• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1999.10a
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• pp.5-5
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• 1999

3단형 과학로켓(KSR-III)의 기본형 및 응용형에 공통으로 사용되는 주엔진은 액체산소를 산화제로, 케로신을 연료로 사용하는 액체추진기관이다. 엔진 기본설계를 통하여 로켓 임무 요구사항에 부합되도록 엔진 각 부분의 기본제원을 설정하였고, 엔진의 형상을 결정하였다. 설계된 엔진의 성능검증 작업은 분사시험용 엔진, 축소형 엔진, 엔지니어링 모델 및 비행시험모델의 설계/제작/시험을 통하여 순차적으로 수행할 계획이다. 본 연구는 3단형 과학로켓 엔진의 기본설계 및 성능검증 계획에 관한 것이다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.2
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• pp.116-122
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• 2016

The performance characteristics of a TBCC engine considering the transition mode from a turbojet to a ramjet engine has been investigated. The performance of each engine was proposed and a transition mode of the TBCC engine has been evaluated by adjusting the operating rate of the ramjet engine and turbojet engine performance changes continuously. Based on the transition model, it was confirmed that the performance is continuously changed at various flight Mach numbers and altitudes. The performance characteristics including thrust and specific impulse considering various flight conditions and transition mode were analyzed, which testifies characteristics of the engine itself, as well as transition of the combined cycle.

• Journal of Aerospace System Engineering
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• v.13 no.1
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• pp.38-46
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• 2019

There is a growing interest in engine diagnostic technology for gas turbine engines. An engine simulation program, precisely simulating the engine performance, is required in order to apply it to the engine diagnosis technology for engine health monitoring. In particular, the simulation program can predict not only design point performance but also off-design point and partial load performance in accurate. So the engine simulation program for the 2-spool separate flow type turbofan engine was developed and the JT9D-7R4G engine of PW(Pratt & Whitney) was analyzed. The steady-sate performance analysis is conducted at both design and off-design points in flight path and the differences between analysis results of takeoff and cruise conditions are compared. The effect of Reynold's correction method was analyzed as a scaling method of the engine component performance. The simulation results was compared with NPSS.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.3
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• pp.269-278
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• 2011

The details of engine manufacturer's engine simulations are generally kept secret and only those parameters that are used for control purposes are accessible to users. Hence, there is often only a limited amount of data accessible for creating a performance model of the engine. The performance modeling of a low bypass turbofan engine for supersonic aircraft is described herein. The Pratt and Whitney F100-PW-229 engine has been employed for low bypass turbofan engine performance modeling. Published data from the open literature are used as initial data for building the F100-PW-229 engine performance model. The unknown components' characteristics were estimated by optimization of parameters using by adaptive random search method and sensitivity analysis with respect to design variables. The engine performance model was evaluated to be properly constructed through the comparison of result of engine performance analysis and engine deck data.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.289-292
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• 2005

Because of accumulation of operation time, the performance of main components(compressor, combustor, turbine, etc.) come to be deteriorated in gas-turbine engine. So, high reliability and minimun of expense are important problem for engine manufacturer and user in operation of gas-turbine engine. In this study, the diagnostic code of the engine performance using the thermodynamic sensitivity between the sensed parameters and the health parameters has been developed without an application of the commercial program. The single performance deterioration of the turbo-shaft engine has been estimated with this code.

• Journal of the Korean Society of Propulsion Engineers
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• v.17 no.1
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• pp.80-88
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• 2013

In currently developed engine condition monitoring systems, most field engine maintenance engineers have difficulties to use them in fields due to complexity, unpractical use, lack of understanding, etc. Therefore a practical usable engine condition monitoring system must be needed. This work proposes a practical performance condition monitoring of a small turbojet engine through comparing between the on-line performance monitoring data and the initial clean performance data calculated by the base engine performance model. Moreover the proposed monitoring system checks the gas path components' on-line health condition through comparing the component performance characteristics between the running engine represented as a deteriorated engine or a degraded engine and the base engine performance model represented as a clean engine. The proposed condition monitoring system is coded in a friendly GUI type program for easy practical application by a commercial tool, MATLAB/SIMULINK and LabVIEW.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.05a
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• pp.133-136
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• 2003

우주발사체의 2단에 사용가능하며, 케로신과 액체산소를 추진제로 하는 10톤급 액체로켓엔진 (LRE)에 대해 노즐 설계 변수와 성능 특성과의 관계를 파악하고 노즐 성능의 개선을 위해 노즐 형상에 따른 성능 해석을 수행하였다. 본 연구에서 10톤급 LRE의 형상을 설계하였으며, 기존의 일차원 성능해석 방법과는 달리, 2차원 유동 해석 결과를 이용한 성능 해석을 수행하기 위해 노즐 성능해석용 코드를 개발하였으며, 액체 산소/메탄 엔진 (LNG 엔진)에 대한 지상 연소시험 결과와 비교, 검토하여 노즐 성능해석 코드를 검증하였다.

• Journal of the Korean BIBLIA Society for library and Information Science
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• v.22 no.2
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• pp.141-160
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• 2011

This study suggested knowledge base and search engine for the libraries that have the largescaled data. For this purpose, 3 components of knowledge bases(triple ontology, concept-based knowledge base, inverted file) were constructed and 3 search engines(search engine JENA for rule-based reasoning, Concept-based search engine, keyword-based Lucene retrieval engine) were implemented to measure their performance. As a result, concept-based retrieval engine showed the best performance, followed by ontology-based Jena retrieval engine, and then by a normal keyword search engine.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.16 no.5
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• pp.3030-3034
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• 2015

It is important to consider powertrain cooling performance, when engine is applied to new vehicle. If the performance is poor, engine will be damaged by overheating. But, the development timing of engine is faster than timing of vehicle, it is difficult to test the cooling performance of new engine and vehicle. In this study the powertain cooling performance was estimated with some test and calculation data. First, the heat rejection test was conducted. From this test, the heat rejection data at required rpm and load was acquired. Second, coolant flow test was conducted. From this test coolant flow rate to radiator was measured. Then engine torque and rpm was calculated from vehicle load and speed. Vehicle load and speed was calculated from test mode. Then by comparing these data, the powertrain cooling performance was estimated.

• Proceedings of the Korean Society of Tribologists and Lubrication Engineers Conference
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• 1991.11a
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• pp.8-13
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• 1991

엔진유는 엔진내에서 사용됨에 다라 마모방지제의 소모, 브로바이 가스의 혼입, 열화생성물과 첨가제간의 반응등의 영향을 받아 서서히 열화되기 시작하며, 아울러 마모방지성능 또한 변화되어간다. 열화생성물 중의 어떤 극성산화물이나 고분자생성물은 엔진마모의 감소에 기여하나, 일부 산성생성물은 부식마모를 일으킬 수도 있으며, 엔진내에서 발생되는 마모분중에는 어브레시브 마모를 발생시키는 것도 있다. 또한, 브로바이 생성물중에는 마찰면을 직접 부식시키는 성분도 있으며, 그외 부식성이 약한 브로바이 성분들도 첨가제와의 반응을 통하여 간접적으로 엔진유의 마모방지성능에 영향을 미친다. 필자는 최근의 연구에서 엔진유의 마모방지성능은 엔진에서의 열화정도에 달 현격히 변화하며, 또한 사용유의 전산가증가치와 마모량간에는 명확한 상관관계가 있다는 것을 보고한 바 있다. 본보고에서도 사용유에 함유되어 있는 성분중 마모방지성능에 크게 영향을 미치는 하이드로퍼옥사이드를 선택하여, 그 함유유인 모델열화유로 윤활하는 마모시험을 수행하여 얻은 결과에 관하여 검토하고자 한다.