• 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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• 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 Energy Engineering
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• v.9 no.3
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• pp.157-162
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• 2000

기존의 IGCC의 장점인 고효율 플랜트의 특성을 살리기 위해 고온정제를 적용하는 경우 조건변화에 따른 플랜트 성능의 영향을 관찰하고자 본 연구를 수행하였다. IGCC에 고온정제 공정을 적용하여 구성한 모델은 연구 목적에 알맞은 범위의 건전성을 가진 것으로 나타났으며 기타 조건을 동일하게 설정한 경우 저온 정제 공정(MDEA amine) 적용에 비해 플랜트 효율이 약 2.7% 가량 상승하였다. 한편 동일한 고온정제 공정이라도 적용하는 흡수제를 zinc titanate에서 zinc ferrite로 달리 하는 경우 탈황제의 화학 반응상 특성 및 차이점으로 인해 연료가스의 발열량 변화를 유발하므로 결과적으로 약 0.5%의 플랜트 효율 손실이 발생함을 알 수 있었다. 또한 탈황 온도 350~$650^{\circ}C$ 사이의 온도범위에 대해 민감도 분석을 실행하였으며 민감도 분석 결과 전제 온도의 증가와 플랜트 효율은 정비례하지 않으며 50$0^{\circ}C$ 이상의 정제 온도를 적용한 경우는 거의 비슷한 효율을 나타내었다. 이와 같은 결과는 정제 온도를 증가시킴으로 인해 가스터빈에 공급되는 연료가스의 온도는 높아지지만 적용한 가스터빈의 출력 및 연소 온도가 제한되어 있어 고온정제를 적용함으로써 얻어지는 이득을 가스터빈에서 충분히 보상하지 못하고 한편으로 고온정제를 채택함으로써 저온정제 적용시 보다 syngas cooler에서 회수할 수 있는 헌열이 줄어듦으로 인한 증기 터빈 출력의 감소가 커지기 때문으로 분석되었다.

• 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.

• 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.

• 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.

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.4
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• pp.63-77
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• 2008

This paper described the general concept of combustion instability and its mechanism in gas turbine engines. The approaching method to study this phenomenon was introduced including the up-to-date research activity in tile world. Combustion instability is one of critical problems, still now, affecting engine performance, durability and operation. In addition it is known that this problem is caused by coupling between fuel or air flow fluctuation and heat release rate in gas turbine engines, which is related with NOx reduction strategies. Therefore, in order to understand the current status of combustion instability we reviewed the combustion instability phenomenon in gas turbine engines.

• Journal of Energy Engineering
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• v.29 no.1
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• pp.13-24
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• 2020

Many countries are actively engaging in the reduction of greenhouse gas emissions, and as part of this effort, gradually reducing the portion of coal power generation and instead increasing the portion of power generations from renewable energy sources and natural gas. Korea is taking a similar policy to expand LNG power generation for the next decade. There is a concern, though, about the policy not being aligned with the domestic industry development, since only a few products are being made in Korea along the LNG power generation industry value chain. Therefore in this paper, we first looked at the current status of the gas turbine and high temperature parts industry used for LNG power generation in Korea, and then looked into the industrial issues and challenges through the analysis of supply chains of the domestic gas turbine industry. Finally, we tried to propose strategies to revitalize and localize the domestic gas turbine and high temperature parts industry. The proposed strategies can be summarized as 1) creation of domestic gas turbine manufacturing ecosystem via construction of gas turbine alliance, 2) strategic R&D support for localization of gas turbine and high temperature parts, and 3) provision of domestic testbeds for technology evaluation and commercialization.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1999.10a
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• pp.26-26
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• 1999

소·중형 산업용 항공기나 초등 훈련기용으로 많이 이용되고 있는 터보프롭 엔진의 성능진단을 위해 선형 GPA 기법을 적용하였다. 대기조건은 지상정지조건으로 하였으며 계측변수의 선정에 따른 오차율을 알아보기 위해 다양한 손상을 가정하였다. 가스터빈 엔진에서 가장 쉽게 발견될 수 있는 성능저하 원인인 압축기 오염과 터빈 부식이 발생하였을 경우를 가정하였다. 다중 손상일 경우 선형 GPA 기법의 신뢰성을 알아보기 위해 압축기에만 오염이 발생하였을 경우, 압축기와 압축기 터빈에 각각 오염과 부식이 발생하였을 경우, 압축기 터빈과 동력터빈에 동시에 부식이 발생하였을 경우, 압축기, 압축기 터빈, 동력터빈이 모두 오염과 부식이 발생하였을 경우를 가정하였다.

• Journal of the KSME
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• v.54 no.8
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• pp.47-51
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• 2014

이 글에서는 가스터빈 부품/소재 분야의 현황과 국산화 방안에 대해 소개하고자 한다.