• Special Issue of the Society of Naval Architects of Korea
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• 2008.09a
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• pp.76-83
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• 2008

New and more efficient propulsion systems are required for LNG carriers. One of the proposed systems is a combination of a gas turbine with a heat recovery steam generator. This system constitutes a novel approach, which needs to be analyzed by system analysis and risk assessment to compensate for the lack of field experience. Of specific concern is the high pressure fuel supply system. This paper describes the dispersion and fire analysis performed to identify for safety and design improvement of proposed system.

• Proceedings of the Korea Society for Simulation Conference
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• 1999.10a
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• pp.176-180
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• 1999

미지 플랜트의 인식방법은 크게 두 가지로 나눌 수 있으며, 하나는 연역적 방법으로서 대상 플랜트에 대한 열적·유체 역학적 법칙을 사용하여 물리적으로 모델을 수식화하는 방식이고, 다른 하나는 귀납적 방법으로서 측정된 입출력데이터에 의해 역으로 구조를 찾아가는 방식이다. 본 논문에서는 후자의 방법으로 가스터빈 발전소의 배기가스 온도계통 모델을 구하기 위해 현장에서 운전 데이터를 취득하였다. 그리고 컴퓨터 시뮬레이션을 통해 경험적으로 구현한 모델이 실제 운전데이터와 유사한 특성을 보임을 알 수 있었다. 이렇게 구현된 모델은 향후 발전소용 가스터빈 제어시스템을 새로이 구축하거나 튜닝하고자 할 때 배기가스 온도제어계통을 설계하는데 기초자료로 활용할 수 있다.

• Proceedings of the Korea Society for Simulation Conference
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• 1999.10a
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• pp.170-175
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• 1999

본 논문에서는 국내에서 운전 중인 한 가스터빈 출력제어 회로의 구성을 살펴보고 현장에서 취득한 자료를 근거로 하여 가스터빈의 모델과 제어기의 조정, 그리고 MW 신호 피이드백 회로에 필터의 사용효과를 시뮬레이션을 통해 살펴보았다. 전력계통의 주파수가 가스터빈 출력제어계의 시상수에 비해 상당히 빠르게 변하므로 자동 주파수 추종을 할 경우 제어계가 쉽게 불안정해진다. 이 출력제어계의 MW 피이드백 회로의 1차지연 요소를 사용하면 안정성 향상에 좋은 효과가 있으며, 이 지연요소의 시상수를 크게 할수록 안정도는 더 향상되며 Open Loop의 특성을 보이게 된다. 그러나, 주파수 추종운전이 아닌 운전원의 출력 증감발 요구에는 시간지연 없이 응답을 하여야 하므로 적절한 설정을 할 필요가 있다. 가스터빈의 연료제어 계통을 포함한 출력제어계에 순수 시간지연 요소가 없으면 피이드백 회로에 1차지연 요소를 사용하지 않는 것이 더 좋은 출력제어 응답을 나타낸다. 그러나 실제 모들 가스터빈에는 다소 시간지연 요소를 포함하고 있으므로 일반적으로 피이드백 회로에 시간지연 요소를 사용하므로써 안정성을 향상시킬 수 있다.

• Proceedings of the KIPE Conference
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• 2014.07a
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• pp.267-268
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• 2014

본 논문에서는 LCI (Load Commuted Inverter) 시스템의 구동원리와 제어방식에 대해서 서술하였으며, 알고리즘 검증을 위한 모델링을 매트랩/시뮬링크를 사용하여 진행하였으며, 5kW급 프로토타입을 통해 제어 알고리즘의 성능을 확인하였다. 시스템 속도에 따라 달리하는 구동방식인 강제전류 모드와 자연전류 모드는 동기발전기의 정격속도 10%인 180rpm에서 모드 전환이 이루어지며, 과도상태 및 정격속도까지 안정적인 동작을 확인하였다.

• Journal of ILASS-Korea
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• v.24 no.3
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• pp.130-136
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• 2019

Spray visualization of a vaporizer fuel injection system of a micro turbo jet engine was experimentally studied. The fuel heating by combustion was simulated by the high pressure steam generator and combustor inlet air from the centrifugal compressor was simulated by compressed air stored in the high pressure air tank. Spray visualization was performed with single vaporizer, and then six vaporizers which are same number of micro turbojet engine were used. As a results, the spray characteristics of the vaporizer were understood with pressure difference of the combustor inlet air and the fuel supply pressure. Spray angles with three types of vaporizer configuration were measured. In the results, guide vane configuration has a wider spray angle than the straight tube and smooth curve tube with a swirler, so it is expected that the fuel will be effectively distributed inside the combustor flame tube.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2016.10a
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• pp.219-220
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• 2016

A power management system (PMS) has been an important part in a ship integrated control system. To evaluate a PMS for a liquefied natural gas carrier (LNGC), this research proposes a real-time hardware-in-the-loop simulation (HILS), which is composed of major component models such as turbine generator, diesel generator, governor, circuit breaker, and 3-phase loads on MATLAB/Simulink. In addition, FPGA based control console and main switchboard (MSBD) are constructed in order to develop an efficient control and a similar real environment in an LNGC PMS. A comparative study on the performance evaluation of PMS functions is conducted using two test cases for sharing electric power to consumers in an LNGC. The result shows that the proposed system has a high verification capability for the operating function and failure insertion evaluation as a PMS simulator.

• Journal of Energy Engineering
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• v.6 no.1
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• pp.104-113
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• 1997

This study aims to develop an analysis model using a commercial process simulator-ASPEN PLUS for an IGCC (Integrated Gasification Combined Cycle) system consisting a dry coal feeding, oxygen-blown entrained gasification process by Shell, a low temperature gas clean up process, a General Electric MS7001FA gas turbine, a three pressure, natural recirculation heat recovery steam generator, a regenerative, condensing steam turbine and a cryogenic air separation unit. The comparison between those results of this study and reference one done by other engineer at design conditions shows consistency which means the soundness of this model. The greater moisture contents in Illinois#6 coal causes decreasing gasifier temperature and the greater ash and sulfur content hurt system efficiency due to increased heat loss. As the results of sensitivity analysis using developed model for the parameters of gasifier operating pressure, steam/coal ratio and oxygen/coal ratio, the gasifier temperature increases while combustible gases (CO＋H2) decreases throughout the pressure going up. In the steam/coal ratio analysis, when the feeding steam increases the maximum combustible gas generation point moves to lower oxygen/coal ratio feeding condition. Finally, for the oxygen/coal ratio analysis, it shows oxygen/coal ratio 0.77 as a optimum operating condition at steam/coal feeding ratio 0.2.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.123-127
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• 2005

LRE(liquid rocket engine) performance design code with several modules for each engine component has been developed for a preliminary design purpose. Thrust chamber, non-cryogenic centrifugal pump, single stage axial impulse turbine, gas generator and exhaust pipe for extra thrust have been considered. For simplicity, pump exit pressures are fixed, which eliminates pressure balancing problem between thrust chamber and turbopump unit. In this paper, calculated performance parameters with system flow charts and the design methodologies for each component are briefly presented and the results are compared with tile real engine specification.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.25 no.8
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• pp.1103-1109
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• 2021

ECS is a control device so that the warship can perform the mission stably by controlling and monitoring the entire propulsion system. As the recent provisions of the warship, it's propelling system is complicated than past, as the demand performance and mission of the warships are diverse. In accordance with the complicated propulsion system configuration, the demand for automatic control function of the ECS is increasing for convenient and stable propulsion system control for convenient and stable. As a result, verification of ECS stability and reliability is required. In this paper, we develop an interlocking signal simulator for verifying ECS control logic and communication protocol for warship with CODLOG propulsion systems. The simulator developed was implemented to simulate a signal of gas turbine, propulsion motors, diesel generator and 11 kinds of auxiliary equipment. The reliability of ECS was verified through the ECS communication program and the I/O signal static test with the simulator.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.2
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• pp.175-181
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• 2018

Electric pump system is new technology for next generation propulsion unit. The system has simple structure which dose not need gas generator, injector and turbine and might better pump for low cost and low payload rocket. Therefore, this paper suggests conceptual design of electric-pump Permanent-Magnet Synchronous Motor (PMSM) which has 50 kW & 50,000 RPM for rocket. To satisfy the system's requirement, electromagnetic analysis is conducted for suitable inner and outer diameter of stator and rotor which uses 4000 Gauss cylinder magnet and Inconel 718 can to fix whole rotor. Futhermore, to confirm rotational vibration, rotordynamics analysis is conducted. By this analysis, Campbell diagram is printed. From the diagram, natural frequency could be determined for the only motor and dynamo meter test bench.