• Transactions of the Korean Society of Mechanical Engineers B
• /
• v.40 no.10
• /
• pp.673-679
• /
• 2016

Because of the growing interest in supercritical carbon dioxide power cycle technology owing to its potential enhancement in compactness and efficiency, supercritical carbon dioxide cycles have been studied in the fields of nuclear power, concentrated solar power (CSP), and fossil fuel power generation. This study introduces the current status of the research project on the supercritical carbon dioxide power cycle by Korea Institute of Energy Research (KIER). During the first phase of the project, the un-recuperated supercritical Brayton cycle test loop was built and tested. In phase two, researchers are designing and building a supercritical carbon dioxide dual Brayton cycle, which utilizes two turbines and two recuperators. Under the simulation condition considered in this study, it was confirmed that the design parameter has an optimal value for maximizing the net power in the supercritical carbon dioxide dual cycle.

• Journal of Advanced Marine Engineering and Technology
• /
• v.37 no.8
• /
• pp.829-835
• /
• 2013

This paper describes an analysis on exergy efficiency of proposed high-efficiency R717 OTEC power system to optimize the design for the operating parameters of this system. The operating parameters considered in this study include outlet pressure in an evaporator and high turbine, inlet pressure condenser and vapor quality at cooler outlet, respectively. The main results are summarized as follows : As the outlet pressure in an evaporator and vapor quality at cooler outlet of R717 OTEC power system increases, the exergy efficiency of this system increases, respectively. But outlet pressure in the high turbine, inlet pressure in the condenser of R717 OTEC power system increases, the exergy efficiency of this system decreases, respectively. And, incase of exergy efficiency of this OTEC system, the effect of inlet pressure in an evaporator and outlet pressure in the high turbine on R717 OTEC power system is the largest and the lowest among operation parameters, respectively.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2012.05a
• /
• pp.52-57
• /
• 2012

A liquid rocket system consists of a combustion chamber, a gas generator, a turbo pump, and a turbine, etc. Each component is connected by supply components such as valves, pipes, and orifices. Since each component has a combined effect on engine performance, preliminary analysis for overall system must be required before the conceptual design stage. Comprehensive analysis program considered the supply system has not been developed yet. In this paper, a supply component model of the liquid rocket engine has been designed after verification of each component. The gas generator cycle with supply components has been composed. The results of the cycle has been compared to those of the F-1 engine with the representative gas generator cycle.

• Transactions of the Korean Society of Mechanical Engineers B
• /
• v.34 no.2
• /
• pp.145-151
• /
• 2010

In this study, an absorption power cycle, which can be used for a low-temperature heat source driven power cycle such as geothermal power generation, was investigated and optimized in terms of power by the simulation method. A steady-state simulation model was adopted to analyze and optimize its performance. Simulations were carried out for the given heat source and sink inlet temperatures, and the given flow rates were based on the typical power plant thermal-capacitance-rate ratio. The cycle performance was evaluated for two independent variables: the ammonia fraction at the separator inlet and the maximum cycle pressure. Results showed that the absorption power cycle can generate electricity up to about 14 kW per 1 kg/s of heat source when the heat source temperature, heat sink temperature, and thermal-capacitance-rate ratio are $100^{\circ}C$, $20^{\circ}C$, and 5, respectively.

• Journal of Advanced Marine Engineering and Technology
• /
• v.34 no.4
• /
• pp.470-476
• /
• 2010

The thermodynamic performance of closed ocean thermal energy conversion (OTEC) cycle with 1 MW gross power was evaluated to obtain the basic data for the optimal design of OTEC. The basic thermodynamic model for OTEC is Rankine cycle and the thermal effluent from power plant was used for the heat source of evaporator. The cycle performance such as efficiency, heat exchanger capacity, etc. was analyzed on the temperature variation of thermal effluent. The saturated pressure of evaporator increased with respect to the increase of thermal effluent temperature, so the cycle efficiency increased and necessary capacity of evaporator and condenser decreased under 1 MW gross power. As the thermal effluent temperature increases about $15^{\circ}C$, the cycle efficiency increased approximately 44%. So, it was revealed that thermal effluent from power plant is important heat source for OTEC plant. Also, if there is an available waste heat, it can be transferred heat to the working fluid form the evaporator through heat exchanger and cycle efficiency will be increased.

• Journal of Advanced Marine Engineering and Technology
• /
• v.38 no.9
• /
• pp.1101-1105
• /
• 2014

Ocean Thermal Energy Conversion(OTEC) which uses the temperature difference between warm surface sea-water and cold deep sea-water to produce electric power is the promising technology. OTEC is able to be utilized as the $CO_2$ reducing technology by using the consistent temperature differential, while the system efficiency is very low. Thus, the design and development of a efficient turbine is essential to improve the system efficiency for OTEC. In this study, a 100kW-class radial inflow turbine using R32 was designed for OTEC and this turbine's performance was estimated by analysis of CFD. According as the simulation results, turbine's geometry was corrected. The radial inflow turbine satisfying the requirements is designed by the repeated attempts.

• Journal of the Korean Society for Marine Environment & Energy
• /
• v.17 no.2
• /
• pp.116-121
• /
• 2014

In order to study the improvement of the multi stage regeneration cycles, muti-stage processes were applied to the cycles, respectively or together. The kinds of the cycles are multi stage reheater cycle (MS) and multi stage reheater regeneration cycle (MSR). Working fluid used was R134a and R245fa. Temperature of the heat source was $65^{\circ}C$, $75^{\circ}C$, and $85^{\circ}C$, and temperature of the heat sink was $5^{\circ}C$. Optimization simulation was conducted for improving the gross power and efficiency with multi stage reheater regeneration cycle for ocean thermal energy conversion(OTEC) with changing of a heat source, kind of the working fluid, and type of the cycle. Performance analysis of the various components was simulated by using the Aspen HYSYS for analysis of the thermodynamic cycle. R245fa shows better performance than R134a. This paper showed the most suitable working fluid with changing of a heat source and the kinds of working cycle. Compared to each other, MS showed better performance at gross power and MSR showed higher cycle efficiency.

• 한국신재생에너지학회:학술대회논문집
• /
• 2008.05a
• /
• pp.361-363
• /
• 2008

탄소 개질반응은 $1200^{\circ}C$(도1) 이상에서 모든 탄화물질과 수분 또는 $CO_2$ 사이에서 흡열/환원반응이 일어나서 합성가스를 생성한다. 개질반응로는 산화반응로와 연결되어, 수소가스와 CO 가스의 혼합인,합성가스가 산화반응로 내에서 산소가스와 연소하여 열과 $H_2O+CO_2$를 생성하여 환원 반응로 내로 유입되어, 환원 반응로를 $1200^{\circ}C$ 이상으로 유지하고, $H_2O$와 $CO_2$는 석탄 속의 모든 탄소를 CO로 개질한다(도2). 동시에 수소가스가 생성되어 합성가스를 생성하게 된다. 석탄 속의 비탄소 물질인 슬래그(Slag)는 개질로 내에 남게 되는데, 개질로를 슬래그 융점(non-fluid point) 이하에서 고체상태로 포집함으로서 Fly-ash로 처리된다. 개질로 내의 온도를 $1200{\sim}1300^{\circ}C$(석탄 슬래그 융점)로 유지함으로서 개질반응이 지속되어 합성가스가 생성된다. IGCC 시스템에서는 합성가스를 가스터빈 속에서 $O_2E가스와 연소하여 고온의 가스를 생성하여 터빈을 가동해 발전을 하고 배출가스를 $1500{\sim}1700^{\circ}C$에서 배출한다. 재래식 IGCC(도4)에서는 ${\sim}1500^{\circ}C$의 배출가스를 열교환 시스템에 의해 증기를 생성하여 Steam turbine(증기터빈)을 가동하여 추가 전력을 생산했다. 그러나 본 시스템에서는 배출가스(증기와 $CO_2E 가스)를 위의 개질로에 유입하여 개질로 온도를 $1200{\sim}1300^{\circ}C$로 유지함으로서 더 많은 합성가스를 생성 하게 된다(도3). 이렇게 하여 Oxidation-reduction cycle을 형성하게 된다. 새로운 IGCC 시스템에서 가스 터빈의 배출가스가 석탄 개질로에 연결되고 석탄개질로의 합성가스 출구가 가스터빈의 가스 입구에 연결됨으로서,외부에너지 주입 없이 지속 가능한 가스화 반응과 터빈 사이클(Cycle)을 완성하여 IGCC 시스템의 석탄 열효율을 1단계 상승시켰다. 이렇게 설계된 석탄가스화기는 Lurgi형 석탄가스화 기와 달리 석탄개질반응의 효율을 높일 수 있고, 슬래그 처리가 간단하기 때문에 석탄가스화기가 소형화 될 수 있으며 슬래그(Slag)용융에 따른 석탄가스화기의 외벽손상을 피할 수 있다.

• 유체기계공업학회:학술대회논문집
• /
• 2006.08a
• /
• pp.531-534
• /
• 2006

This study is concerned with radial turbine design and performance improvement of a turbo generator system, which is used for maximizing performance of a 250kW MCFC fuel cell system. A preliminary design of a radial turbine has been performed under the thermodynamic and fluid-dynamic conditions determined by a cycle analysis of the MCFC BOP system. Basic demensions are determined by a meanline analysis and calculation of radial variation at the exit of the turbine. The turbine impeller is designed and modified by iterative processes of three dimensional flow analysis.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2008.11a
• /
• pp.167-170
• /
• 2008

A TBCC(Turbine Based Combined Cycle) engine performance design method for reusable launch vehicles flying both in subsonic and supersonic regime was proposed. The TBCC consists of turbo jet engines and ramjet engines, operating individually or together according to operation schedule. The performance scheme of turbojet and ramjet was validated and the combined engine performance of the TBCC at a typical flight condition was analyzed.