• Aerospace Engineering and Technology
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• v.10 no.1
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• pp.63-69
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• 2011

In this study, we developed a dispersion analysis program of the gas-generator cycle liquid propellant rocket engine by expanding the mode analysis software(GEMAT). The performance dispersions of an engine that are arisen from the internal dispersion factors of engine's sub-components were formulated and solved to find the effects of each dispersion factor. We were also able to present the calculation method to find the required pressure margin for the compensation of those dispersion to satisfy the required performances of engine. Using this method, we could propose a novel procedure of compensating during the ground firing test which would induce the performance improvement by lessening the pumps discharge pressures or augmenting the combustion chamber pressure.

• Journal of KIISE:Databases
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• v.29 no.2
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• pp.148-157
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• 2002

Caching in meta-search engines can improve the response time of users' request. We describe the cache scheme in our meta-search engine in terms of its architecture and operational flow. In particular, we propose a popularity-driven cache algorithm that utilizes popularities of queries to determine cached data to be purged. The popularity is a value that represents the normalized occurrence frequency of user queries. This paper presents how to collect popular queries and how to calculate query popularities. An empirical performance evaluation of the popularity-driven caching with the traditional schemes (i.e., least recently used (LRU) and least frequently used (LFU)) has been carried out on a collection of real data. In almost all cases, the proposed replacement policy outperforms LRU and LFU.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.7
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• pp.517-524
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• 2019

A system design has been performed for a vacuum thrust 88 ton staged combustion cycle rocket engine. Previous research has been used to estimate the performance of the engine components. And the algorithm has been proposed to evaluate the converged engine system performance. The present methodolgy has been verified by comparing the published data for RD-180. The present work adopts the most of the previous KSLV-II engine heritage for both performance improvement and cost competitiveness. The combustion pressure has been decided as 12MPa considering manufacturing difficulty, cost and performance improvement, and as a result the vacuum specific impulse has increased by 23.4s.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.3
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• pp.58-66
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• 2019

In this study, the start-up characteristics of a staged combustion engine were analyzed numerically based on relational equation modeling of the entire engine components. The start-up characteristics were extensively analyzed considering the transient period of the total engine system from the start-up sequence till the steady-state of the engine. The performance characteristics of the engine components such as RPM of engine power-pack, chamber pressure and O/F ratio of pre-burner, and mass flow of propellants in the start-up period were investigated. Furthermore, the calculated engine data were compared satisfactorily with the experimental data. Through the comparison of data, successful validation of present engine start-up analysis has been obtained.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.339-342
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• 2010

Doosan Heavy Industries & Construction Co., Ltd. constructed a gas turbine engine test cell to verify operating characteristics and design parameters of 5MW class gas turbine engine for power generation under developing. Engine test cell was designed to satisfy critical requirements to scrutinize all performance parameters of the engine with safe and reliability in accordance with design specification. As the test cell developed can effectively reproduce engine operation conditions covering from start-up to maximum power condition, it can be utilized to make a continuing design improvement of the engine based on practical test data at full stretch. Moreover, it is expected to be serviceable to develop derivative engines and be utilized to put them into serial production and contribute to a competitiveness reenforcement as a gas turbine engine manufacturer.

• Journal of Biosystems Engineering
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• v.25 no.6
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• pp.471-480
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• 2000

대체연료로서 바이오 연료의 디젤엔진에의 적합성을 파악하기 위하여 경유, 가온 미강유, 초음파 적용 가온 미강유, 미강유 메틸 에스테르, 폐식용유, 초음파 적용 폐식용유, 폐식용유 메틸 에스테를 14kW 예연소실식 디젤 엔진의 연료로 사용하여 그 성능과 배기배출물을 측정하였다. 시험에 사용한 바이오 연료들에 의해 엔진 분사 펌프의 조정이나 다른 부품의 개조를 하지 않고도 단기간 전부하 상태로 1,600~2,800 rpm 의 범위에서 엔진은 정상적으로작동하였다. 바이오 연료를 사용하였을 경우 전반적으로 엔진성능과 배기 배출물 특성에 있어서 경유를 사용하였을 경우와 비견할만 하였으며 특히 매우 낮은 농도의 $SO_2$와 매연을 배출하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.6
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• pp.96-103
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• 2004

Sought a set of component performance lines from experiment data or some data supplied in the engine manufacturer to improve the traditional scaling method and suggested a map scaling method that construct component performance lines newly using polynomial equations of MATLAB program. In this study, applied technique that is proposed newly to PT6A-62 that verified technique that is proposed newly using experiment data of small. size turboshaft engine, and is actuality aircraft engine. In identification of the component maps of the turboprop engine, the simulated performance using the proposed scaling method was compared with the real engine performance data and the performance using the traditional scaling method.

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.2
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• pp.15-23
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• 2008

A numerical method based on the prediction of total pressure loss of major components of the engine has been developed for prediction of the windmilling start performance of micro-turbojet engine. The start performance in on/off design region has been analysed by applying this method to predict windmilling start-able regions of the centrifugal-type engine. The results of this analysis have been validated by comparing with the test data. The effect of each design parameters on windmilling start performance has been analysed for the enlargement of start-able regions.

• Aerospace Engineering and Technology
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• v.3 no.1
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• pp.65-78
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• 2004

This research was conducted for an acquisition of the ramjet engine test facility design technique which are concerned about freejet type test facility. In this research, we concentrated on the design technique and the construction technique of the vitiation air heater(VAH), test section, diffuser and ejector. Based on the operating modes of the basic test facility, ten operating modes in coordinates "Altitude-Mach number" was regenerated from Mach 2, Altitude 0km to Mach 5, Altitude 15km. In this operating modes, we calculated a design parameter of the supersonic nozzle, VAH, diffuser and ejector and acquired a technique for the ramjet test facility operating and repairing.

• Proceedings of the Korean Information Science Society Conference
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• 2011.06a
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• pp.135-138
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• 2011

자바스크립트 언어는 클라이언트 사이드 웹 언어로서 지금까지 널리 사용되어 왔다. 그러나 최근에서야 내장형 시스템에서의 웹 브라우징이 보급되면서 그 성능이 이슈가 되고 있는데, 이를 위해 여러 오픈 소스 진영에서 적시 컴파일러를 탑재한 고성능의 자바스크립트 엔진이개발되고 있다. 그 중 V8 자바스크립트 엔진이 현재는 성능이 가장 좋은 것으로 알려져 있으나, 자바스크립트 언어의 극도로 동적인 특성으로 인하여 아직 성능의 최적화 여지가 많이 남아 있다. 본 논문에서는 V8 자바스크립트 엔진의 적시 컴파일러에서 함수 호출 코드 생성에 관한 최적화를 적용 하였다. 두 개의 명령어와 하나의 상수 풀을 사용하던 기존의 함수 호출 코드에서 하나의 명령어만으로 함수 호출을 하도록 구현함으로써 성능이 1.5% 개선되었고, 네이티브 캐시 사용량이 7.7% 감소하였다.