• Journal of the Korea Academia-Industrial cooperation Society
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• v.19 no.5
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• pp.681-688
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• 2018

As environmental regulations have been strengthened and high fuel efficiency has been in demand in recent years, the number of ships using natural gas as a fuel is increasing. The demand for ships using LPG or methanol, which are emerging as eco-friendly vessel fuels, is also increasing. In this perspective, ME-LGI engines using LPG or methanol as a fuel have attracted considerable attention. Ships equipped with an ME-LGI engine are required to check the reliability of the fuel injection valve during shipping. This means that the development of a fuel injection valve tester is essential for the commercialization of ME-LGI engine. This study conducted the conceptual design of a fuel injection valve tester for ME-LGI engines using a system engineering process in the order of requirements analysis, functional analysis, and design synthesis. In the requirement analysis stage, the operating process of fuel injection valve was analyzed, and the necessity of checking the sealing oil leakage was then derived. In the functional analysis stage, the functions and flow of them were defined at each functional level. In the design synthesis stage, the equipment for each function was set and the process block diagram based on it was derived. In addition, preliminary risk analysis was performed as a part of system analysis and control, and safety measures were added to the conceptual design. This study is expected to be a good reference material for the concept design of other systems in the future because it shows the application process of a system engineering process to the conceptual design in detail.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.37 no.1
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• pp.51-57
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• 2013

This study aims to experimentally investigate the combustion characteristics of a lean premixed swirl-stabilized burner with dual-stage fuel injection arrays. The results show that a variation in the fuel distribution to fuel stages 1 (upstream) and 2 (downstream) produces a noticeable change in the NOx and CO emissions. Reducing the confined ratio, defined as the ratio of the nozzle exit diameter to the liner diameter, may reduce NOx and CO emissions owing to reduced combustion loading and longer residence time, respectively. A nozzle exit velocity of 30 m/s shows the optimum characteristics in terms of NOx and CO emissions and flame stability: increasing or decreasing the nozzle exit velocity leads to a degradation in emissions or flame stability, respectively.

• 한국신재생에너지학회:학술대회논문집
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• 2007.06a
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• pp.816-819
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• 2007

국내에서 IGCC 플랜트의 복합발전시스템의 평가는 여러 분야별로 진행되어 왔다. 크게 살펴보면 다음과 같다. 첫 번째는 가스터빈 쪽의 기술이다. 즉, 기존 천연가스를 이용하는 가스터빈을 어떻게 하면 석탄가스를 사용하는 IGCC 플랜트에 적합하게 맞출 것인가 하는 문제이다. 두 번째는 효율을 어떻게 하면 높일 수 있는가의 문제로서 석탄의 종류, 가스화 방법을 효율적으로 선택, HRSG(heat recovery steam generator)를 효율적으로 설계, 그리고 정제공정에서의 에너지 소비를 줄이는 분야였다. 세 번째는 어떻게 하면 오염을 줄일까의 문제로서 질소나 스팀 분사를 연계하여 NOx를 감소시키고 정제 공정에 사용되는 촉매를 개발한다던지 공정을 발달시키는 분야였다. 이 외에도 여러 종류의 연구가 이 분야에서 있었으나 주로 설계 분야의 연구가 주되였다. 이것은 발전소의 건설을 위한 초기 단계로서 당연한 결과일 수 있다. 그러나, 지금 IGCC 플랜트가 건설되는 과정에 있으므로 우리나라 전력계통 연계와의 문제도 생각해보아야 한다고 생각한다. 따라서 이번 연구에서는 IGCC 플랜트 운영의 불확실성이 약간이라도 존재하기에 이 플랜트가 기저발전 보다는 첨두발전 쪽이나 태양열/광발전, 풍력발전 등 다른 신재생에너지 자원처럼 독립된 전력 시스템으로 운영될 것이라 생각하고 이렇게 운영될 때는 발전소의 부하률의 변화가 심할 수 있다는 가정하에 플랜트의 부하률에 따른 석탄의 합성가스, 연료가스 전환량 및 전환효율 및 발전량 및 발전효율을 전산모사를 통해 예측해보았다.

• Journal of the Korean Society of Propulsion Engineers
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• v.27 no.1
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• pp.58-67
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• 2023

Results of dry-run tests, cold-flow tests, and hot-firing tests performed to throttle a methane engine uni-element thrust chamber are covered in the paper. After installing flow control valves on the oxidizer and fuel supply lines of the methane engine combustion test facility, a number of dry-run tests were repeated so that the valves could reach set strokes quickly and stably. Then, cold-flow tests using liquid nitrogen and gaseous nitrogen were conducted to confirm the stable supply of the simulated propellants according to the valve control. Finally, using liquid oxygen and gaseous methane, hot-firing tests for fixed and continuous thrust control of 50% to 10% of the nominal thrust were successfully performed.