• Proceedings of the Korean Powder Metallurgy Institute Conference
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• 1994.04c
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• pp.34-34
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• 1994

• Proceedings of the Korean Powder Metallurgy Institute Conference
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• 2003.04a
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• pp.43-44
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• 2003

• Transactions of the Korean Society of Mechanical Engineers B
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• v.37 no.4
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• pp.387-394
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• 2013

Hydrogen-compressed natural gas (HCNG) blend has attracted attention as a fuel that can reduce $CO_2$ emissions because it has low carbon content and burns efficiently. An increase in the compression ratio of HCNG engines was considered as one of the methods to improve their efficiency and reduce $CO_2$ emissions. However, a high combustion rate and flame temperature cause abnormal combustion such as pre-ignition or knocks, which in turn can cause damage to the engine components and decrease the engine power. In this study, the performance and knock characteristics with a change in the compression ratio of an HCNG engine were analyzed. The combustion characteristics of HCNG fuel were evaluated as a function of the excess air ratio using a conventional CNG engine. The effects of the compression ratio on the engine performance were evaluated through the same experimental procedures.

• Journal of Nuclear Fuel Cycle and Waste Technology(JNFCWT)
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• v.13 no.3
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• pp.201-209
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• 2015

Currently, 23 nuclear power plants are in operation at Kori, Uljin, Younggwang and Wolsong site and a reference deep geological disposal system has been developed for the spent fuels generated by them. The reference spent fuel for this disposal system has 4.5wt% of initial enrichment, 55 GWd/MtU of burn-up, and 40 years of cooling time. In this paper, to improve disposal efficiency and economic feasibility, the characteristics of spent fuels from nuclear power plants, such as type and burn-up, were reviewed. A disposal canister concept for shorter length and relatively lower burn-up spent fuels than the reference spent fuels was developed. Based on this canister concept, thermal analyses were carried out and a deep geological disposal concept was proposed. Measures of disposal efficiency such as unit disposal area and disposal density were compared between this disposal system and the reference disposal system. Also, economic feasibility, such as the volume reduction of copper, cast iron, and bentonite, was analyzed and the results of these analyses showed that the disposal system proposed in this paper has an efficiency of at least 20%. These results could be used for establishing spent fuel management policy and designing practical disposal systems for spent fuels.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.20 no.10
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• pp.100-106
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• 2019

Ground and high altitude simulated combustion experiments were conducted using a liquid rocket engine with hydrogen peroxide and kerosene as the propellant. A ground and high altitude simulated combustion test facility was constructed by installing a high altitude model diffuser and TMS (Thrust Measuring System) on a vertical combustion test bench. The thrust characteristics according to altitude were investigated using the combustion test equipment. The diffuser was designed on a 1:4.8 scale to verify the characteristics of the high diffusing diffuser and starting pressure. The cold flow tests were conducted using nitrogen gas, and the performance characteristics and starting characteristics of the scale down diffuser were verified. A diffuser and TMS were installed on the vertical combustion test bench, and the thrust correction equations for the system resistance were derived. The thrust correction equations were derived from the step test and vacuum step test before the actual hot firing test. Nozzles with an operating altitude of 10km were designed. Hot firing tests were conducted to analyze the thrust characteristics according to the operating altitude changes. The actual thrust was calculated using each correction equation with the thrust value measured by the TMS.

• 한국항공운항학회:학술대회논문집
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• 2016.05a
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• pp.14-18
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• 2016

본 연구에서는 하이브리드로켓 모터와 고체로켓 모터를 이용하여 목표 고도 1km인 2단 로켓 설계를 수행하였다. 비행 시나리오는 총 비행시간 51.59초, 1단부 로켓 연소시간은 3초이며 연소 종료 후 3초 뒤 단 분리를 수행하여 2단부 로켓 점화가 이루어져 총 3초간 연소가 진행된다. 1단부 모터는 하이브리드로켓으로써 5port의 HDPE를 연료 그레인으로 사용하였고 $LN_2O$를 산화제로 사용하였다. 2단부 모터는 고체로켓으로 KNSB(Sorbitol/$KNO_3$)추진제를 사용하였다. 단 분리는 영전자석을 이용하여 분리하며 2단부 모터의 점화는 광학 센서와 니크롬선 점화방식을 이용하여 점화하도록 설계하였다. 비행하는 동안 AVR를 이용해 압력, 가속도, GPS 등의 자료를 수집할 수 있도록 설계하였다.

• 한국연소학회:학술대회논문집
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• 2001.11a
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• pp.125-135
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• 2001

Aiming at a direct, also more realistic, prediction of unstable waves evolving in the combustion chamber, present paper introduces a new analytical method. Instability equations are freshly formulated, and solve the time-integrated ODEs for amplification factors to find the transients of pressure and velocity fluctuations. Present numerical approach requires no separate treatments for nonlinearities. Preliminary numerical experiments for unstable waves in quasi-one-dimensional rocket combustor, show validity and applicability of present model, and promise for its practical use. Study for the complex models for physics, especially velocity- and pressure-coupled responses, and inclusion of multi dimensionality remains as future tasks.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.219-222
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• 2007

This research on 2nd stage solid rocket motor of KSLV-I for performance change was carried out. Solid rocket motor shall ignite on altitude of 300km. Solid Rocket Motor performed Static Firing Test and High Altitude Test for motor performance. A study made an analysis of specific impulse variation for nozzle ambient pressure.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 1992.10a
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• pp.31-35
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• 1992

자동차 관련 소음 및 진동중 엔진과 관련된 것은 흡.배기계 소음과 엔진 자 체의 각 구동 부위 및 연소실 소음으로 대별하여 볼수 있다. 특히 연소실 소 음의 경우에는 엔진 내부에서 발생하는 진동과 압력파가 엔진을 진동시키고, 이러한 엔진의 진동이 방사음을 발생시켜 형성되는 만큼 그 해석 및 공학적 접근 방법이 용이하지 않다. 연소실 소음은 압력의 갑작스런 변화에 의한 폭 발소음과 피스톤과 실린더 벽면의 충돌에 의한 피스톤 슬랩(piston slap)으로 크게 구분할 수 있으며 압력이 높지 않고 압력의 변화가 빠르지 않을 경우 에는 피스톤 슬랩이 기계적 소음의 주 원인이 되는 것으로 알려져 있다. 본 고에서는 피스톤 슬랩에 의한 진동 현상을 예측하기 위한 이론적 접근 방법 을 제시하고 이의 타당성을 검증하기 위한 실험적 방법을 제시하고자 한다. 또한, 피스톤과 실린더의 간극 진단을 위해 슬랩 신호를 이용하는 방법에 대 해 살펴보고, 피스톤과 실린더의 충돌 속도를 통해 슬랩 신호를 줄이기 위한 엔진의 설계 방법에 대해 살펴보고자 한다.

• 한국연소학회:학술대회논문집
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• 2002.11a
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• pp.57-64
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• 2002

This paper describes the results of a series of experiments executed by using two pilot-scale oxv-fuel burners are designed for maximum capacity of 50,000 kacl/hr, 300,000 kcal/hr and installed in the test furnace. The effects of turn-down ratio, excess oxygen ratio, nozzle exit velocity, injection angle, swirl vane angle and inlet oxygen temperature on the combustion characteristic are investigated. Temperature distributions are measured using R-type and Molybdenum sheathed C-type thermocouple. The results showed that maximum temperature and mean temperature increase with the increase of turn-down ratio and inlet oxygen temperature. The maximum flame temperature was increased about 35% compared to the case of equivalent air operated condition. In addition, Optimum excess oxygen ratio and nozzle characteristics are obtained for this oxy-fuel glass melting furnace.