• Journal of the Korean Society for Marine Environment & Energy
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• v.14 no.4
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• pp.301-306
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• 2011

The paper presents an analysis of the heating cycle and discusses a desalination cycle that uses lowtemperature seawater. The basic heating cycle model is the heat pump cycle, and seawater desalination is usually performed by the indirect freezing desalination method. The low temperature of the seawater (below $5^{\circ}C$) acts as the heat source of the evaporator. R-134a, R-1234yf, R-600a are used as working fluids. In the 2-stage compression cycle, the compressor's work decreased by about 15.6% from that in the 1-stage compression cycle. Further, the COP in the 2-stage cycle was 17.6% higher than that in the 1-stage cycle. In the indirect desalination cycle, the energy per unit fresh water productivity in the 2-stage cycle was 19.8% lower than that in the 1-stage cycle.

• Proceedings of the KAIS Fall Conference
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• 2010.11b
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• pp.684-687
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• 2010

본 논문은 복합사이클 발전플랜트의 폐열회수 보일러 최적운전 및 최적설계에 대한 새로운 접근 방법을 도출하기 위해 폐열회수 보일러에서 발생되는 증기로 증기터빈을 구동하는 하부사이클 효율을 검토하였다. 열역학 제1법칙 해석을 통해 하부사이클 에너지 평형을 검토하였고, 열역학 제2법칙을 통해 엑서지 평형을 검토하였다. 하부사이클 효율이 최대가 되는 폐열회수 보일러를 설계하기 위해서는 열역학 제1법칙을 해석할 경우 하부사이클 전체를 해석하여야 함을 알 수 있다. 하지만, 열역학 제2법칙을 통한 엑서지 해석을 행할 경우 하부사이클 효율이 최대가 되는 증발온도와 폐여회수 보일러에서 소모되는 엑서지가 최소가 되는 점이 일치함을 알 수 있었다. 따라서 본 논문을 통해 폐열회수 보일러에서 소모되는 엑서지 해석을 통해 하부사이클 효율이 최대가 되는 폐열회수 보일러 최적화가 가능함을 알 수 있다.

• Transactions of the Korean Society of Mechanical Engineers
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• v.13 no.6
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• pp.1231-1237
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• 1989

본 연구에서는 이러한 단열해석상의 문제점을 해결하기 위한 하나의 방식이 광방법으로서 적절한 가정을 도입하여 단열모델에 대한 해석적인 근사해를 시도하였다. 실제조건에 부합하면서도 간편하며 경제적인 해석방법의 확립은 VM 사이클로 작동되는 냉동기에 대한 최적설계의 중요한 기초가 될 것이다. 해석모델의 정립, 종속변수에 대한 근사해, 성능평가에 필요한 열역학적량들을 종속변수의 해석적 함수형태로 표시하는 과정을 내용에 포함한다.

• Journal of Energy Engineering
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• v.18 no.2
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• pp.93-100
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• 2009

An exergy analysis is carried out for the regenerative wet-compression Brayton cycle which has a potential of enhanced thermal efficiency owing to the reduced compression power consumption and the recuperation of exhaust energy. Using the analysis model, the effects of pressure ratio and water injection ratio are investigated on the exergy efficiency of system, exergy destruction ratio for each component of the system, and exergy loss ratio due to exhaust gas. The results of computation for the typical cases show that the regenerative wet-compression gas turbine cycle can make a notable enhancement of exergy efficiency. The injection of water results in a decrease of exergy loss of exhaust gas and an increase of net power output.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.46-51
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• 2012

This study aims to develop the performance analysis program on the staged combustion cycle of the liquid rocket engine using liquid oxygen(LOx) as oxidizer, liquid hydrogen(LH2) and RP-1 as fuel. The developed analysis program can obtain the propellant mass flow rate, the specific impulse, and representative design values of engine components for the required thrust satisfying pressure, mass flow, and energy balance conditions. The analysis results show that the the specific impulses (Isp) compared to those of the real engines have been less than 1%. With additional constraints, the program will be improved for the system optimization.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.3
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• pp.104-111
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• 2019

A separate type rotary engine consisting of a compressor and an expander is under development. The engine motoring, compressor pressure, and fuel combustion have been tested with the initial prototype for operability checks of the mechanism. This paper describes an engine cycle analysis method designed specifically for this new-concept engine. The unique operational mechanism of the engine and the thermodynamic properties of each step of air intake, compression, filling of combustion chamber, combustion, expansion and exhaust were analyzed. The cycle efficiencies of this engine according to various engine design parameters as well as the cooling effect of compressed air between the compressor and expander can be easily calculated with this method; further, some case studies are presented in this paper.

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

• Journal of the Korean Society of Propulsion Engineers
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• v.24 no.5
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• pp.21-33
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• 2020

In this study, the program for system analysis of an expander cycle rocket engine using liquid hydrogen as a fuel was developed. The properties of hydrogen were considered by the ratio of isomers with temperature. The analysis procedure was established with the open and closed types of the expander cycle engine and the simulation methods were suggested for each component. To validation of the analysis program, we compared the performance of the engine operating point and the analysis results performed overseas for Vinci and SE-21D, which are expander cycle engines. As a result of the analysis, the main performance factors of the system, such as the mass flow of the propellant, specific thrust, and power, except for some of the inaccurate input information, showed high accuracy with an error of around 1-2%.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.40 no.9
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• pp.589-596
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• 2016

Recently organic flash cycle (OFC) has been proposed which is a vapor power cycle where heat addition occurs with the working fluid remaining in the liquid state. This study proposes a modified OFC with regeneration and carries out thermodynamic performance analysis of the system utilizing low-temperature heat source in the form of sensible energy. Effects of working fluid and flash temperature are systemically investigated on the system performance such as net power production and thermal efficiency. Results show that the net power production has a peak value with respect to the flash temperature but the thermal efficiency increases with the flash temperature. The regenerative system shows higher thermal efficiency compared to the original OFC and improved potential for recovery of low-temperature heat sources.

• Aerospace Engineering and Technology
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• v.11 no.1
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• pp.145-157
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• 2012

The novel limit cycle analysis of the attitude control system using jet thrusters was presented based on a phase plane method by paper. It was shown in the software simulation results that the analysed results of the limit cycle was more accurate than those of the Haloulakos' method. But it was not verified in the real system. The proposed method is verified in the reaction control system for KSLV-I via an real time hardware in the loop simulation. It can be shown in this test that analyzed result of the limit cycle is very accurate.