• 한국추진공학회지
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• 제20권4호
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• pp.40-49
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• 2016

본 연구의 목적은 저선회 모델 연소기에서 저선회 연소의 특성을 확인하는 것이다. 이를 위해 선회각도에 따른 화염의 형상 및 안정화 영역, 배기성능에 대한 평가가 실험적으로 수행되었다. 저선회 연소의 큰 특징은 화염이 부상되어 존재하게 되는데, 이러한 부상화염은 확대유동과 예혼합 화염의 전파특성이 절묘하게 결합되어 발생하게 된다. 본 연소기에서 이러한 부상화염의 특징을 속도 유동장을 통하여 확인하였으며 화염을 가시화하여 나타내었다. 가시화된 화염은 열용량과 당량비에 따라 분류하였다. 선회각도의 변화에 따른 연구를 통해 선회각도만으로도 희박 가연한계를 확장시킬 수 있음을 보였다. 또한 선회각도가 증가할수록 혼합이 향상되고 체류시간이 짧아져 NOx와 CO의 배출이 감소되는 것으로 확인되었다.

• 한국추진공학회지
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• 제24권3호
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• pp.1-11
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• 2020

본 연구에서는 lab-scale 젤로켓모터를 이용하여 액상 케로신 연료와 이를 젤화 시킨 젤 케로신 연료의 연소시험을 수행함으로써, 각 연료별 연소실 정압특성 및 동압특성에 대해 분석하였다. 액상 케로신과 젤 케로신의 정압, 특성속도 및 특성속도 효율은 예상외로 큰 차이를 보이지 않음을 확인하였다. 그러나 액상 케로신과 젤 케로신의 동압 특성을 비교한 결과, 특정 고주파수 영역에서 젤 케로신의 압력 진폭이 액상 케로신 대비 증가하는 것을 확인하였다. 이는 젤 추진제의 고유 연소 메커니즘에 기인한 특성으로 여겨지며, 이들 압력 섭동 진폭이 추후 젤로켓모터의 고주파 연소불안정에 영향을 미치는 주요 인자로 적용될 가능성이 클 것으로 판단되었다.

• 한국연소학회:학술대회논문집
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• 한국연소학회 2000년도 제20회 KOSCO SYMPOSIUM 논문집
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• pp.9-15
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• 2000

Characteristics of lifted flames for highly diluted propane and methane with nitrogen in coflowing air is experimentally investigated. In case of propane, for various fuel mole fractions and jet velocities, three distinctive types of flames are observed; nozzle attached flames, stationary lifted flames, and oscillating lifted flames. When fuel jet velocity is much smaller than coflow velocity, the base of nozzle attached flame has a tribrachial structure unlike usual coflow difusion flames. Based on the balance mechanism of the propagation speed of tribrachial flame with flow velocity, jet velocity is scaled with stoichiometric laminar burning velocity. Results show that there exists two distinctive lifted flame stabilization; stabilization in the developing region and in the developed region of jets depending on initial fuel mole fraction. It has been found that lifted flame can be stabilized for fuel velocity even smaller than stoichiometric laminar burning velocity. This can be attributed to the buoyancy effect and flow visualization supports it. Lifted flames are also observed for methane diluted with nitrogen. The lifted flames only exist in the developing region of jet.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년도 제31회 추계학술대회논문집
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• pp.82-85
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• 2008

액체로켓엔진에서 고주파 연소불안정의 제어를 위해 연소 안정화 장치인 음향공을 적용하여, 제한된 공간에서 유동장의 특성과 설계인자에 따른 감쇠효과를 연구하였다. 연소 불안정을 모사하기 위하여 제한된 공간에 압력 진동 장치를 이용하여 공진을 발생시켜, 음향공의 장착에 따른 감쇠 효과를 측정하였다. 유동장의 특성중 하나인 유속을 변화시키기 위하여 유량을 변화시켰으며, 설계인자로는 음향공 오리피스의 직경과 길이를 변화시켜 연구를 수행하였다. 유동장 하에서의 음향공 장착에 따른 감쇠효과를 확인 하였으며, 오리피스 길이와 직경이 작을 경우 유속 증가에 따라서 음향공의 튜닝이 오른쪽(고주파수)으로 이동하는 현상을 확인하였다.

• 대한기계학회논문집B
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• 제27권1호
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• pp.32-38
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• 2003

Staged combustion, such as air- and fuel-staging, is a relatively well-known technique fur reduction of NOx emission and used in combination with other techniques nowadays. However, the design variables are still selected depending upon operating conditions. There are many variables tested to investigate the NOx emission characteristics fur changing of fuel or air velocity, swirl intensity, and staging ratio of air and fuel in multi-staged burner. In air-staging case, the fuel-rich condition of the primary combustion zone is very helpful to reduce NOx emission and its range is known to be restricted by the increase of carbon monoxide. However, in many cases carbon monoxide level is not too high to be restricted operating condition. So we tried to expand the equivalence ratio range to the richer condition in the primary combustion zone and certificate the function of each burner component and its contribution to the overall NOx production.

• International Journal of Aeronautical and Space Sciences
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• 제18권2호
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• pp.270-278
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• 2017

This paper describes development procedure and verification test results of a bi-propellant thruster using hydrogen peroxide and kerosene. The design thrust of the thruster is about 500 N and six swirl type coaxial injectors were used. The passage type manifolds were employed for the injector head to reduce the response time. The passage was designed to minimize stagnation points and recirculation region to ensure uniform flow distribution and sufficient cooling performance through flow analysis using Fluent. A catalytic igniter using hydrogen peroxide was installed at the center of the injector head. The propellant feeding and spray characteristics were confirmed by hydraulic tests. Combustion tests were performed on design and off-design points to analyze combustion characteristics under various mixture ratio conditions. The combustion test results show that combustion efficiency was over 95 % and chamber pressure fluctuation were less than 1.5 % under all test conditions.

• 한국수소및신에너지학회논문집
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• 제23권6호
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• pp.619-627
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• 2012

This study was experimentally investigated on the effects of spring stiffness applied to linear compressor chambers. The springs prevented piston head from colliding with engine cover, stored the kinetic energy and regenerated the kinetic energy. The linear engine has two combustion chambers and four compressor chamber. The combustion chamber bore size was 30 mm, maximum stroke was 31 mm and effective stroke volume was 25.45 cc respectively. The spring stiffness was varied such as 0, 0.5, 1.00, 2.9 and 14.7 N/mm. The linear engine was fueled with premixed LPG (propane 99%) and air by pre-mixture device. As an experimental result, The stroke, piston velocity and the piston frequency were increased by high spring stiffness. Also, thermal efficiency was grown. because the increased stroke made the higher compression ratio. In conclusion, electric power and efficiency were improved.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 추계학술대회논문집B
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• pp.65-70
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• 2001

OH radical and NOx have been measured in a methane-air partially premixed flame using PLIF technique to define preheated air combustion characteristics. The temperature of mixture is determined by 300K, 400K, 600K and 800K below the auto-ignition temperature respectively. Flame height increases as equivalence ratio increased. As initial enthalpy is supplied, the radius of flame was increased and much amount of yellow flame in rich equivalence ratio was observed. This is due to the faster burning velocity. Also initial oxidization begins earlier as the initial temperature of mixture increased. It means that height of premixed flame front decreased. This phenomenon can be observed OH PLIF image. The qualitative analysis of OH concentration in the PLIF image shows that overall OH concentration increases with equivalence ratio and the initial temperature of mixture increased. At the preheating temperature goes up, axial gradient of OH concentration is less steep than that of lower temperature condition. This may identify that combustion reacts continuously, so preheated air combustion can evade the local heating and make high temperature indiscriminately in the overall reaction zone.

• Journal of Mechanical Science and Technology
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• 제15권1호
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• pp.88-97
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• 2001

The present study numerically investigates the fuel-air mixing characteristics, flame structure, and pollutant emission inside a double-swirler combustor. A PSR(Perfectly Stirred Reactor) based microstructural model is employed to account for the effects of finite rate chemistry on the flame structure and NO formation. The turbulent combustion model is extended to nonadiabatic flame condition with radiation by introducing an enthalpy variable, and the radiative heat loss is calculated by a local, geometry-independent model. The effects of turbulent fluctuation are taken into account by the joint assumed PDFs. Numerical model is based on the non-orthogonal body-fitted coordinate system and the pressure/velocity coupling is handled by PISO algorithm in context with the finite volume formulation. The present PSR-based turbulent combustion model has been applied to analyze the highly intense turbulent nonpremixed flame field in the double swirler combustor. The detailed discussions were made for the flow structure, combustion effects on flow structure, flame structure, and emission characteristics in the highly intense turbulent swirling flame of the double swirler burner.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2003년도 제20회 춘계학술대회 논문집
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• pp.266-269
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• 2003

액체로켓 엔진 연소 시 발생하는 연소 가스는 고온, 고속의 유동특성을 갖는다. 이러한 유동특성에 견딜 수 있는 연소시험 화염유도로 제작에 필요한 기초 자료를 얻고자 본 실험을 수행하였고, 연소 가스에 물을 분사하여 냉각된 연소가스의 온도 및 압력을 측정하였다. 동시에 열화상 카메라장비를 통해 온도를 측정하고 센서측정 데이터와 비교 분석한 결과 화염유도로에 적용 가능한 온도데이터를 획득하였고 물분사기 성능과 설치를 위한 구조적 강도를 예측할 수 있었다.