과 프로판의 경우가 메탄에 비해 강도 변화율이 큰 것을 알 수 있었다.