• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.318-321
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• 2005

The design and performance test of a low NOx gas turbine combustor to be used in 55kW class micro-gasturbine engine was performed in KARI's combustion test facility. The combustor is reverse flow-can type for easy installation of injector and other parts and LNG is used as fuel. The performance targets are $99.5\%$ combustion efficiency, less 10ppm NOx, $30\%$ patten factor and $4\%$ pressure loss. Most of the performances required are satisfied.

• IE interfaces
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• v.17 no.2
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• pp.190-199
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• 2004

Recently, many enterprises are introducing a workflow management system for the successful implementation of BPR(Business Process Reengineering). Proposed in this study is the workflow management system which has a light-weight component structure and an XPDL(XML Process Definition Language) file interpretation facility. The XPDL is the standard process definition exchange format developed by WfMC(Workflow Management Coalition). The major causes of inefficiency at current implementations of workflow management systems are the centralized workflow engine structure and the use of proprietary workflow definition format among most solutions. The proposed light-weight component structure in this study is the intermediate structure that takes the strength of both centralized and distributed workflow engines. And a prototype workflow system which uses an XPDL process definition file as input is developed through the thorough analysis of functional requirements.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.705-708
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• 2011

Ejector system can induce the secondary flow or affect the secondary chamber pressure by both shear stress and pressure drop which are generated in the primary jet boundary. Ejectors are widely used in a range of applications such as a turbine-based combined-cycle propulsion system and a high altitude test facility for rocket engine, pressure recovery system, desalination plant and ejector ramjet etc. The primary interest of this study is to set up an design procedure on the configuration and operating condition of multi-ejector for the various high altitude simulation.

• Journal of the Korean Society of Combustion
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• v.13 no.4
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• pp.37-46
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• 2008

Performance test of 5MW class gasturbine combustor was carried out at combustor test facility of KARI(Korea Aerospace Research Institute). The combustor is dry low NOx type premixed combustor and fuel is natural gas. The characteristics of combustor were measured including emission, pressure pulsation and exit temperature distribution. Optimum operation point of combustor was found by changing parameters like fuel ratio between pilot and main burner. The test result showed that the combustor performance is sufficient to satisfy the gasturbine system requirement.

• Proceedings of the Korean Operations and Management Science Society Conference
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• 2003.05a
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• pp.118-122
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• 2003

본 연구를 시물레이션방법을 이용한 실린더 헤드라인 생산설비의 적정계획 및 성능산정을 위해 가용한 생산설비의 자료들로부터 요구되는 생산능력을 만족하는 생산설비를 구성한다. 구성된 설비들은 가용한 생산설비 운영조건을 고려한 가상의 시물레이션 모델로 구축하여 생산설비의 적정 구성 및 공정간의 재고 등을 산정한다. 시스템 성능 산정을 위해 본 연구에서는 AutoMod 시물레이터를 이용하여 실린더 헤드라인의 생산설비계획 문제에 적용한다. 본 연구는 다수의 생산설비를 이용한 설비계획 연구시 사전 분석과 능력산정 및 기존의 설비 운영 조건에 따른 생산능력산정에 유용할 수 있으며 3차원 동영상으로 분석 결과를 제시할 수 있다.

• Transactions of the Korean Society of Mechanical Engineers
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• v.19 no.8
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• pp.1964-1971
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• 1995

In the present study, the performance characteristics of a centrifugal air compressor were investigated experimentally. The PC controlled performance test facility for a centrifugal air compressor driven by an electric motor with a gear box to achieve higher compressor rotating speed was set up in the present study. The performance test for a turbocharger compressor of a diesel engine was conducted, and in a case of 34,800 rpm, pressure ratio 1.18, flow rate 0.09kg/s, compressor efficiency 61% were investigated. Adiabatic power for a tested compressor showed maximum value at mass flow ratio 0.8. The value of mass flow ratio of maximum efficiency was about 0.37, it was independent of compressor rotating speed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.05a
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• pp.171-176
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• 2003

A Test Facility was established to carry out the integrated propulsion performance tests(IPPT). To perform IPPT's with maximum safety, an emergency blockage system was investigated. An emergency blockage system using combustion chamber pressure and acceleration signals was set up to monitor ignition delay and fail, flame out, propellant feeding status, unstable combustion and excessive structural vibration. With such system, the maximum safety could be secured by rapid judgement and follow-up measures, which made IPPT's be safely completed.

• The KSFM Journal of Fluid Machinery
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• v.8 no.6 s.33
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• pp.26-32
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• 2005

1.6 MW class supersonic partial admission impulse turbine has been designed and tested in Korea Aerospace Research Institute for the liquid rocket engine application. The test has been performed using a high pressure air source facility in KARI. For the turbine power absorption, a hydraulic dynamometer has been used. Appropriate similarity relations are used for the determination of test condition. Various settings of turbine pressure ratio and rotational speed are tested to investigate global turbine characteristics. From measured data, parameters related to the turbine design are derived and validated.

• 유체기계공업학회:학술대회논문집
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• 2004.12a
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• pp.125-131
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• 2004

1.6 MW class supersonic partial admission impulse turbine has been designed and tested in Korea Aerospace Research Institute for the liquid rocket engine application. The test has been performed using a high pressure air source facility in KARI. For the turbine power absorption, a hydraulic dynamometer is used. Appropriate similarity relations are used for the determination of test condition. Various settings of turbine pressure ratio and rotational speed are tested to investigate global turbine characteristics. From measured data, Parameters related to the turbine design are derived and validated.

• Proceedings of the SAREK Conference
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• 2008.06a
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• pp.214-219
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• 2008

In this study, medium capacity EHP and GHP for air-conditioning a building with a floor area of $1,200\;m^2$ are compared economically. To consider all the factors of initial and operation costs effectively, an annual equal payment method is proposed. For the initial cost, equipment, construction, installation, electric facility, financial subsidy and tax cut are considered. Basic electricity, energy(electricity and gas), space charge, labor, insurance and repair are considered for the operation cost. Under the assumptions made in this study, overall cost of EHP is less than that of GHP. However, different outcome may result if different assumptions are made. This study is useful for performing an economic evaluation of various air-conditioning systems.