• Journal of the Korean Society of Propulsion Engineers
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• v.21 no.1
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• pp.63-71
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• 2017

Liquid methane ($CH_4$)/oxygen ($O_2$) bipropellants have been recently considered as a next-generation propellant due to eco-friendly and non-toxic properties, low cost and high performance. In this study, the combustion characteristics of gaseous $CH_4/O_2$ nonpremixed coflow flames in a model combustor with variation of internal pressure are investigated through measuring the combustion stability limits and visualizing flames. Results show that the combustion stability limits are extended and the reaction region is widened with increasing internal pressure of the combustion chamber for fuel-rich condition.

• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.6
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• pp.45-52
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• 2021

A hot-firing test was conducted using gaseous-methane and gaseous-oxygen under highly fuel-rich condition as a prior study for the development of a liquid propellant small rocket engine. To compare combustion characteristics for various equivalence ratios, the oxygen flow rate was set to 12 g/s and the methane flow rate was changed according to the equivalence ratio. As a result, it was observed that the steady-state characteristic velocity obtained during the hot-firing test steeply rose in the latter part of each test: the difference between the former and the latter steady value was enhanced overall in proportion to the equivalence ratio. Based on this, the equivalence ratio range depending on the variational characteristics of the characteristic velocity could be divided into three combustion regimes.

• Journal of Advanced Marine Engineering and Technology
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• v.35 no.6
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• pp.814-819
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• 2011

An Oxy-fuel combustion has been studied in order to reduce exhaust emissions and fuel consumption. The flow and flame behaviors are analyzed with focal length variation in one-focussing oxygen burner introduced in this study. Oxygen is supplied into the center of the nozzle, methane fuel is into the outer nozzle of the center, and then oxygen is again supplied into the outer of the fuel nozzle. The test conditions are 5 focal lengths of 100mm to 500mm. The mixing behaviors and temperature distributions are analyzed. The result shows that the shorter the focal length is, the longer the mixing length becomes, and the flame width and length are the biggest in the case of 300mm.

• Journal of the Korean Society of Propulsion Engineers
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• v.21 no.2
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• pp.1-8
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• 2017

In order to analyze combustion characteristics of methane-oxygen diffusion flame in a model combustor, combustion experiments were carried out under various spray conditions of propellant scrutinizing combustion stability limit and flame shapes. As the propellant approached the theoretical equivalence ratio condition, a stable detached flame was observed even under high oxygen Reynolds number. And the length of the visible flame increased and the lift-off distance of the flame exhibited a tendency toward decrease. Due to the swirl effect of the propellant by the swirl-coaxial injector, a wide and short flame was produced. Thus, it may be appropriate to employ the swirl-coaxial injector in thrusters having a limited physical dimension.

• Journal of Energy Engineering
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• v.8 no.1
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• pp.34-47
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• 1999

본 연구에서는 촉매상에서 메탄의 산화시 발생되는 반응열을 이용하고 반응생성물과 미반응 메탄과의 개질반응에 의해 합성가스의 수율을 증대시키기 위하여 연소촉매와 개질촉매를 연속적으로 배치한 hybrid 촉매상에서 개질촉매에 따른 메탄의 부분산화반응의 반응 특성과 합성가스 수율에 미치는 영향을 관찰하였다. 메탄의 산화를 위해서 Pt-Rh/cordierite 촉매를 사용하였으며, 개질촉매로는 상업용 개질촉매인 R67, ICI46-1, 수성가스 전환반응촉매인 LX821 촉매와 6 wt% Ni/cordierite 촉매를 사용하였다. 실험결과 연소촉매와 개질촉매를 연속적으로 사용한 경우 메탄의 산화 과정에서 생성된 CO2 및 H2O가 미반응 메탄과의 개질반응 촉진으로 인하여 합성가스이 수율이 증가됨을 확인할 수 있었다. 이때 생성되는 합성가스의 H2/CO 몰비는 온도에 따라 감소하는 것으로 나타났으며, 80$0^{\circ}C$에서 촉매에 따라 2.2~2.8의 값을 가짐을 알 수 있었다. 개질촉매로 R67 및 Ni/cordierite 촉매를 사용하였을 경우 가장 높은 합성가스의 수율을 얻을 수 있었으며, 연소촉매와 개질촉매의 질량비는 1:1~1:2에서 가장 높은 수율의 합성가스를 얻을 수 있었다. 메탄과 산소의 몰비가 2:2에서 메탄의 전환율과 수소 수율이 가장 높게 나타났으며 메탄의 몰비 증가에 따라 감소되는 경향을 보였다.

• 한국연소학회:학술대회논문집
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• 2015.12a
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• pp.139-141
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• 2015

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.787-790
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• 2017

This study is a preliminary research on characterization of methane - oxygen combustion used in bipropellant thruster. The limit of combustion stability and flame shape of methane - oxygen non-premixed flame injected by shear coaxial injector in the model combustion chamber Experimental studies have been carried out. A direct image of the flame was photographed using a DSLR camera, and combustion characteristics and flame length were quantified through image post-processing. As a result, it was confirmed that the stabilized flame was generated at the stoichiometric ratio as the oxidizer Reynolds number ($Re_o$) was increased, and the length of the turbulent flame was increased under the same injector diameter condition.

• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.3
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• pp.89-100
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• 2021

This paper deals with the construction of a combustion test facility and preliminary tests for hot-firing tests of a methane engine. First, the combustion test facility for a 1 kN-class thrust chamber using liquid oxygen/gas methane as propellants was designed and built. Before hot-firing tests, the cold-flow tests of each propellant line and the ignition tests of torch igniter/afterburner were performed to verify propellant supply stability of the combustion test facility, operation of the control and measurement system, and successful ignition. Finally, a preliminary hot-firing test was conducted to measure the combustion efficiency, heat flux, and combustion stability of a thrust chamber prototype. The constructed combustion test facility will be helpfully used for basic research and development of methane engine thrust chambers.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.4
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• pp.70-80
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• 2019

Combustion tests using six bi-swirl coaxial injectors with different shapes and recess lengths were performed in a model combustion chamber capable of flame visualization. By utilizing gaseous methane and gaseous oxygen instead of actual propellants, the effects of injector design and experimental conditions on the flame structure and combustion stability were analyzed. It was found that not only the experimental conditions but also the injector geometry such as the recess length and orifice diameter had a considerable influence on the combustion stability. In addition, it was confirmed that the heat release pattern changed with the occurrence of combustion instability.

• Applied Chemistry for Engineering
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• v.9 no.6
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• pp.878-883
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• 1998

The methane combustion reaction was conducted over Pb-ZSM-5 catalysts. ZSM-5 synthesized at low temperature and atomospheric pressure was used as a support. The change of methane conversion with $SiO_2/Al_2O_3$ molar ratio was tested. The methane conversions of the synthesized Pb-ZSM-5 catalyst was compared with those of a commercial Pd-ZSM-5(PQ Co.) and $PdO/{\gamma}-Al_2O_3$. The methane conversion increased with the decrease in $SiO_2/Al_2O_3$ molar ratio. The combustion rate of methane also increased with the decrease in $SiO_2/Al_2O_3$ molar ratio. The synthesized Pb-ZSM-5 showed better methane conversion than that of the commercial one. It is found that a crucial factor in methane combustion reaction is oxygen adsorption strength on the catalysts.