• 한국신재생에너지학회:학술대회논문집
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• 2008.05a
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• pp.630-633
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• 2008

Geothermal heat pump systems use the earth as a heat source in heating mode and a heat sink in cooling mode. These systems can be used for heating or cooling systems in farm facilities such as greenhouses for protected horticulture, cattle sheds, mushroom house and etc. A horizontal type means that a geothermal heat exchanger is laid in the trench buried in 1.2 to 1.8 m depth. Because a horizontal type has advantages of low installation, operation and maintenance costs compared to a vertical type, it is easy to be adopted to agriculture. In this study, to heat and cool farm facilities and obtain basic data for practical application of horizontal geothermal heat pump system in agriculture, a horizontal geothermal heat pump system of 10 RT was installed in greenhouse. Heating and cooling performance of this system was estimated. The horizontal geothermal heat pump used in this study had heating COP of 4.57 at soil temperature of $14^{\circ}C$ with depth of 1.75m and heating COP of 3.75 at soil temperature of $7^{\circ}C$ with the same depth. The cooling COP was 2.7 at ground temperature at 1.75m depth of $25.5^{\circ}C$ and 2.0 at the temperature of $33.5^{\circ}C$.

• Journal of the Korean Society for Geothermal and Hydrothermal Energy
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• v.3 no.1
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• pp.11-16
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• 2007

The purpose of this study is to use the CFD(Computational Fluid Dynamics) method for the ground source heat pump(GSHP) system with vertical U-tube ground heat exchangers. In order to predict LWT(leaving water temperature) in the length of time, This simulation is used by utilizing FLUENT which is commercial CFD code. It was performed by based on four boreholes in the field. Comparing with the results of CFD and field measurement for LWT, the results of CFD was presented very good agreement with 1.0% average difference.

• Journal of the Korean Society for Geothermal and Hydrothermal Energy
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• v.10 no.1
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• pp.7-13
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• 2014

This study intends to analyse the economical aspect of a GSHP(Ground Source Heat Pump) system compared to the conventional system which is consisted with a boiler and a chiller. This study has simulated four systems in Incheon. It developed and analyzed for applications in a residential and an office building which was based on the hourly EPI(Energy Performance Index, $kWh/m^2yr$). Case 1 is utilizing a boiler and a chiller to meet heating and cooling demand of a house. Case 2 is utilizing the same conventional set up as Case 1 of a office. Case 3 is summation of Case 1(house) and 2(office) systems and loads. And Case 4 is utilizing a GSHP to meet the combined loads of the house and office. The method of the economic assessment has been based on IEA ECBCS Annex 54 Subtask-C SPB(Simple Payback) method. The SPB calculated the economic balanced year of the alternative system over the reference system. The SPB of the alternative systems (GSHP) with 10%, 30% and 50% initial incentive has been calculated as 9.38, 6.72 and 4.06 year respectively while the SPB without initial incentive of systems was 10.71 year.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.235-239
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• 2005

A 30-tonf-class fullscale thrust chamber for the application to a LEO SLV has been combustion tested over the wide ranges of a mixture ratio and a chamber pressure. The thrust chamber designed for an open cycle engine with a turbopump was tested with a ablative combustion chamber instead of a regenerative chamber to first evaluate its performance and function. The test results revealed stable combustion characteristics. The hardware survived the harsh environment and showed very sound functional characteristics. The estimated combustion efficiency of the chamber turned out to be 95% and a specific impulse at sea level was estimated as 254sec, which are comparable to or above the predicted design values.

• Journal of the Korean Society of Propulsion Engineers
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• v.8 no.4
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• pp.102-108
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• 2004

A layout of regenerative liquid rocket engine using turbo pump has been designed for development of high performance liquid rocket engine. each components of engine system was placed by considering assembly and characteristic. first stage engine system is controled by one plane of axis gimballing and composed of four engine assembly to cluster with launch vehicle. second stage engine system is controled by two plane of axis gimballing and composed of one engine assembly. assembly and disassembly Processes and required program have been developed. various shape of instruments were also developed for carrying out assembly and disassembly process efficiently.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.162-165
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• 2004

A layout of regenerative liquid rocket engine using turbo pump has been designed for development of high performance liquid rocket engine. each components of engine system was placed by considering assembly and characteristic. first stage engine system is controled by one plane of axis gimballing and composed of four engine assembly to cluster with launch vehicle. second stage engine system is controled by two plane of axis gimballing and composed of one engine assembly. assembly and disassembly processes and required program have been developed. various shape of instruments were also developed for carrying out assembly and disassembly process efficiently

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.4
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• pp.40-46
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• 2006

A 30-tonf-class fullscale thrust chamber for the application to a Low-Earth-Orbit Space Launch Vehicle has been combustion tested over the wide ranges of a mixture ratio and a chamber pressure. The thrust chamber designed for a pump-fed open cycle engine was tested with an ablative chamber instead of a regenerative one for the initial evaluation of its performance and function. The test results revealed stable combustion characteristics. The hardware survived the harsh environment and showed very sound functional characteristics. The measured combustion efficiency turned out to be 95% and a specific impulse at sea level was estimated as 254sec, which are comparable to or above the predetermined design values.

• Journal of the Korean Society of Propulsion Engineers
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• v.11 no.4
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• pp.38-45
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• 2007

A liquid rocket engine fuel-rich gas generator has been developed for the first time in the country, which can produce combustion gas over the rate of 4 kg/s at 900 K and 58 bar. The gas is not only for driving a turbopump but also for providing heat source for propellant supply tanks. The final design of the gas generator had been fixed based on the concept and preliminary development tests, and was validated through structure and heat transfer analysis. The manufacturing involved precision machining, surface finish, and special welding technique. The final assessment on the characteristics of ignition and combustion had been carried out for two different versions of injector heads. This concluded that the present product satisfies the development requirements such as spatial temperature distribution and the development has been successful.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.181-185
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• 2006

A liquid rocket fuel-rich gas generator developed for the first time in the country can produce combustion gas over the rate of 4 kg/s at 900 K and 58 bar. The gas can be used not only for driving a turbopump but also for providing heat source for propellant supply tanks. The final design of the gas generator has been fixed based on the concept and preliminary development tests, and was validated through structure and heat transfer analysis. The manufacturing involves precision machining, special surface finish, and welding techniques. The final assessment on the characteristics of ignition and combustion had been carried out through five combustion tests. This concluded that the present product satisfies the development requirements.

• 한국신재생에너지학회:학술대회논문집
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• 2010.11a
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• pp.157-157
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• 2010

RDF는 장기저장이 가능한 것이 특징 중의 하나이지만, 우리나라보다 앞서 대량저장을 시작한 일본의 RDF 저장 사일로에서 폭발사고가 발생한 사례가 있어, RDF를 실제로 저장하여 RDF 온도 및 가연성가스 발생상황 등을 장기간 감시 측정하여 사일로 안전관리지표를 도출하였다. 실험에 사용한 RDF 저장조는 직경 3.1m, 높이 11.4m의 사일로방식으로 제작하였다. RDF 저장량은 $70m^3$이었으며, 저장기간은 475일이었다. 사일로에는 15개의 열전대를 설치하여 사일로 표면, 직경방향 1.2m 지점 및 기온을 측정하여 수직방향 및 수평방향의 온도변화를 분석하였다. 가스 샘플링포트는 온도측정지점과 동일한 위치 설치하여 진공펌프로 흡인하여 테트라 백에 포집하여 GC로 분석하였으며, 가스샘플링은 17회 실시하였다. 비교적 대형 저장설비이고 RDF가 열전도성이 낮은 물질임에도 불구하고 사일로 내부온도는 기온보다는 높았지만, 기온의 영향을 많이 받아 7월에 정점, 1월에 하점을 나타내는 사인곡선과 같은 패턴을 보였다. 측정지점별 온도차는 수평방향 보다 수직방향에서 높게 나타났으며, RDF층으로 전열 및 축열이 진행되고 생화학반응을 촉진시키는 상승작용의 결과로 월평균온도가 $49^{\circ}C$를 나타내는 지점도 있었다. 실제 사일로는 RDF의 투입과 배출이 연속적으로 진행되어 방열이 이루어지므로 하계에 대량저장을 실시하지 않는 한 RDF층 내부에서 생화학적 반응열이 생성되더라도 $40^{\circ}C$를 상회할 가능성은 매우 희박할 것으로 판단된다. RDF 저장시 발생하는 가스는 대부분 $CO_2$였으며, 미량이지만 $H_2$, CO, $CH_4$도 검출되었다. 가연성 가스는 저장 후 2개월 동안은 발생하지 않았으며, 하계에는 타 계절에 비해 상대적으로 고농도로 검출되었다. 발생가스와 온도 및 $CO_2$와 $H_2$농도의 상관성은 높게 나타나지 않았지만, 정의 상관관계를 나타내었다. 저장한 RDF의 성상(수분, 발열량, 분화물)은 실험개시 전의 RDF분석결과와 실험종료 후 분석결과에서는 큰 차이가 나타나지 않았다. 따라서 RDF의 안전 저장을 위해서는 (1) 반입되는 RDF성상관리, (2) RDF가 2개월 이상 장기간 체류하는 데드스페이스가 발생하지 않고 선입선출이 확보되는 저장조 설계, (3) 사일로 내부에 최소 3개 이상의 지점에서 온도를 측정하여 상시감시하고 $40^{\circ}C$이하로 관리, (4) 발생가스는 CO, $CO_2$, $H_2$, $CH_4$ 등의 가연성가스를 모두 측정 감시하는 것이 바람직하지만, 최소 $CO_2$와 $H_2$는 상시감시하고 각각 1%와 100ppm 미만으로 관리, (5) 배풍기 등을 이용한 상시 환기실시, (6) 하계에는 대량저장이 이루어지지 않도록 저장조 운용계획 수립 등을 실시해야 한다.