• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.11a
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• pp.30-30
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• 2000

일반적인 소형 고체로켓의 모터 내에는 연료 첨가제로써 알루미늄이 함유되는데, 연소 시 산화된 이 성분은 액적 상태로 이동하여 노즐부내에 이상유동장을 형성시킨다. 이러한 산화알루미늄입자는 노즐벽면에 충돌, 점착하여 기계적, 열적 에너지전달을 일으키며 노즐벽면의 삭마를 유발시키는 한편, 가스유동과의 속도 차, 온도차로 인해 저항요소로 작용하면서 노즐의 추력 성능 손실에 간접, 직접적인 원인이 된다.(중략)

• Journal of the KSME
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• v.35 no.7
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• pp.620-637
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• 1995

이 글에서는 유동층소각로와 관련된 기술적 사항을 정리하고자 한다. 일부 교과서적인 내용이 서술되어 있으나, 자세한 이론적 고찰보다는 현상적인 이해에 중점을 두고, 실제 유동층 소각로와 관련된 분야에서 연구를 수행하는 연구자들과의 토론 및 설계시 고려하여야 할 사항들을 간략히 포함한다. 일반적으로 유동층은 효울적인 화학반응로로서 주로 이용되고 있으나, 이 글에서는 환경 및 에너지분야와 일정한 관계가 있는 폐기물 소각로 및 석탄연소로로서의 유동층의 응용에 초점을 맞추고 있다. 우선 환경 및 에너지산업의 현황을 이해함으로써 유동층의 핵심적 역할 담당 가능성을 밝힌다. 그리고 소각로의 종류 및 유동층의 역사와 응용에 대하여 각략히 설명 한다. 여타의 소각로와는 다른 특성인 기포유동특성 및 유동화에 대하여 논함으로써 유동층에 대한 기본현상을 파악한다. 유동층 소각로의 중요한 기능인 공해물질의 노내처리에 대하여 논 의하고, 기포유동층보다 효율적인 순환유동층 및 가압유동층의 특성과 역할을 소개한다. 그리고 유동층 소각로의 예로 일본의 폐기물소각로 및 하수슬러지 소각로개발 현황을 소개한다. 최종 적으로는 유동장 소각로의 실제 설계과장에 대하여 간략히 해설한다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.59-63
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• 2005

The experimental study has been conducted to investigate the effect of the recirculation zone on the multi-slot film cooling in the ramjet combustor. The recirculation zone which is generated by the protrusion tip on the entrance of the coolant flow path affects on the first slot. Velocity fields, dimensionless temperature fields and adiabatic film cooling effectiveness on the downstream wall of the slot exit are measured. The results show that the film cooling performance is rapidly decreased after the slot exit by the share layer and high turbulence intensity between separated flows and coolant flows.

• Journal of the korean Society of Automotive Engineers
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• v.14 no.1
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• pp.47-53
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• 1992

대도시의 자동차 배기가스에 의한 대기오염문제는 날로 심화되어 가고 있으며, 그 규제 역시 매 우 엄격해지고 있다. 배기가스의 문제는 연소실내에서의 고효율연소에 의해 개선될 수 있으며, 이 를 위해서는 혼합가스 생성장치에서의 잘 미립화된 혼합가스의 생성에 관한 미시적 연구가 필수 적이다. 본 연구에서는 범용 유체 유동해석, 프로그램을 이용하여 Butterfly밸브 주위에서의 공기 의 흐름현상을 예측하였으며, 밸브의 손실계수(Kv)를 실험치와 비교하여 보았다. 또한 압축성과 비압축성 유체 유동해석의 비교, Residual Mass(R. M)의 최적치 정의에 의한 CPU 시간의 최소 화, Numerical Grid Size의 해석결과에 미치는 영향 등에 관해 알아보았다.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.37 no.2
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• pp.161-170
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• 2013

The flow and combustion characteristics in a premixed swirl combustor with a double cone burner are numerically analyzed to adopt a swirler model. The internal recirculation zone formed at the burner exit can be realized by a swirler with inner and outer diameters of 56 and 152 mm, respectively, and accordingly, the flow rate and radial velocity were determined. To select the tangential velocity, swirl and recirculation angles are introduced. A tangential velocity of 40 m/s produces an internal recirculation zone similar to that in a combustor. At the liner exit, the errors in temperature and velocity are 2.8% and 0%, respectively, and they are negligibly small. However, NOx emissions are underestimated by 67% in the numerical results obtained using the swirler model. Although considerable quantitative errors are induced by the swirler model, it can be useful numerical model for the EV burner because it can approximately simulate the essential flow and combustion characteristics in a premixed swirl combustor with a double cone burner and it is expected to make combustion analysis efficient in a gas turbine combustor with complex geometries.

• Journal of the Korean Society of Propulsion Engineers
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• v.17 no.5
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• pp.70-79
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• 2013

The isothermal flow structure and mixing characteristics of a hybrid/dual swirl jet combustor for micro-gas turbine (MGT) were numerically investigated. Location of pilot burner, swirl angle and direction were varied as main parameters with the identical thermal load. As a result, the variations in location of pilot nozzle, swirl angle and direction resulted in the significant change in turbulent flow field near burner exit, in particular, center toroidal recirculation zone (CTRZ) as well as turbulent intensity, and thus the flame stability and emission performance might be significantly changed. With the comparison of experimental results, the case of swirl angle $45^{\circ}$ and co-swirl flow including optimum location of pilot burner were chosen in terms of the flame stability and emissions for the development of hybrid/dual swirl jet combustor.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.189-193
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• 2005

Thermal effect of finite-rate chemistry on linear combustion stability and film cooling effect are investigated in sample rocket engine. The flow variables required to evaluate stability limits are obtained from CFD data with finite-rate chemistry adopted in three dimensional chamber. Major flow variables are affected appreciably by finite-rate chemistry and thereby, the calculated stability limits are modified. It is found that finite-rate chemistry contributes to stability enhancement in thermal point of view. And film cooling also has the effect of combustion stabilization.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.996-999
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• 2011

The flow and combustion dynamics in the ignition and ramjet sustainer phase of an integrated rocket-ramjet(IRR) engine are investigated. The physical model includes the entire engine flowpath, from the freestream in front of the inlet to the exit of the exhaust nozzle. The flowfield obtained from a rocket booster study is used as the initial condition for the present analysis, so that the complete operation history of the engine can be obtained. The analysis for the primary factor governing flame propagation during the ignition and the key mechanisms for driving and sustaining the flow oscillations are performed.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.2
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• pp.75-81
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• 2006

Thermal effect of finite-rate chemistry on linear combustion stability and film-cooling effect are investigated in sample rocket engines. The flow variables required to evaluate stability limits are obtained from CFD data with finite-rate chemistry adopted in three dimensional chamber. Major flow variables are affected appreciably by finite--rate chemistry and thereby, the calculated stability limits are modified. It is found that finite-rate chemistry contributes to stability enhancement in thermal point of view. And film cooling also has the effect of combustion stabilization.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.1
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• pp.114-123
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• 2002

A supersonic rocket plum flowfield of kerosene/liquid-oxygen based propulsion system has been analysed using the Reynolds-averaged Navier-Stokes equations coupled with a 9-species 14-reaction finite-chemistry model. The result were compared with chemically frozen flow solution to investigate the effect of finite-rate chemistry on the plume flowfield. The computations were performed using a commercial CFD software, FLUENT 5. The finite-rate chemistry solution exhibited higher temperature caused by the reactions within the nozzle. All the chemical reactions within the plum were dominated only in the shear layer and behind the barrel shock reflection region where the temperatures are high and the effect of finite-rate chemical reactions on the flowfield was found to be insignificant. However, the present plume computation including the finite-rate chemical reaction within the plume has revealed major reactions occurring in the plum and their reaction mechanisms.