• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.303-306
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• 2007

A engineering analysis has been conducted to study operating characteristics of a supersonic exhaust diffuser simulating high altitude atmosphere from a flow-developing point of view. Emphasis is placed in the detail flow structure resulting from several design- and operating- parameters of the diffuser such as the area ratios of a exhaust nozzle to the diffuser, the vacuum chamber size, and jet pressure.

• 한국가시화정보학회:학술대회논문집
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• 2006.12a
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• pp.145-148
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• 2006

In order to design a micro-thruster which controls the altitude of a space vehicle for a very long lifetime, the flow field should be analyzed considering the nozzle geometry and the difference between stagnation and environmental pressures and so on. This paper describes the axisymmetric non-reacted computational results which were carried out to understand the basic flow phenomena according to the high nozzle pressure ratio. The area ratio is about 56 and the diameter of a nozzle exit is about 0.46 inch. The Mach cell and waves are predicted well.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.2
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• pp.51-57
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• 2012

Base pressure at the base of high-speed jet has long been one of the important issues from both the view points of fluid dynamics as well as practical engineering applications. The base pressure characteristics of incompressible flows have been well known to date. However, the base pressure at transonic or supersonic speeds would be different due to the compressibility effects and shock waves. In the present paper, a CFD study has been performed to understand the base pressure characteristics at transonic and supersonic speeds, prior to experimental work. An emphasis is placed on the control of the base pressure using a simple orifice. A variety of supersonic jet plumes have been explored to investigate the flow variables influencing the base pressure. The results obtained were validated with existing experimental data and discussed in terms of the base pressure and discharge coefficient of the orifice.

• Explosives and Blasting
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• v.19 no.3
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• pp.105-113
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• 2001

채석, 굴착, 가공과 같은 워터젯 응용분야에서 대상재료에 깊은 홈(kerf)을 절단할 수 있는 실험실용 회전식 슬로터(slotter)를 제작하여 암석을 대상으로 워터젯 시스템의 절단효율을 시험하였다. 고압펌프는 유율 7.5 l/min, 압력 379 MPa, 용량 75 kW급의 JETPAC을 주로 사용하였고, 암석시료는 화강석인 제천석, 거창석을 사용하였다. 시험과정에서는 물과 연마재 투입에 의한 절단 및 진동식 슬로터에 의한 슬롯절단 기초시험을 먼저 수행하고, 그 결과를 토대로 회전식 슬로터에 의한 절단시험을 실시하였다. 순수한 물에 의한 시험의 결과 고압수류의 토출압력은 절단심도에 정비례하였고, 노즐의 이송속도는 이차함수 형태의 반비례 관계를 보였다. 연마재 투입시험에서는 순수한 물에 의한 경우에 비해 연마재로 인한 충격력의 증가로 절단심도가 크게 증가하였는데, 유사한 조건하에서 3~5배 이상의 절단심도의 증가를 보였다. 진동식 슬로터에 의한 슬롯절삭에서는 생성된 슬롯의 내벽면이 바닥으로 갈수록 좁아짐으로써 넓은 폭의 슬롯형성은 가능하나 절삭심도가 제한되었다. 회전식 슬로터에 의한 시험에서 생성된 슬롯들은 평균 22 mm의 폭으로 내벽면이 바닥까지 서로 평행하여 깊은 심도까지 비트진입이 가능하였다. 절단율은 16~32 mm/sec의 속도범위에서 $40~160{\;}\textrm{mm}^2/sec$로 나타났다. 한편, 최대유율 24 l/min의 HUSKY S-200 펌프에 의한 시험결과 JETPAC 펌프에 비해 1.13~3.47 배의 절단심도를 보였다

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.196-200
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• 2005

A theoretical model for the calculation of chemical equilibrium composition of propellant combustion product is briefly presented for the performance analysis of monopropellant hydrazine rocket engine. Analysis result is compared to that of test and evaluation of 1-lbf class thruster and is scrutinized primarily from the view point of ammonia dissociation fraction. Chemical equilibrium composition and average molecular weight is additionally depicted according to the variation of propellant inlet pressures and the varying nozzle area ratio. The theoretical analysis is tried as a way of derivation of design parameters for mid- and large-thrust class of monopropellant rocket engines.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.79-82
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• 2009

Unsteady numerical analysis of an entire supersonic propulsion system from intake to nozzle was performed to study dynamic interaction between terminal shock in the intake and flame in the combustor. Both acceleration and cruise flight-modes were considered. Acoustic mode of the entire engine for both flight-modes were investigated by detail analysis of pressure fluctuation at each location of engine.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.397-400
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• 2008

Traditional propellants which have a hypergolic characteristic have a high performance but also have disadvantages of toxicity and complex handling requirement. In order to replace these propellants, one of the alternatives is hydrogen peroxide which generates high temperature oxygen and water vapor after catalytic reaction. In this paper, autoignition characteristics of kerosene by decomposed hydrogen peroxide were investigated to perform fundamental research for designing a thruster using hydrogen peroxide and kerosene propellants. Contraction ratio, whether flame holder exists or not, and feeding pressure of propellants were selected as variables. From the experiments for different mixture ratio, we confirmed the ignition stability is strongly affected by a feeding pressure of propellants.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.36 no.12
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• pp.1151-1159
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• 2012

Spray visualization and computer simulation of a DME injector have been conducted to investigate the enlarged injection hole diameter effect. To increase the reliability of the computational result, simulation results have been compared with the visualization test results, and the behaviors of a DME spray under various high-pressure and -temperature conditions have been computed. This study shows a discrepancy of 3.57% between the experimental and the computational results of penetration length for an injection pressure of 35 MPa and ambient pressure of 5 MPa. When simulating the engine conditions, the maximum penetration length of a fully developed DME spray is 42 mm when the temperature to pressure ratio is 300 K/MPa. The DME spray behavior is dominantly affected by the ambient pressure under the condition that the ratio is less than 300 K/MPa, and by the ambient temperature under the condition that the ratio is more than 300 K/MPa.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.22 no.6
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• pp.11-18
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• 2021

Nano bubble water is used in various washing processes, including cleaning of solar panels, salt rejection of roads, and cleaning precision parts of machines. High cleaning efficiency and water conservation are obtained by applying nano bubbles during pretreatment of the marine waste cleaning system. This study compared the salt rejection of nano bubble water, and it was revealed that marine waste was produced by wood immersed in 200,000 mg/L NaCl solution. Using tap water and nano bubble water for washing, comparisons of the surface salt concentrations of wood were determined according to the nozzle, orifice diameter, pump speed and washing time. Decreased surface salt concentration was observed on the wood surface with increasing washing time. Water consumption was optimal between 5- and 10-seconds washing time. Increasing orifice diameter of the nozzle reduced the spraying pressure, with consequent increase in the wood surface salt concentration, thereby establishing the importance of orifice diameter of the nozzle. Compared to levels obtained with tap water, salt concentration of the wood surface after washing with nano bubble water was 2.2% lower with sector nozzle, and 30.9% lower with circular nozzle. In the washing experiment using nano bubble water, the salt concentration on the wood surface was about 9.5 mg/L lower when washed with sector nozzle than the circular nozzle.

• Journal of the Korean Institute of Gas
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• v.25 no.6
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• pp.22-28
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• 2021

Combustion characteristics were examined experimentally for a swirl-stabilized double cone premixed burner nozzle used for industrial gas turbines for power generation. An original model and a variant with a different fuel injection pattern are tested to compare their combustion characteristics such as NOx, CO and stability in pressurized conditions with single burner-flame and in an ambient multi-flame conditions with multi-burners. Test results show that NOx emissions are smaller for the variant, whose number of fuel holes is reduced with the same total area of fuel holes, in ambient and pressurized single-flame conditions with single burner, which results from enhanced fuel/air mixing due to a higher penetration of fuel into the air stream. The multi-burnerflame test results show that NOx emissions are smaller for the variant due to reduced flame interactions, which, on the contrary, slightly reduces the stability margin. On-site test results fromin an actual power plants also show that NOx emissions are reduced for the variant, compared with the original one, which is in agreement with the lab test results stated above.