• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.730-733
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• 2017

An ignitor for the initiation of burning propellants becomes one of the most critical components for the operation of liquid rocket engines. The important phenomenon of the igniter is thermoacoustic resonance. This paper mainly includes experimental results on thermoacoustic resonance phenomenon from distance between nozzle and resonance tube. The ultimate goal is to develop an ignitor capable of multiple ignitions based on research results about the usage of the thermoacoustic resonance phenomenon.

• 한국가시화정보학회:학술대회논문집
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• 2006.12a
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• pp.48-54
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• 2006

A visualization study of flow characteristics in a mixer using multi-nozzle bubbling was performed. The mixer is filled with liquid glycerin (dynamic viscosity = $1000mPa{\cdot}$ s at $25^{\circ}C$) and convective mixing is induced by air bubbles generated from 9 orifices installed on the bottom of the mixer. To visualize the flow field, PIV (Particle Image Velocimetry) system consisting of 532nm Nd:YAG laser, $2k\times2k$ CCD camera and synchronizer is adopted. The bubbles generated with uniform size and frequency form bubble stream, and bubble streams rise vertically without interaction between bubble streams. Mixing efficiency is affected by the height of bubbler and the effective height of bubbler is 20mm from the bottom of the mixer.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.439-441
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• 2008

Three dimensional CFD study has been performed for analyzing the supersonic plume exhausting from the eject motor of a guided missile. The purpose of the study is to assess the impact of the plume to the shooter in a small bunker. The main body of the present paper is the development of a numerical method including grid generation and solver schemes.

• Journal of Advanced Marine Engineering and Technology
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• v.32 no.6
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• pp.869-876
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• 2008

A thermocompressor is the equipment which compresses a vapor to a desired discharge pressure. Since it was first used as the evacuation pump for a surface condenser, it has been widely adopted for energy saving systems due to its high working confidence. In the present study, the geometrical analysis of the shape between the jet nozzle and the diffuser inlet, the drag force was calculated by means of the integrated equation of motion and the computational fluid dynamic (CFD) package called FLUENT. The computer simulations were performed to investigate the effects by the various suction flow rates, the distance from jet nozzle outlet to the diffuser inlet and the dimensions of the diffuser inlet section through the iterative calculation. In addition, the results from the CFD analysis on the thermocompressor and the experiments were compared for the verification of the CFD results. In the case of a jet nozzle, the results from the CFD analysis showed a good agreement with the experimental results. Furthermore, in this study, a special attention was paid on the performance of the thermocompressor by varying the diffuser convergence angle of $0.0^{\circ}$, $0.5^{\circ}$, $1.0^{\circ}$, $2.0^{\circ}$, $3.5^{\circ}$ and $4.5^{\circ}$. With the increase of the diffuser convergence angle. the suction capacity was improved up to the degree of $1.0^{\circ}$ while it was decreased over the degree of $1.0^{\circ}$.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.28 no.2
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• pp.135-145
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• 2004

An experimental study is conducted to investigate the flow and heat transfer characteristics of a multi-tube inserted impinging jet. Four different multi-tube devices are tested for various nozzle-to-plate distance. Flow visualization by smoke-wire method and velocity measurements using a hot-wire anemometer are applied to analyze the flow characteristics of the multi-tube insert impinging jet. The local heat transfer coefficients of the multi-tube inserted impinging jet on the impingement surface are measured and the results are compared to those of the conventional jet. In multi-tube inserted system the multi-tube length plays an important role in the flow and heat transfer characteristics of the jet flow. With multi-tube insert of I3d4 and I6d4 which has relatively longer tube length than the multi-tube-exit of I3d1 and I6d1, the flow maintains its increased velocity far downstream due to interaction between adjacent flows. For the small H/D of 4, the local heat transfer coefficients of multi-tube inserted impinging jet are much higher than those of the conventional jet because the flow has higher velocity and turbulent intensity by the use of the multi-tube device. At large gap distance of H/D=12, also higher heat transfer rates are obtained by installing multi-tube insert except multi-tube insert of I3d1.

• Proceedings of the Korean Vacuum Society Conference
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• 2011.08a
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• pp.94-94
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• 2011

본 논문은 "차세대 반도체용 진공공정의 실시간 측정/진단/제어 기술개발"과제의 제 3 세부과제 "스마트형 진공 배기 진단 제어 시스템 개발"의 주요 연구 실적을 소개한다. 본 세부과제는 (1)진공펌프 및 배기 시스템의 다중 상태변수 측정 장치 개발, (2)공정별 펌프 상태 및 공정 조건 data base 구축 및 진단 알고리즘 개발(e-Diagnostics Level 2 FDC 수준), (3)공정별 펌프 상태 변수 측정을 통한 자기 진단 기술 개발(e-Diagnostics Level 2 FDC 수준), 그리고 (4)측정/통신 PMS (Pump Monitoring System) 개발(통신속도 56k bps 이상, e-Diagnostics Level 0~1)을 최종 목표로 추진되어 왔다. 첫 번째 주요실적은 진공배기시스템의 다중 상태변수 측정 및 평가 장치를 성공적으로 개발하였다. 본 장치는 현장에서 진공펌프의 배기속도를 3% 이내로 정밀하게 측정할 수 있는 소닉 노즐을 이용한 배기속도 측정 장치 및 기술을 성공적으로 개발 완료하였다. 그리고 측정 가능한 상태변수는 20종에 달하며 이들을 이용하여 진공펌프의 성능인자 15종과 특성치 9종을 종합적으로 평가할 수 있는 능력을 갖추었다. 두 번째 주요실적은 공정별 진공배기시스템의 자기진단 및 예지보수 기수 개발이다. 연구에서 개발된 적응형 인자모델을 이용한 상태진단 기술은 이미 학회 논문으로 소개되었으며 본 기법은 기존의 시계열 상태변수를 이용한 기존의 상태진단 기법보다 메모리 소요량을 100배로 줄였으며 그리고 연산양은 10% 이하로 줄인 획기적인 기법이라 할 수 있다. 세 번째 주요실적은 상태변수 측정, 통신, 제어 및 공정적응 기능 통합형(smart) PMS(pumper monitoring system) 개발이다. 본 장치는 CAN통신 기법을 새로이 채택하였으며 한 대의 PC로 64대의 단위 진공펌프들의 운전 상태변수를 실시간으로 수집할 수 있도록 하였다. 그리고 운전 중인 개별 진공펌프들의 운전 상태진단은 적응형 인자모델을 이용한 상태진단 기술을 응적용함으로써 매우 정확한 상태진단을 매 batch마다 수행할 수 있는 기능을 제공한다.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.2
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• pp.25-33
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• 2012

A genetic algorithm (GA) has been employed to optimize the major design variables of the liquid rocket engine. Pressure of the main combustion chamber, nozzle expansion ratio and O/F ratio have been selected as design variables. The target engine has the open gas generator cycle using the LO2/RP-1 propellant. The gas properties of the combustion chamber have been obtained from CEA2 and the mass has been estimated using reference data. The objective function has been set as multi-objective function with the specific impulse and thrust to weight ratio using the weight method. The result shows about 4% improvement of the specific impulse and 23% increase of the thrust to weight ratio. The Pareto frontier line has been also obtained for various thrust requirements.

• Fire Science and Engineering
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• v.33 no.6
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• pp.1-8
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• 2019

In this study, the effects of the characteristics of droplets of water spray on suppression of fire were analyzed numerically using fire dynamics simulator (FDS) 6.5.2. Additionally, the fire suppression characteristics by the water spray nozzle, including the extinguishing coefficient (EC), droplet size distribution function (SDF), median volumetric diameter (MVD), and droplets per second (DPS), were evaluated in terms of the decreasing normalized heat release rate (HRR) curve and cooling time. It was observed that with increase in the EC, the normalized HRR curve decreased rapidly, and the changing MVD affected the suppression of fire. In case of mono-disperse, the normalized HRR curve decreased slowly with the increase in DPS. On the contrary, in case of multi-disperse, the normalized HRR curve decreased rapidly even with a small increase in DPS.

• Transactions of the Korean Society of Mechanical Engineers
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• v.15 no.1
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• pp.323-327
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• 1991

An experiment was conducted to determine the local heat transfer from a supersonic hot jet impinging at 45.deg. to a plate surface. A semi-analytic method was used to determine the Nusselt number from experimental data. The results indicates that the location of the peak heat transfer is displaced from the geometric center of the axisymmetric jet and that the radial variation of the local heat transfer is steeper than that in the subsonic impinging jet. In the stagnation region, the heat transfer from the supersonic impinging jet is about 10 times larger than that from the subsonic one, while the heat transer away from the stagnation region is of the same magnitude as that of the in compressible turbulent radial wall jet.

• Journal of the Korean Society for Precision Engineering
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• v.28 no.1
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• pp.73-79
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• 2011

Inkjet printhead may have a lot of nozzles to increase productivity as a manufacturing tool. So, the uniformity of jetting performance among a lot of nozzles has been one of the key issues in inkjet technology In this study, we investigated the cross-talk effect which should be reduced for uniform jetting performance among a lot of nozzles. Due to the cross-talk, the jetting performance of a nozzle can be affected when neighboring nozzles are firing. For experimental study, we used commercial inkjet head SE-128 from Dimatix. To understand the cross-talk effect of SE-128 head, we measured the change in jetting speed of a nozzle when neighboring nozzles are jetting. The measured jetting speed was compared to the case of one nozzle jetting. Also, we used laser vibrometer to measure change in pressure wave due to cross-talk. As a result of the cross-talk, the jetting speed can become faster or sometimes slower depending on firing nozzle location. If the all nozzle are jetting, the jetting speed of a nozzle became slower because the pressure wave for jetting is reduced.