• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.2
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• pp.88-97
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• 2021

The controller of the gas turbine engine is a component that needs to be developed for the development of the gas turbine engine because it is impossible to get the technology transferred from the engine manufacturer due to the import and export regulation. As a part of the engine control logic research, the Korea Aerospace Research Institute conducted a failure diagnostic research using a small gas turbine engine. Before simulating the engine fault, the ground test was performed to analyze normal behavior and performance of engine. Afterwards, the control logic analysis test equipment was established to simulate various engine fault. It is intended to provide background knowledge to engine control logic research for various engine failure conditions.

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.6
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• pp.48-55
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• 2008

We have simulated the performance of a simple engine model with a gas turbine engine simulation program based on CFD. 2-dimensional Navier-Stokes code for the viscous flow was applied to simulate a compressor and a turbine, and the chemical equilibrium code with the lumped method was applied to simulate the combustor. Unsteady-flow phenomenon between rotor and stator of the compressor and the turbine was analyzed by steady mixing-plane method. In this way, the influence of the turbine blade pitch on the engine was investigated. It was shown that the compressor is operated at more higher pressure conditions as narrower the pitch distance of the turbine.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.11a
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• pp.18-18
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• 2000

산업용 가스터빈에서 대기로 방출되는 배기열을 효과적으로 이용하기 위한 역 브레이튼 사이클 가스터빈(Reverse Brayton Cycle Gas Turbine) 엔진의 출력과 비연료 소비율 및 열효율을 기본 브레이튼 사이클 엔진, 재열사이클에 역 브레이튼 사이클을 추가한 엔진, 역 브레이튼 사이클에 중간냉각기를 추가한 엔진의 출력, 비연료 소비율 및 열효율을 비교하였다.(중략)

• Journal of the Korean Society of Propulsion Engineers
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• v.3 no.2
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• pp.48-55
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• 1999

Performance analysis of a 50KW turbo-generator gas turbine engine with a recuperator was studied. Recuperated cycle has been employed to meet maximum fuel economy and ultra low emissions especially for military and vehicular engines. From thermodynamic stand point, it is known that recuperative cycle can contribute most to enhance thermal cycle efficiency for the Pressure ratios under 10 and of comparatively low turbine inlet temperature. Efficiency of a simple cycle with a recuperator increases relatively about 30% than without one at effectiveness of 0.5. Pressure losses in the heat exchanger less than 5.2% is considered in the design process. A tubular type heat exchanger is selected for this particular engine because it can provide simple construction as well as structural sturdiness and excellent leak tightness.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.04a
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• pp.28-28
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• 2002

가스터빈 엔진을 운용하는 데 있어서 가/감속율을 크게 하면 엔진성능 천이 시간은 짧으나 압축기에서의 서지나 터빈 입구온도의 급격한 상승이 발생할 수 있으며 가/감속율을 작게 하면 엔진은 안정적이나 천이시간이 길어지게 되어 결과적으로 엔진의 동적 응답성이 나빠지게 된다. 또한 압축기에서 발생할 수 있는 서지를 방지하기 위하여 압축기 서지 마진이 l0%∼20%인 서지 한계선(조정선)을 설정하여 엔진이 서지 한계선을 넘지 않도록 제어한다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.04a
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• pp.25-26
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• 2002

가스터빈 엔진의 성능모사는 개발단계에서의 개발위험도 감소나 개발비용 절감의 목적뿐만 아니라 운용단계에서 최적의 정비를 위한 엔진의 상태 진단을 위해서도 그 필요성이 매우 크다. 가스터빈 엔진의 성능모사를 위해서는 "각 구성품의 성능은 구성품 성능선도를 따라야 한다"는 제약조건을 만족해야 하며 이를 위해서는 구성품의 특성을 나타내는 성능선도가 매우 중요하다. 구성품 성능선도는 다양한 조건에서의 성능시험을 통해 얻는 것이 당연하나 이는 엔진 개발사에서나 가능하며 대부분 공개를 기피한다. 따라서 일반 구매자나 가스터빈 엔진의 성능을 연구하는 사람들은 일부 공개된 성능도를 축척하여 이용하고 있다.여 이용하고 있다.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.6
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• pp.64-71
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• 2018

It is essential to understand the characteristics of gas turbine components in order to carry out an off-design analysis of a gas turbine engine. In this study, a micro gas turbine engine test system was constructed to understand the performance characteristics of gas turbines. The temperature and pressure in the flow path of the micro gas turbine was collected by measuring the engine spool speed, and a compressor map was constructed by using the experimental data. The exhaust gas was collected at the turbine outlet and the combustion efficiency was calculated. An off-design performance analysis at ground static was performed using GasTurb software by applying the compressor map and combustion efficiency obtained from the experimental data. Futhermore, we compared and evaluated the analysis results with engine operating data.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.542-545
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• 2009

In this study, the effect of turbine geometry on the overall performance of a gas turbine was investigated by computational fluid dynamics. Overall engine performance was predicted through a full engine simulation program which can predict the interactions of the compressor, the combustor and the turbine. The compressor and the turbine analysis code solves 2D and 3D Navier-Stokes equations respectively. The chemical equilibrium code was applied to simulate the combustor. The computations were performed for two different shapes of turbine nozzle. The nozzle shapes adopted a baseline blade and a blade with fillet.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.354-358
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• 2009

Micro gas turbine engine is well known as a power plant of unmanned aerial vehicle and a small scale emergency generation system and also, it is significant as initial research of large gas turbine and educational purpose of gas turbine. Many sort of Micro gas turbine test set for education is produced by several manufacturers, but all of the engine control system of them is separated with data acquisition system; moreover, the engine control algorithms are inaccessible and related variables could not be collected. In this investigation, the Integrated Modifiable Test Rig which has modifiable engine start-up, drive and situational control logics is developed by LabVIEW with I/O devices and it provides wide experimental applicability to studies of dynamic characteristics of fuel system and combustion instability.

• Journal of the KSME
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• v.34 no.12
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• pp.918-928
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• 1994

금세기 들어 가스터빈 엔진이 실용화되기 시작한 후 1\ulcorner2차 세계대전을 거치면서 향공기 추진 기관으로서의 기술적 진화가 활발히 이루어져 오고 있다. 최근 항공기용 가스터빈 엔진은 100,000 LB급의 초대형 추진기관으로 발전되기에 이르렀고 사용연로의 효율성 및 안정성이 크게 향상 됨으로써 기술적으로 더 이상 개선의 여지가 거의 없을 정도의 수준에 도달했다고도 볼 수 있다. 이러한 추세와 병행해서 최근 분산형 발전설비의 개념이 전 세계적으로 활발하게 응용되고 천 연가스를 이용한 열병합 발전단지의 건설추세에 따라 발전설비용으로서의 가스터빈 응용이 증 가되는 추세에 있다. 또한 일본을 중심으로 가스터빈의 장점을 이용한 비상용 발전설비로의 사 용이 보편화되고 있다. 이 글에서는 발전설비용 산업용 가스터빈의 시장동향을 분석하고, 이에 관련된 소요기술 발전추세를 소개하며, 마지막으로 국내의 산업용 가스터빈 개발현황을 기술하 고자 한다.