• Proceeding of EDISON Challenge
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• 2013.04a
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• pp.365-370
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• 2013

현대에 이르러 초음속 운영 영역에서의 항공기에 대한 많은 연구가 진행되고 있으나, 음속 폭음 현상과 충격파 현상에서 야기된 높은 항력 및 연료 효율성 저하로 인하여 그 한계에 부딪치고 있다. Busemann 복엽 익형은 이와 같은 문제를 해결하기 위한 형상이며, 상하 형상에 의한 파동 상쇄효과 및 파동 감소효과를 통해 충격파의 강도와 음속 폭음 효과를 감소시키는 형상이다. 하지만 본 익형은 탈설계 조건에서 항력 계수가 급격하게 증가하는 등의 문제점을 가지고 있다. 본 연구에서는 EDISON_CFD를 이용하여 Busemann 복엽 익형의 주변 유동 특성에 대하여 면밀한 고찰을 수행하였다. 우선 Busemann 복엽 익형의 초기 형상에 대한 유동 조건별 해석을 통하여 탈설계 조건에서의 항력 성능 저하 문제에 대한 고찰을 하였다. 이후 3개의 형상 변수에 대한 매개 변수 연구를 통하여 익형의 각 형상 변수가 탈설계 영역 및 해당 영역에서의 최대 항력 계수에 미치는 영향에 대한 고찰을 수행하였으며, 이를 통하여 기존 형상보다 좁은 탈설계 구간을 가지고, 최대 항력 계수가 약 34.8% 감소한 부스만 복엽 익형을 설계하였다.

• Proceedings of the Korea Water Resources Association Conference
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• 2011.05a
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• pp.239-243
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• 2011

우리나라 주요 수자원인 댐 저수지는 여름철 성층현상으로 인해 많은 수질문제가 발생하여 산기식 수중폭기장치를 설치하고 있다. 그러나 산기식 수중폭기장치의 설계인자들은 대부분 lab-scale의 실험연구를 통해 검토되고 설계에 반영되고 있어 실제 댐 저수지에 적용하기 위해서는 현장적용성을 고려하여 개선될 필요가 있다. 따라서 본 연구는 실제 댐 저수지의 현장조건을 고려하여 CFD 모의실험을 통해 산기식 수중폭기장치의 설계인자인 무차원변수 DN (Destratification Number)과 탈성층 영향반경 및 효율을 검토하였다. 그 결과 현장조건에서의 DN값은 lab-scale 실험조건보다 더 넓은 범위를 가지며, 단위수심당 탈성층 영향반경은 DN값이 증가할수록 감소하는 것으로 분석되었다. 또한 탈성층 효율은 DN값이 증가할수록 선형적으로 증가하다가 증가율이 감소하면서 일정해지는 것으로 분석되었다.

• Journal of Aerospace System Engineering
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• v.14 no.5
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• pp.91-99
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• 2020

A liquid rocket engine goes through many tests to prove its performance before liftoff. It means the tests for setting ignition and start-up conditions or a test on design condition, which verifies the design performance. However, the development process requires verification of performance under off-design conditions through tests involving different operating conditions, which affects the duration of engine development. The off-design performance test is performed by altering the conditions of the propellant supplied to the engine in conjunction with the engine performance test that varies the opening of the control valves in the engine. This paper is based on the results of the engine tests performed at the KSLV-II engine test facilities in the Naro Space Center and describes the operations of the test facility for off-design condition test that changes the inlet conditions of the turbo-pump due to changes in the pressure and temperature of the propellant supplied to the test engines.

• Journal of Aerospace System Engineering
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• v.16 no.4
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• pp.1-9
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• 2022

A design factor analysis was conducted to reduce the thrust reduction in the off-design, due to the driving of the aerospike pintle nozzle. The close (NPR 100) as well as the open (NPR 11) stroke were fixed, as under-expansion conditions. The pintle contour, pintle head radius (R), cowl angle (θ), and cowl exit length (L) were selected as design factors. The change in thrust was analyzed, using a verified numerical analysis technique. First, the pintle head radius and the length of the cowl exit had little influence on the thrust. The cowl angle changed the mass flow rate by affecting the effective nozzle throat area, and created a reverse pressure gradient at the cowl exit. As a result of applying the dual aerospike contour, it was confirmed that the thrust in the design-off increased by approximately 1.2%, compared to the reference case and by approximately 3.4% compared to the worst case.

• Journal of Korea Society of Industrial Information Systems
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• v.7 no.2
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• pp.40-45
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• 2002

In this paper, we design and implement an agent-based mask dance guidance system which provides multimedia information on traditional masques through WWW. When the server receives a query from the client, it produces the multimedia data by connecting several real full-motion videos, and synthesizing adequate voice data for guiding announcement. To develop an agent-based guidance system, we designed and implemented four agents such as interface agent, user modeling agent coordinator agent and data management agent. The mask dance guidance system also provides the functions of searching using the keyword and learning.

• Proceedings of the Korea Society for Energy Engineering kosee Conference
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• 1997.10a
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• pp.99-104
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• 1997

기존의 천연가스 가스터빈 시스템을 IGCC 발전소에 적용함에 있어 야기되는 탈설계점효과를 고려할 수 있는 압축기 성능곡선의 예측방법을 제안하였다. 압축기 성능해석방법으로는 익렬요소방법에 전압력손실, 유동편차각 모델들을 결합하여 사용하였으며, 본 방법에 의한 예측결과와 실제 압축기 성능실험결과를 비교하였다. 예측결과가 다양한 압축기 운전조건에 대해 시험결과와 비교적 잘 일치하였으며, 이를 통해 본 예측방법이 IGCC 공정설계 및 성능평가시 가스터빈 탈설계점 효과를 분석할 수 있는 기본 모듈로 사용될 수 있을 것이다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.3
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• pp.195-203
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• 2019

Since the hypersonic intake is directly related to the overall performance of the engine, it is essential to analyze performance characteristics under various off-design conditions. In this paper, Busemann intake and conical intake with external compression were designed, and numerical simulations were performed at on/off-design conditions. Based on the results, the overall performance characteristics of two types of intake were analyzed in various Mach numbers and angle of attacks. The results showed that performance degradation of Busemann intake with truncation angle of 2 degrees was minimal. Also, the performance of Busemann intake was higher than external compression intake at various Mach numbers, however, the starting characteristics were significantly reduced with an angle of attack.

• Proceedings of the Korean Nuclear Society Conference
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• 2002.05a
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• pp.135.2-135
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• 2002

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.12
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• pp.881-889
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• 2019

The pre-swirl system is the device that minimizes energy loss of turbine cooling airflow from the stationary parts into rotating parts. In this paper, an off-design analysis was conducted for the ambient air temperature and turbine load conditions. The discharge coefficient was constant for ambient air temperature and turbine load. However, adiabatic effectiveness was increased. This is due to the volume flow rate. The volume flow rate was increased at higher ambient temperature and higher turbine load. It means that the volume of cooling air was increased and the cooling performance of the air was improved. Consequently, adiabatic effectiveness increased by 30.46% at 100% turbine load compared to 20% turbine load. And increased by 18.42% at 55℃ ambient air temperature compared to -20℃ ambient air temperature.

• Journal of Energy Engineering
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• v.21 no.4
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• pp.411-418
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• 2012

The effect of built-in volume ratio of expander on the performance of a two-loop Rankine cycle system for engine waste heat recovery of vehicle has been investigated. In the case of positive displacement expander in the various operating condition of the vehicle, it can operate in both under-expansion and over-expansion conditions. Therefore, the analysis of off-design performance for the expander is very important. Furthermore, the volume and weight of the expander as well as the efficiency must be considered in the optimization of the expander. This study shows that the built-in volume ratio of expander causing under-expansion at a target condition is more desirable considering the off-design performance and size of the expander, based on the simple modeling of off-design operation of the expander.