• 한국수소및신에너지학회논문집
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• 제27권5호
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• pp.571-580
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• 2016

In this paper, performance of the gas turbine combined cycle(GTCC) using pre-combustion carbon capture technology was comparatively analysed. Steam reforming and autothermal reforming were used. In the latter, two different methods were adopted to supply oxygen for the reforming process. One is to extract air form gas turbine compressor (air blowing) and the other is to supply oxygen directly from air separation unit ($O_2$ blowing). To separate $CO_2$ from the reformed gas, the chemical absorption system using MEA solution was used. The net cycle efficiency of the system adopting $O_2$ blown autothermal reforming was higher than the other two systems. The system using air blown autothermal reforming exhibited the largest net cycle power output. In addition to the performance analysis, the influence of fuel reforming and carbon capture on the operating condition of the gas turbine and the necessity of turbine re-design were investigated.

• 한국추진공학회지
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• 제12권6호
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• pp.56-65
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• 2008

• Journal of Mechanical Science and Technology
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• 제16권6호
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• pp.839-850
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• 2002

A performance simulation program for the turboprop engine (PT6A-62), which is the power plant of the first Korean indigenous basic trainer KT-1, was developed for performance prediction, development of an EHMS (Engine Health Monitoring System) and the flight simulator. Characteristics of components including compressors, turbines, power turbines and the constant speed propeller were required for the steady state and transient performance analysis with on and off design point analysis. In most cases, these were substituted for what scaled from similar engine components'characteristics with the scaling law. The developed program was evaluated with the performance data provided by the engine manufacturer and with analysis results of GASTURB program, which is well known for the performance simulation of gas turbines. Performance parameters such as mass flow rate, compressor pressure ratio, fuel flow rate, specific fuel consumption and turbine inlet temperature were discussed to evaluate validity of the developed program at various cases. The first case was the sea level static standard condition and other cases were considered with various altitudes, flight velocities and part loads with the range between idle and 105% rotational speed of the gas generator. In the transient analysis, the Continuity of Mass Flow Method was utilized under the condition that mass stored between components is ignored and the flow compatibility is satisfied, and the Modified Euler Method was used for integration of the surplus torque. The transient performance analysis for various fuel schedules was performed. When the fuel step increase was considered, the overshoot of the turbine inlet temperature occurred. However, in case of ramp increase of the fuel longer than step increase of the fuel, the overshoot of the turbine inlet temperature was effectively reduced.

• 대한조선학회 특별논문집
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• 대한조선학회 2008년도 특별논문집
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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.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2004년도 하계학술대회 논문집 B
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• pp.752-754
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• 2004

Super high speed motors and generators are increasing in various applications such as air compressor, gas turbine and fuel cell systems because of small size and light weight at the same power level. This paper presents an experiment and simulation for a permanent magnet synchronous motor(PMSM) in super high speed applications.

• Korean Chemical Engineering Research
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• 제43권3호
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• pp.331-343
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• 2005

연료전지와 수소를 사용하는 연료전지 자동차의 상용화를 위해서는 수소 공급용 수소 스테이션(hydrogen station)의 개발이 중요한 핵심 기반기술이다. 일반적으로 수소 스테이션은 탈황반응, 개질반응(reforming), 수성가스전환(WGS) 반응 및 수소분리(PSA) 장치로 구성된 수소제조 공정과 압축, 저장 및 분배 장치로 구성된 후처리(post-treatment) 공정으로 구성되어 있다. 본 총설에서는 수소 경제(hydrogen economy) 사회로의 진입을 위해 국내외에서 연구개발 중인 수소 스테이션에 대한 연구 개발 동향과 전망을 고찰하였다. 그리고 향후 풍력 및 태양열 등 재생 가능 에너지(renewable energy)원으로부터 물의 분해에 의한 수소제조 기술이 확립되기 전까지는 화석연료의 개질 반응이 수소를 제조하는 핵심기술이 될 것으로 판단된다. 따라서 화석연료의 탈황반응, 화석연료의 개질 반응에 의한 수소제조, CO 농도 저감을 위한 수성가스 전환반응 및 수소의 분리기술 등 수소 스테이션의 상용화에 필수적인 단위공정개발에 대한 최근의 연구동향을 정리하였다.

• 한국추진공학회지
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• 제19권5호
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• pp.1-14
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• 2015

아음속에서 초음속까지 운용되어야 하는 초음속 터빈엔진의 경우, 엔진 운용 공기량이 범위가 넓고 추력 및 연료소모율 등의 엔진 성능에 대해 요구조건이 높으므로 가변시스템 및 이를 제어하기 위한 최적의 제어로직 개발이 반드시 필요하다. 본 연구에서는 압축기 가변 시스템이 적용된 가스터빈 성능해석 모델 및 제어기법을 개발하였다. 그리고 터빈 노즐 가변에 따른 엔진 운용 특성을 분석하였다. 또한 가변 시스템을 구동하는 액추에이터에 대한 개념 설계를 수행 하였다. 저바이패스비 혼합흐름 터보팬 엔진에 대한 탈설계점에서의 성능해석을 수행하였으며, 제어기법을 적용하여 탈설계점에서의 서지마진을 확보할 수 있었다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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• pp.513-520
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• 2004

A steady-state/transient performance simulation model was newly developed for the propulsion system of the CRW (Canard Rotor Wing) type UAV (Unmanned Aerial Vehicle) during flight mode transition. The CRW type UAV has a new concept RPV (Remotely Piloted Vehicle) which can fly at two flight modes such as the take-off/landing and low speed forward flight mode using the rotary wing driven by engine bypass exhaust gas and the high speed forward flight mode using the stopped wing and main engine thrust. The propulsion system of the CRW type UAV consists of the main engine system and the duct system. The flight vehicle may generally select a proper type and specific engine with acceptable thrust level to meet the flight mission in the propulsion system design phase. In this study, a turbojet engine with one spool was selected by decision of the vehicle system designer, and the duct system is composed of main duct, rotor duct, master valve, rotor tip-jet nozzles, and variable area main nozzle. In order to establish the safe flight mode transition region of the propulsion system, steady-state and transient performance simulation should be needed. Using this simulation model, the optimal fuel flow schedules were obtained to keep the proper surge margin and the turbine inlet temperature limitation through steady-state and transient performance estimation. Furthermore, these analysis results will be used to the control optimization of the propulsion system, later. In the transient performance model, ICV (Inter-Component Volume) model was used. The performance analysis using the developed models was performed at various flight conditions and fuel flow schedules, and these results could set the safe flight mode transition region to satisfy the turbine inlet temperature overshoot limitation as well as the compressor surge margin. Because the engine performance simulation results without the duct system were well agreed with the engine manufacturer's data and the analysis results using a commercial program, it was confirmed that the validity of the proposed performance model was verified. However, the propulsion system performance model including the duct system will be compared with experimental measuring data, later.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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• pp.499-505
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• 2004

A Propulsion System of the CRW(Canard Rotor Wing) type UAV(Unmanned Aerial Vehicle) was composed of the turbojet engine to generate the propulsive exhaust gas, and the duct system including straight bent ducts, tip-jet nozzles, a master valve and a variable main nozzle for three flight modes such as lift/landing mode, low speed transition flight mode and high speed forward flight mode. In this study, in order to operate safely the propulsion system, the dynamic Performance behavior of the system was modeled and simulated using the SIMULIN $K^{ }$, which is the user-friendly GUI type dynamic analysis tool provided by MATLA $B^{ }$. In the transient performance model, the inter-component volume model was used. The performance analysis using the developed models was performed at various flight condition, valve angle positions and fuel flow schedules, and these results could set the safe flight mode transition region to satisfy the inlet temperature overshoot limitation as well as the compressor surge margin. Performance analysis results using the SIMULIN $K^{ }$ performance program were compared with them using the commercial program GSP.m GSP.

• Journal of Advanced Marine Engineering and Technology
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• 제36권8호
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• pp.1050-1060
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• 2012

SOFC시스템 고효율화의 한 방법으로 SOFC/GT 하이브리드시스템은 유효하다. 그러나 시스템의 출력 규모가 수십 MW급의 선박용이라면 하부시스템으로 사용되는 GT시스템의 냉각방식 도입은 장치를 복잡하게 만들고 제어 또한 쉽지 않게 된다. 따라서 선박용으로는 SOFC/GT(유냉각) 하이브리드시스템보다 SOFC/GT(무냉각) 하이브리드시스템이 더 적합해 보인다. 본 연구는 SOFC/GT(무냉각) 하이브리드시스템을 구축하고 그 시스템에 대한 스택의 작동온도와 전류밀도, 가스터빈의 압력비, TIT가 시스템의 성능에 미치는 영향 등을 시뮬레이션을 통하여 검토한 것으로 공기압축기 소요 동력의 증가에도 불구하고 전기적 효율은 상승되며 TIT에는 운전을 위한 제한된 온도범위가 존재한다는 것을 알 수 있었다.