• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1999.10a
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• pp.30-30
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• 1999

추진기관의 연소실과 같이 큰 열부하를 받는 경우 막냉각은 연소실을 보호하기 위해서 사용되는 대표적인 냉각기법이다. 막냉각의 성능을 극대화하기 위해서는 냉각유체를 2차원 슬롯을 통해서 분사시키는 것이 가장 효율적이지만 여러 가지 이유 때문에 실제 적용에 있어서는 슬롯입구 부근에 작은 구멍을 만들어 이로부터 분사되는 유체를 통해서 냉각시키게 된다. 본 연구에서는 주어진 덕트에서 분사율, 분사방법, 슬롯의 형상에 따른 슬롯 출구에서의 유동장 및 온도장 측정과 함께 물질전달 방법을 이용하여 슬롯 립(slot lip) 내벽에서 자세한 국소 열/물질전달계수를 구하였다. 분사율 0.5와 1.0에 대해서 주유동과 같은 방향으로 분사시켜줄 경우와, 유동을 제한시켜 주고 이차유동의 방향을 각각 주유동과 같은 방향과 반대방향으로 분사시키는 방법에 대하여 실험하였으며, 슬롯 입구에 경사슬롯을 설치하여 냉각유체를 분사시키는 방법에 대해서 실험하였다.

• Transactions of the Korean Society of Mechanical Engineers
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• v.16 no.8
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• pp.1552-1565
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• 1992

Three dimensional numerical calculations were carried out for two different combustion chambers with the offset valve in order to investigate the swirl and the squish effects on the flow fields. The modified K-.epsilon. turbulence model considering the change of the density under the condition of the rapid compression and expansion of the pistion was used. During the compression process, it was found that the squish flow which controls the subsequent combustion process was produced due to the piston bowl in the bowl piston type combustion chambers but not for the flat piston type. The swirl velocity close to the solid body rotation was maintained in the flat piston type combustion chambers, but for the bowl piston type a resulting from the change of the solid body rotation was generated in the radial-circumferential plane. For the swirl ratio effect, as the swirl ratio increases, it was found that a large and strong vortex was generated in the radial-circumferential plane of bowl piston type combustion chambers because of the strong inward flows from the combustion chamber wall. These computational results were compared with the results of LDA measurement.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.40 no.7
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• pp.417-427
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• 2016

This paper is the first investigation of the steady flow characteristics of an SI engine with a semi-wedge combustion chamber as a function of the port shape. For this purpose, the planar velocity profiles were measured at the 1.75B position by particle image velocimetry. The flow patterns were examined with both a straight and a helical port. Two swirls were observed up to 4 mm valve lift with the straight port and up to 2 mm with the helical one; however, only one swirl was present after these lifts. The flow characteristics changed suddenly between 4 and 5 mm lift in the straight port; on the other hand, the change with lift was gradual with the helical port - the transition points between flow regimes were different with the port shapes. In addition, the centers of the swirls were relatively far from the cylinder center so that the effect of eccentricity may not be negligible at 1.75B, regardless the shape. The eccentricity values with the straight port were especially high - over 0.5 for all lifts. Finally, real velocities were found to be much lower than those predicted by the assumption of ISM evaluation, with the profiles differing qualitatively as well.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1999.10a
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• pp.29-29
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• 1999

점화천이(Ignition transient)는 일반적으로 점화 신호를 주는 순간부터 로켓모타가 평형상태(equilibrium) 혹은 설계 작동조건에 도달했을 때까지의 시간 구간으로 정의되며, 이 시간 동안에 높은 연소실 압력 증가율에 의한 동연소효과(dynamic burning effect)와 연소가스의 높은 cross-flow 속도에 의한 침식연소효과(erosive burning effect)에 의해 추진제의 연소증가 현상을 일으킨다. 이런 두가지의 증가된 연소효과와 더불어 과대하게 설계된 점화기로부터 유입되는 질량유량에 의해 연소실을 채우는 시간(Chamber filling) 중에 압력 과잉(pressure overshoot)이 나타난다 그러나 동연소효과 및 침식연소효과의 경우 추진제의 종류와 로켓모타의 형상 등에 의해서 복합적으로 나타나는 현상이기 때문에 모든 로켓모타에 대해서 공통으로 적용할 수식이나 방정식이 존재하지 않는다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.11a
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• pp.13-13
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• 2000

램제트 엔진에 대한 기초 연구로서 양쪽 대칭의 공기 흡입구를 갖는 2차원 형태의 램제트엔진 연소기를 제작하여 그 특성을 분석하였다. 실험은 흡입공기의 연소실내 유입각도와 연소실내의 도움 위치에 따른 연소실 형상을 바꾸어가며 연소기내의 유동특성을 살펴보았다. 이를 위하여 고속 유동장의 2차원 평면 속도 분포를 측정할 수 있는 two color PIV 기법을 개발하였다. 이 기법은 다른 색의 두 레이저빔을 사용하여 방향성의 문제를 해결하며, 이미지의 색 분리에 따른 거의 완벽한 cross-correlation이 가능하며 높은 single-to-noise 비를 얻게 됨으로써 dynamic range의 증가가 가능해지며, 조사 영역 안에 존재해야 하는 입자 쌍의 수가 줄어들게 된다.(중략)

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.232-235
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• 2011

A typical unsteady internal ballistic analysis model was developed to take account the erosive burning of a solid rocket motor. The variance of local velocity and pressure along grain surface were analyzed by using the continuity and momentum equation. The coefficients of erosive burning were drew from comparing experiment data with analysis. It was investigated that the grain shapes of propellant affect the erosive burning.

• Transactions of the Korean Society of Automotive Engineers
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• v.11 no.1
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• pp.55-63
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• 2003

In a diesel engine, air-fuel mixture formation and ignition delay period have great influence on the performance of engine. Their main factors are combustion chamber shape, fuel injection system. air volume, air flow and so on. So, the combustion process in the cylinder is complex because of many factors which have direct and indirect effects on it. In this study, we take into consideration of scavenging pressure and scavenging temperature that are hewn as the main factor to the combustion process of two-stroke D.1. diesel engine. It is taken a picture of the combustion flame process for combustion chamber of re-entrant type and cylindrical type. So, it is applied to the basis data of combustion chamber design from an image analysis.

• Transactions of the Korean Society of Automotive Engineers
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• v.7 no.8
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• pp.99-106
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• 1999

The present study deals with the effect of combustion chamber shape on in-cylinder soot oxidation characteristics of a D.I . diesel engine. The analysed combustion chambers were a toroidal and a reentrant with a projection(Complex). The two-color method was used to measure in-cylinder flame temperature and KL value which is approximately proportional to the soot amount along the optical path. In addition, heat release rate was calculated from the in-cylinder pressure data. From these investigations , the soot oxidation of the reentrant and the complex which were strengthen squish flows went worse in late combustion period under heavy-load operation compared to that of the toroidal at retarded fuel injection timing . It might be the cause of the flame holding that squish lip depress the outflow of flame from the bowl to the entire combustion space.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.10a
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• pp.8-8
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• 1998

액체 추진제를 사용하는 연소기관내의 연소 불안정 현상에 대하여 수치적인 해석을 수행하였다 비정상 다차원 다상 유동장에 대한 Eulerian-Lagrangian 방법에 기반을 두고 수학적으로 모델 하였으며 속도-압력-밀도에 대한 결합메커니즘은 개선된 PISO 알고리즘을 사용하여 처리하였다. 연소실의 기하학적 형상 및 추진제의 분무조건이 액체 연료 추진기관의 연소 불안정 현상에 미치는 영향을 체계적으로 해석하였으며 액체 추진제의 증발 특성이 연소 불안정 현상의 Driving Mechanism에 미치는 영향을 상세히 분석하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.231-235
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• 2009

The mainly objectives of this study was a combustion dynamics and instability characteristics in a model dump type combustor which is scale down of GE 7FA+e DLN 2.6 gas turbine combustor with running at Seo-Inchon combined cycle power plant. Model gas turbine injector has 2-stage swirl vane and it's reduced 1/3 size of the original one. The shape of plenum and combustor were designed for similar acoustic characteristics. As the result, this research have been shows the peak frequency of model combustor was changed quarter-wave mode to Helmholtz resonator mode in plenum and longitudinal mode in dump combustor at unstable flame conditions caused by the different of combustor temperature and fuel-air mixture distributions.