• Proceedings of the KAIS Fall Conference
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• 2010.05b
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• pp.1173-1176
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• 2010

회전익 항공기의 연료탱크는 피탄으로 인해 연료 누유시 발생할 수 있는 화염으로부터 기체와 승무원의 생존성을 높이기 위하여 연료누설을 차단하는 자기밀폐 기능이 필수적으로 요구된다. 자기밀폐 기능은 내부에 적층된 자기밀폐 소재가 누설되는 연료와 화학반응을 일으켜 급속히 팽창됨으로써 피탄부를 막아, 연료누설을 차단하는 역할을 한다. 본 연구는 미군사규격(MIL-DTL-27422D) 기준으로 국내에서 제작 및 수행한 회전익 항공기의 연료탱크 자기밀폐 성능시험 평가 결과를 제시한다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.79-82
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• 2011

An afterburning device was developed to safely treat unburnt gases of fuel-rich condition discharged by a gas generator. Hot-firing tests for a subscale gas generator were carried out to investigate operation and safety of the afterburning device. When supplying additional liquid oxygen, the length of the afterburning flame was significantly reduced.

• Proceedings of the Korean Society of Marine Engineers Conference
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• 2012.06a
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• pp.205-205
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• 2012

선박에서는 화재안전목표를 달성하기 위해 선박을 방화구획화 함으로써 발화의 지점에서 화재를 차단하여 인근지역으로 확산 되지 않도록 하고 있다. 또한 방화구획을 관통하는 파이프, 덕트 및 전선관통부 등을 통하여 유독가스 및 화염이 순식간에 이동하게 되며, 한쪽 구역에서 발생한 화재의 영향이 다른 구역으로 영향을 미치게 되므로 화염에 의한 피해를 방지하고 불길을 차단하기 위하여 관통부재에 대하여 해당 방화구획과 동등한 성능을 요구하고 있다, 선박에 적용되고 있는 방화구획의 등급은 용도에 따라 일반 상선 등에는 "C ~ A"급, 해양플랜트에는 "C ~ H"급 등급이 요구되고 있다. 그러나 현재 국내 선박 기자재 제작 기술은 "A"급에 머물러 있고 최근 국내 조선소의 해양플랜트 수주 증가와 해양플랜트로의 사업전환으로 관련기자재기업에서 "H"급 기자재 개발에 많은 관심을 가지고 개발 시도를 하고 있다. 이에 본 논문에서는 "H" 급 방화구획에 적용되고 있는 탄화수소계(Hydrocarbon Fire) 내화시험기준과 "H"급 Fire Damper의 단열두께에 따른 탄화수소계(Hydrocarbon Fire) 내화성능실험을 통한 방화 댐퍼의 비 노출면에 대한 방열성능 확보방안에 대하여 언급하고자 한다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.05a
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• pp.266-269
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• 2003

During liquid rocket engine combustion, the resulting combustion gas has flow characteristics of high temperature and high velocity. An experimental study was performed to obtain basic data for a flame deflector design that is endurable under such flow characteristics. While the injected-water cools down the combustion plume, temperature and pressure of the plume was measured. As the experiment is being performed, gas temperature was measured using infrared cameras, and the gas temperature data was compared with the temperature data from the sensor in the plume. With the results of this experiment, we were able to obtain applicable temperature data for flame deflector design and predict the performance and structural strength required for installation of water injector.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.150-155
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• 2010

Liquid rocket injectors play crucial roles on propulsive performance, combustion stability, and heat transfer characteristics. Nevertheless, their developments have mainly relied on empirical methods and expensive hot-firing tests due to lack of fundamental understanding of high pressure combustion phenomena in the near-injector regions. The present study was motivated by recent efforts to develop reliable modeling of liquid rocket combustion. The turbulent combustion model based on the flamelet concept has been extended to take into account real-fluid behaviors occurred at supercritical pressures, and validated against measurements for a cryogenic nitrogen injection, a non-premixed turbulent jet flame at atmospheric pressure, and a LOx/$GH_2$ coaxial shear injector at a supercritical pressure.

• Journal of Aerospace System Engineering
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• v.13 no.5
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• pp.16-23
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• 2019

This paper describes the design and analysis of a periscope imaging system installed at the engine test facility in the Agency for Defense Development. The periscope system is a cylinder-shaped image observation system installed at the rear of the engine and at the top of the diffuser. The periscope system has high risk of breaking because it is directly affected by high temperature (2300 K) and products of combustion. Thus, we used 1D heat transfer calculation, and 2D and 3D CFD analysis to confirm the heat flux and temperature distribution. Also, the cooling performance was verified. In the current design, using the periscope system, we can see flame shapes, control of the nozzle, and stability of the exhaust flow visually.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.38 no.6
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• pp.601-608
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• 2014

An offshore plant is vulnerable to fire because of the isolated environment. In particular, the damage to an offshore plant is increased when a hydrant reducing valve, which is a main piece of equipment in an offshore plant, is damaged in a fire. In this study, we conducted a fire safety test for a hydrant reducing valve and proved the validity of our analysis by comparing the results of the test and analysis. Therefore, we here suggest an analysis method for a fire safety test. FSI(fluid structure interaction) was considered in the fire safety test. The reliability of the analysis method was verified by comparing the temperature distributions of the test and analysis. In addition, we verified the problems that were caused in the fire safety test by conducting a structure analysis. At a result, the main problem was found to be deformation of the valve seat.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.35 no.4
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• pp.439-444
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• 2011

To determine the test gases for gas appliances of new gas group, the interrelation between gas interchangeability, including thermal efficiency, of 13A gas appliances and present 13A test gases was experimentally investigated. The test results show that the Wobbe indices in the case of incomplete combustion and the flame lifting limit gas for the new gas group are respectively 2% higher than the upper limit and 1% lower than the lower limit of the Wobbe index range. The most suitable composition of R gas is 96 mol% of methane and 4 mol% of propane; LNG could be also used as R gas. Further, analysis results showed that the hydrogen concentration of flash back limit gas could be lowered from 30 vol% to 23 vol%.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.40-45
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• 2005

Techniques used for throcket motors are mainly classified as fixed nozzles with mechanical exhaust jet interferences on the expansion region (such as jet tabs and jet vanes) and movable nozzles(such as ball&socket md flexible seal). Using the numerical analysis and the cold-flow test, this paper evaluates the performance of supersonic nozzle for asymmetric entrance shape at tilted position of ball&socket nozzle. Numerical results show that the asymmetric effects in the flow fields are gradually diminished up to the nozzle throat and are not noticeable downstream of the nozzle throat. Although the calculated thrust and the lateral force are less than those of cold-flow test, two results show a flirty good agreement.

• Aerospace Engineering and Technology
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• v.3 no.1
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• pp.188-196
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• 2004

To optimize and limit the axial length of baffle in KSR-III engine, stability rating tests using pulse gun as one of artificial disturbance devices have been done. Decay time and other parameters for the evaluation of stabilization ability of engine to external perturbation have been analyzed to quantify stabilization capacity of engine, in other words, dynamic stability margin. If baffle does not cover flame zone enough which can be considered as collision region of injector, it wasn't be able to suppress external perturbation sufficiently. The limit of combustion stability margin of engine is assumed to be 50 mm length baffle.