• Proceedings of the KIEE Conference
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• 2002.07d
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• pp.2082-2085
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• 2002

This paper describes the development of a gas turbine engine simulator in detail. The simulator presented in this paper has a mathematical engine model based on a target gas turbine engine performance data and is developed for generating a gas turbine engine sensor signals between the hardwares and softwares of a gas turbine engine control system using Data Acquisition systems(DAS) and 1553B communication, a aeronautic standard communication specification. In addition, this paper proves the excellent performance of this simulator by showing the results of a gas turbine engine field test and simulation.

• 유체기계공업학회:학술대회논문집
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• 2001.11a
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• pp.361-366
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• 2001

A mim turbo-shaft engine of 50HP for UAV, which can be easily modified to turbo-prop and turbo-jet engine by sharing the core engine and has many applications to civilian demands and munitions, will be developed This kind of micro gas turbine engine has been developed mostly by the corporations which have special technology but are small in its scale. Especially, the gas turbine engine can be easily applied to other fields and developed by domestic technology, so that the sharing of technology is planed to realize through the cooperations with academies and research institutes. In this paper, the gas turbine engine, which has the compressor ratio of 3.8, the turbine inlet temperature of l180K and the engine speed higher than 100,000 rpm, is composed of centrifugal compressor, combustor, gas generator turbine, free power turbine and gear box. The competitiveness of the gas turbine engine can be obtained from minimizing its cost by the utilization of domestic infrastructure for the performance test and the decisive outsourcing.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.11 no.1
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• pp.75-82
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• 2007

In advanced countries, a gas turbine engine is developed to use in aircraft, vessels, and target weapons. Our nation also passed the level of producing engine components and now, we are developing small-sized gas turbine engine. The most important point of the gas turbine engine, the engine control technique, is evaded by the advanced nations. This document contains the research about the development of the gas turbine engine simulator. The simulator presented in this document has a mathematical engine model based on a capacity data of the gas turbine engine to advance the engine simulator. Through this process, it eases the development of the gas turbine engine control algorithm and helps to check the engine controller function. In this simulator, the engine sensor signal conversion board is designed, so the engine model shows like a real sensor signal during the simulation. Also, this paper contrasts the actual engine test with the simulation results to verify the performance.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.587-590
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• 2017

Performance test was conducted by micro gas turbine engine. A small test rig was established for the performance measurement of the micro gas turbine engine. The performance was conducted by the Olympus HP engine. Engine inlet mass flow rate, static thrust, fuel consumption rate, air and gas temperature at the inlet of major components were measured. In the test results, we could well understand about the micro gas turbine engine performance characteristics.

• The KSFM Journal of Fluid Machinery
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• v.14 no.4
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• pp.52-56
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• 2011

Small-sized gas turbine engine could be applied to various fields such as propulsion, power generation, machine driving, etc., and Doosan has been developing 5MW class gas turbine engine for power generation since 2005. To verify its design performance and operating characteristics, a gas turbine engine test facility was constructed, and control system was also established to satisfy rapid and reliable control performance. In this paper, the hardware specification and structure of control system for gas turbine engine are introduced, and test result for starting characteristics analysis and loading is also presented.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.10a
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• pp.219-222
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• 2003

Turbo generator system need starter for gas turbine engine. Turbo generator has high rate gearbox for reduce rotating speed. Because a conventional generator could not operate same speed of gas turbine engine. But Recently turbo generator system is directly connected a gas turbine engine with a super high-speed generator. In this paper, starter driver are implemented direct coupled turbo generator system, Which is directly connected 100kW, 60,000rpm gas turbine engine and 25kW 60,000rpm super high speed generator.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.829-832
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• 2010

For gas turbine engine starting, external power should be supplied with engine to accelerate to suitable rotational speed for air and fuel ignition conditions. Electric starting system for small gas turbine engine has simple system and light weight, so it is generally used for small aircraft. For system analysis of gas turbine engine electric starting system, Characteristics of battery, start motor, engine drag torque should be analyzed and theirs temperature effects should be considered. In this paper, preliminary design procedure of small gas turbine engine electric starting system and major design parameters were described.

• Proceedings of the Korean Society of Marine Engineers Conference
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• 2006.06a
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• pp.27-28
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• 2006

최근 LNG 연료 시장의 호황에 힘입어 LNG선들이 점차 대형화 추세에 있고, LNG선의 추진 기관 또한 경제성, 환경 영향 등의 주어진 요구 환경에 따라 다양화 되고 있다. 기존의 Steam Turbine Propulsion 외에 Conventional 2-stroke Diesel Engine 및 Dual-fuel 4-stroke Diesel Engine of LNG선의 주 기관으로서 이미 상용화 되었고, 기술적/경제적인 이유로 일반 상선의 주기관으로서는 논외에 있었던 Gas Turbine 또한 일부 Oil Major와 Gas Turbine Maker에 의해 그 적용 가능성이 논의되고 있다. 이에 따라 LNG 선에 Gas Turbine 적용 타당성, 고려 사항 및 적용에 따른 이점과 단점 등을 고찰하였다.

• 유체기계공업학회:학술대회논문집
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• 1998.12a
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• pp.191-197
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• 1998

The recent results of the engine development performed in this you on Turbogreen 1200, the first industrial gas turbine engine developed in Korea, are presented. In order to improve the engine performance and structural stability from the first prototype engine, several variants of the engine and major components such as combustor and rotor assembly have been developed and tested. This paper shows these results especially focused on the engine test and performance analysis, in which test system, instrumentation and data processing are discussed as well. The engine performance and its trend give relatively good coincidence with the design ones. At design power of 1.2MW, the thermal efficiency of the engine is estimated over $25\%$ which is below the design target of $27.2\%$. This gap of efficiency is caused mainly by large tip clearance between turbine blades and casing. Considering high design efficiency superior to those of other competitive engines in this power class, Turbogreen 1200 would have a strong competition in its performance if the design efficiency is achieved by further developments such as tip clearance control, which are very possible and natural in final mass production of the developed gas turbine engine.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.03a
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• pp.369-375
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• 2004

Gas turbine engine simulation in terms of transient, steady state performance and operational characteristics is complex work at the various engineering functions of aero engine manufacturers. Especially, efficiency of control system design and development in terms of cost, development period and technical relevance implies controlling diverse simulation and identification activities. The previous engine simulation has been accomplished within a limited analysis area such as fan, compressor, combustor, turbine, controller, etc. and this has resulted in improper engine performance and control characteristics because of limited interaction between analysis areas. In this paper, we propose a new simulation methodology for gas turbine engine performance analysis as well as its digital controller to solve difficulties as mentioned above. The novel method has particularities of (ⅰ) resulting in the integrated control simulation using almost every component/module analysis, (ⅱ) providing automated math model generation process of engine itself, various engine subsystems and control compensators/regulators, (ⅲ) presenting total sophisticated output results and easy understandable graphic display for a final user. We call this simulation system GT3GS (Gas Turbine 3D Graphic Simulator). GT3GS was built on both software and hardware technology for total simulation capable of high calculation flexibility as well as interface with real engine controller. All components in the simulator were implemented using COTS (Commercial Off the Shelf) modules. In addition, described here includes GT3GS main features and future works for better gas turbine engine simulation.