• Korean Journal of Air-Conditioning and Refrigeration Engineering
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• v.12 no.1
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• pp.50-58
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• 2000

Experiments were carried out to obtain the effects of nozzle configuration and jet to jet spacing on the heat transfer characteristics of single line of circular water jets impinging on a constant heat flux plane surface. The nozzle configurations are Cone type, Reverse cone type and Vertical circular type, and the nozzle arrays are single jet(nozzle dia. 8 mm), 1 row of 3 jets and 1 row of 5 jets. Jet velocities ranging from 3m/s to 8m/s were investigated for the nozzle to target plate spacing of 80 mm. For the Cone and Reverse cone type nozzle arrays, the average Nusselt number of 1 row of 5 jets was larger than that of 1 row of 3 jets at Re$_{D}$<45000, but that of 1 row of 3 jets was larger than that of 1 row of 5 jets at $Reo\le45000$. For the Vertical circular type nozzle, however, the average Nusselt number of 1 row of 3 jets was larger than that of 1 row of 5 jets at all jet velocities. In the condition of fixed mass flow rates, the maximum heat transfer augmentation was obtained for 1 row of 5 jets and was over 2 times larger than that of the single jet for all nozzle configurations. The nozzle configurations that produce the maximum average Nusselt number are as follows: For 1 row of 3 jets, the Vertical circular type at $Reo\le45000$ and the Reverse cone type at $Reo\le45000$. But, they are the Reverse cone type at Re$_{D}$<55000 and the Vertical circular type at$Reo\le55000$ for 1 row of 5 jets.

• Transactions of the Korean hydrogen and new energy society
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• v.25 no.1
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• pp.47-58
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• 2014

The characteristics of flame shape, laminar burning velocity, emissions and heat flux of stagnation point in premixed impinging jet flame of syngas fuel with 10% hydrogen content were experimentally investigated. Also, the adiabatic temperature and burning velocity are calculated by Chemkin package with USC-II mechanism. The equivalence ratios(0.8~5.0) and dimensionless separation distance(2.0~5.0) with fixed Reynolds number(1800) are main parameters in this work. Different flame shapes and colors were observed for different impingement conditions. The experimental results of burning velocity by flame surface area have a consistent with previous works and numerical simulation of this work. The inner flame length could be predicted with the ratio of mixture velocity and burning velocity from a simple formulation by the laminar burning velocity definition. It has been observed that the heat fluxes at stagnation point are directly affected by the flame shape including the separation distance. The emission results in impinging flame of syngas fuel show that the characteristics of $NO_x$ emission traced well with adiabatic temperature trend and CO emission due to fuel rich condition increased continuously with respect to the equivalence ratio.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.04a
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• pp.44-45
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• 2002

일반적으로 노즐이나 오리피스로부터 방출되는 초음속 단일 자유제트 유동의 경우, 제트내부에서 발생하는 충격파 시스템이나, 제트경계의 형상 그리고 제트코어의 길이 및 초음속 영역의 길이 등은 종래의 연구로부터 비교적 잘 알려져 있다. 이들 연구에 의하면, 제트의 압력비가 어느 정도 증가하게 되면, 노즐 하류에서 제트내부에는 마하 디스크가 발생하게 되며, 제트유동은 압축과 팽창을 반복하는 구조로 된다. 또 노즐 출구로부터 마하 디스크까지의 거리와 마하 디스크의 직경 등은 노즐의 압력비의 함수로 주어진다고 알려져 있다.

• Proceedings of the SAREK Conference
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• 2004.06a
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• pp.22-22
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• 2004

• Journal of the Korea Institute of Military Science and Technology
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• v.16 no.5
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• pp.712-717
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• 2013

The gas management system for a vertical launching system must be safely managed within a ship. The plenum and uptake are capable of containing and surviving a full-burning restrained firing without loss of gas management integrity. To secure the safety, the pressure characteristics with a supersonic under-expanded jet on a gas management system are numerically investigated using computational fluid dynamics. The results of present analysis and the preliminary design of the gas management system are described in this paper.

• Transactions of the Korean Society of Automotive Engineers
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• v.2 no.2
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• pp.124-131
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• 1994

자동차엔진의 연소과정에 상사하는 밀폐정적연소실을 주연소실과 대향 2개 부연소실로 분할하고 오리피스로 연결하였다. 이때 부연소실로부터 주연소실로 분출하는 대향분출염 연소에 의한 질소산화물 배출저감특성을 연소방식, 연소실형상 그리고 연료종류를 변경한 수종의 실험으로 조사하였다. 질소산화물농도, 연소실 최고압력, 화염전파과정의 고속도슐리렌사진 가시화를 수행한 결과, 대향분출염 연소방식을 도입하연 연소실의 중앙부공간이 상대적으로 넓은 경우에 고부하운전과 동시에 질소산화물의 배출량도 저감할 수 있었다. 그러나 연료의 종류는 질소산화물생성에 매우 영향이 적었다.

• International Journal of Fluid Machinery and Systems
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• v.5 no.2
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• pp.72-90
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• 2012

A computational study is reported on flow and heat transfer characteristics from five rows of circular air jets impinging on a concave surface with four rows of effusion holes. The effects of exit configurations of spent air and the arrangement of jet orifices and effusion holes for a jet Reynolds number of 7500 is investigated. In all, eight cases are studied and a good qualitative correlation is found among their flow patterns, pressure variations and heat transfer distributions.

• 한국연소학회:학술대회논문집
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• 2012.04a
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• pp.245-246
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• 2012

The possibility that self-ignition can be generated near an obstacle is high in practical applications such as a hydrogen car. In this paper, experimental investigations were suggested to understand the effects of a wall on self-ignition phenomena through high-speed images. The results showed that the existence of a wall could not change the ignition phenomena itself irrespective of wall height and burst pressure. However, when a strong flame was induced in the tube, a wall could promote the flame stabilization.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.04a
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• pp.18-18
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• 1998

평판에 충돌하는 초음속 세트에 관한 연구는 수직/단거리 이·착륙기의 발진, 미사일 발사시스템, 다단계 로켓 분리 등 실제적인 분야에 응용되고 있으며 고온의 충돌제트와 화염에 의한 가열문제와 관련된 산입분야에서도 많은 연구가 이루어지고 있다. 과소팽창하는 초음속 제트가 평판에 충돌할 때 Barrel shock, exhaust gas boundary, Mach disk, contact surface, reflected shock, plate shock, stagnation bubble 등 매우 복잡한 유동 구조가 표면에 나타나는데 이것은 평판으로부터 반사된 shock과 free jet의 충격파 구조 사이에서의 상호간섭 때문이다. 노즐로부터 방출되는 고속, 고온가스가 주변 장비 등에 부딪힐 때 발생하는 이러한 복잡한 간섭현상의 연구는 관련 주변장비 설계 및 상황예측에 필수적인 자료를 제공하며 이해를 도와준다.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.30 no.3 s.246
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• pp.215-221
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• 2006

A stereoscopic particle tracking velocimetry (SPTV) technique based on the 2-frame hybrid particle tracking velocimetry (PTV) method was developed. The expansion of 2D PTV to SPTV is facilitated by the fact that the PTV method tracks individual particle centroids. To evaluate the performance and measurement accuracy of the present SPTV technique, it was applied to flow images of rigid body translation and synthetic standard images of jet shear flow and impinging jet flow. The data processing routine and measurement uncertainty of the SPTV technique are compared with those of conventional stereoscopic particle image velecimet.y (SPBV). In addition, the centroid translation effect of 2D particle image velocimetry (PIV) is defined and its effect on SPIV measurements is discussed. Compared to the SPIV method, the SPTV technique has inherited merits of concise and precise velocity evaluation procedures and provides better spatial resolution and measurement accuracy.