• Aerospace Engineering and Technology
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• v.2 no.2
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• pp.186-198
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• 2003

Small sized engine test stand has been built up and modified to measure the engine performance for 15g class small UAV propulsion systems. An engine performance standard test stand was developed in order to validate the prediction performance and to shoot trobles. The performance data were measured and analyzed for the newly developed gasoline engine.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.239-248
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• 2010

This paper dealt with the Performance Modeling of a low-bypass turbofan engine for supersonic aircraft. The Pratt and Whitney F100-PW-229 engine has been employed for low-bypass turbofan engine performance modeling. Generally, The complete commercially-classified information concerning the engine are unknown. So, Components' generic characteristics are described and assumptions made in order to model the F100-PW-229 engine performance model. All the analysis has been undertaken using published data taken from the open literature. The results of the Engine Performance using Gasturb11 showed that the Engine performance model was evaluated to be properly constructed.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.6
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• pp.79-88
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• 2010

This paper dealt with the performance modeling of a low bypass turbofan engine for supersonic aircraft. The Pratt and Whitney F100-PW-229 engine has been employed for low bypass turbofan engine performance modeling. Generally, the complete commercially-classified informations concerning the engine are unknown. The components' generic characteristics and assumptions made in order to build the F100-PW-229 engine performance model using by the published data from the open literature as basic data are described. Through the comparison of engine performance model's analysis data using Gasturb11 with engine deck data showed that the engine performance model was evaluated to be properly constructed.

• LP가스
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• s.71
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• pp.49-53
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• 2000

대형디젤엔진의 대체용으로 LPG 엔진을 개발함에 있어서 차세대 연료공급방식인 LPG 연료의 액상분사방식을 채택하여 기존의 믹서방식의 연료공급시스템을 가진 LPG 엔진보다 고출력, 고효율, 저공해성을 추구하고자 하였다. 이를 위한 기초연구로서 먼저 단기통 연소엔진을 이용하여 대형엔진에 LPG 연료 적용 가능성, 액상분사 시스템을 포함한 여러 가지 연료공급방식에 따른 엔진의 성능파악, 대형엔진에 적합한 최적 선회비의 결정, 연료조성에 따른 엔진성능의 변화 등을 알아보았다. 실험결과, 대형엔진에 LPG 연료의 적용은 아무런 문제점이 없었으며 LPi 연료공급방식은 다른 방식에 비해서 10%정도의 체적효율 및 출력의 증가를 확인할 수 있었다. 최적의 선회비는 2.0 부근에서 형성되었고, 연료 조성은 프로판 대 부탄의 비율이 60 : 40에서도 정상적으로 운전됨을 확인하였다. 시제품 엔진의 경우, 과급방식의 KL6i 엔진을 개발하기 앞서 좀더 기술적 접근이 용이한 자연흡입방식의 K-1엔진의 개발이 선행되었으며 현재 개발 진행중인 K-1엔진의 성능평가 결과, 기존의 디젤엔진에 비해 출력성능이 20% 정도 향상됨을 확인할 수 있었다. 특히 대형차량에서 중요시 생각되는 저속토크 성능이 매우 우수한 것으로 파악되었다. 이러한 결과를 바탕으로 단기통 연소엔진에서 확인된 최적화된 연료조성과 선회비를 향후 K-1엔진에 적용할 예정이다. 최근 열린 가스학회 추계발표회와 LPG자동차세미나의 주요내용을 게재한다.

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

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.62-67
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• 2004

This paper investigates the off-design performance of methane-fueled air turbo ramjet(ATR) engine in subsonic flight speed range. The ATR engine was modeled and simulated numerically. Each component was modeled to enable their off-design calculation. Compressor operating point was determined by flow matching with nozzle, and turbine by work matching. The ATR engine exhibited quite different off-design behavior compared to the conventional gas turbine engine.

• 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 KAIS Fall Conference
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• 2012.05b
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• pp.671-673
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• 2012

본 연구에서는 상용 엔진 해석프로그램인 GT-Power를 이용하여 디젤엔진의 성능을 개선 개발을 위한 일차원 성능해석 모델을 개발하였다. 개발된 일차원 엔진 성능모델을 통하여 엔진의 출력, 토크 및 연비등을 검토하였다. 향후 터보챠져를 장착한 엔진개발에 사용이 가능하도록 터보매칭을 할 수 있는 모델을 추가하였으며, 향후 디젤엔진의 실험결과와 비교를 통하여 엔진 모델을 지속적으로 보완할 예정이다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.578-585
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• 2012

Reciprocating engine is widely used for small propeller driven aircraft. because it is the superior efficiency and low price. Currently, reciprocating engine is used for the development of KC-100, LSA, PAV, UAV in domestic. In this study, Naturally aspirated engine and turbocharger engine performance model is developed. The propeller is designed and analyzed at cruise condition of reciprocating engine aircraft using optimum method, the propeller performance model is developed. The Integrated propulsion performance model is developed, through the matching with engine and propeller performance model, for small reciprocating engine aircraft performance analysis.

• Proceedings of the Korean Society of Tribologists and Lubrication Engineers Conference
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• 1994.06a
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• pp.34-39
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• 1994

자동차엔진의 고성능화 및 경량화는 지속적으로 추구되어 왔으며, 향후에도 배기가스 저감 및 연비향상등의 문제 해결을 위한 기술개발이 지속될 것으로 예상된다. 이와 같은 엔진의 지속적인 성능향상에 따라 엔진유의 요구성능도 증가일로에 있는데, 특히 엔진유에 가해지는 열부하의 증대로 고온산화에 의한 열화가 촉진되기 때문에 이와 관련된 엔진유의 고성능화가 절실히 요구되고 있다. 국내에서도 가솔린엔진유의 신규격인 API SH 및 ILSAC GF-1 규격을 만족하는 신제품들이 개발되어 상업화되어 있다. 그러나, 이러한 고성능제품들의 성능이 구규격 제품인 API SG, SF, SE, SD 등의 제품과 어떻게 차이가 있는지에 대한 체계적인 연구가 되어있지 못한 실정이다. 본보에서는 성능등급이 서로 다른 가솔린엔진유에 대한 성능차이를 조사하기 위하여 수행항 실험결과를 보고하고자 한다.