• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년도 제31회 추계학술대회논문집
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• pp.405-406
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• 2008

연소기는 가스터빈 엔진의 주요 구성품 중의 하나이며, 다른 구성품과 달리 거의 시험을 통해서 개발된다. 항우연은 항공용 및 발전용 가스터빈의 연소기 성능시험을 성공적으로 수행해왔다. 연소기 성능시험을 위해서는 대량의 공기를 고온/고압 조건으로 공급해야 하므로, 시험은 대형 시험설비에서 이루어진다.

• 열병합발전
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• 통권74호
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• pp.22-25
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• 2010

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2005년도 제24회 춘계학술대회논문집
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• pp.318-321
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• 2005

한국항공우주연구원에서는 55kW급 마이크로 터빈용 엔진에 사용되는 저공해 예혼합 연소기를 개발하였다. 연소기는 역류-캔 형 연소기로써 항공우주연구원에서 설계, 해석 제작 및 시험을 수행하였으며 최종 시험결과, 연소효율 $99.5\%$, NOx 10ppm 미만, Pattern Factor $30\%$이하. 압력 손실 $4\%$이하의 성능을 확인하였다.

• 한국연소학회지
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• 제13권4호
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• pp.37-46
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• 2008

Performance test of 5MW class gasturbine combustor was carried out at combustor test facility of KARI(Korea Aerospace Research Institute). The combustor is dry low NOx type premixed combustor and fuel is natural gas. The characteristics of combustor were measured including emission, pressure pulsation and exit temperature distribution. Optimum operation point of combustor was found by changing parameters like fuel ratio between pilot and main burner. The test result showed that the combustor performance is sufficient to satisfy the gasturbine system requirement.

• 신재생에너지
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• 제7권2호
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• pp.10-17
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• 2011

Korea is the 11th largest energy consumption country and 96% of its total energy consumption depends on imports from overseas. Therefore it is a very important task to secure renewable energy sources which can reduce both the carbon-dioxide emission and dependency on overseas energy imports. Among the various renewable energy sources, organic wastes are important sources. In Korea, 113 million toe of methane is generated from organic wastes annually, but only 3.7% is effectively used for energy conversion. Thus, it is very important to make better use of organic wastes, especially for power generation. The goals of this project are to develope the fuel supplying system of Bio Gasturbine (GT) for 5MW-class co-generation system. The fuel supplying system mainly consists of $H_2S$ removal system, Bio Gas compression system, Siloxane removal system and moisture separating systems. The fuel requirement of 5MW-class GT is at around 60% of $CH_4$, $H_2S$ (<30 ppm), Siloxane(<10 mg/$nm^3$) and supply pressure (> 25 bar) from biogas compressor. Main mechnical charateristics of Bio Gasturbine system have the specific performance; 1) high speed turbine speed (12,840 rpm) 2) very clean emmission NOx (<50 ppm) 3) high efficiency of energy conversion rate. This paper focuses on the development of design technology for food waste biogas pretreatment system for 5MW-class biogas turbine. The study also has the plan to replace the fuel of gas turbine and other distributed power systems. As the increase of bioenergy, this system help to contribute to spread more New & Renewable Energy and the establishment of Renewable Portfolio Standards (RPS) for Korea.

• 에너지공학
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• 제19권1호
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• pp.8-15
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• 2010

새로운 발전설비의 건설부지 확보의 어려움을 극복하고 친환경적인 에너지시스템으로 분산형 초소형 가스터빈이 주목받고 있다. 분산형 초소형 가스터빈 발전시스템은 다음과 같은 장점을 가지고 있다. 첫째는 친환경성으로서 NOx < 9 ppm, 소음 < 65 dB, 둘째는 다양한 연료를 사용할 수 있으며 천연가스 뿐만 아니라, 디젤, 저발열량 신재생에너지원료, 등유이다. 셋째는 작은 면적대비 높은 출력을 얻을 수 있고 컴팩트한 건설이 가능하다. 1998년부터 미국에서 개발되어 캘리포니아 및 일본등에서 활발히 적용되고 있다. 기존의 대용량 발전시스템이 주로 바닷가 근처에 건설되었다면 본 시스템은 수요자 인근에 설치되어 열과 전기를 동시에 공급하고 있으며 다양한 적용처에 에너지를 공급한다. 최근들어 국내에서는 신재생에너지의 개발, 보급이 아주 중요한 이슈로 떠오르고 있는 가운데, 이러한 소형 분산전원의 적용성이 많이 요구되고 있다. 따라서, 본 논문에서는 분산형 가스터빈의 최적 현장 적용을 위하여 필수적인 계통연계를 통한 병열운전 모델링과 실증시험 및 평가과정을 분석하여 에너지 품질을 정립하고자 한다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2006년도 추계 학술대회논문집
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• pp.18-21
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• 2006

This paper investigates LES of turbulent combustion flow based on 2-scalar flamelet approach, where a G-equation and a conserved scalar equation simulate a propagation of premixed flame and a diffusion combustion process, respectively. The turbulent SGS modeling on these flamelet combustion approach is also researched. These LES models are applied to an industrial flows in a full scale gasturbine combustor with premixed and non-premixed flames. The numerical results predict the characteristics of experiment temperature profiles. Unsteady features of complex flames in combustor are also visualized.

• 연구논문집
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• 통권30호
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• pp.5-13
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• 2000

The computation scheme of simulating gas turbine transient behavior was developed. The basic principles of this scheme and main input data required are described. Calculation results are presented in terms of whole operating regime of the cycle. The influence of main initial parameters such as starting engine power, moment of inertia of the rotor, fuel supplying schedule etc. on performance characteristics of has turbine during transient operation is studied In addition, bleeding air influence on transient behavior was also considered For validation of the developed code, comparison of present calculation with that of measurement data of the experimental data for the range of operating period studied.

• 연구논문집
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• 통권26호
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• pp.43-50
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• 1996

Present paper describes on/off design performance analysis of an 74KW industrial turboshaft gasturbine engine. Procedures to match between the compressor, combustor and turbine have been incorporated into the developed program satisfying compatibility requirement of flow and work and ratational speed. The validity of the performance results from the developed program are yet to be proved through performance experiments of the resultant engine, but comparison of the present results with those from "GASCAN(Thermoflow:America) under similar mass inlet flow, pressure ratio, and speed condition show good agreement despite present results underpredict 6-10% for power and up to 3% in efficiency, respectively.

• 한국유체기계학회 논문집
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• 제15권1호
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• pp.64-69
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• 2012

Currently axial flow compressor is used primarily in a large power generation gas turbine. In this paper,the main factors to be considered when designing a axial flow compressor were compared to those of a small power generation gas turbine(DGT-5). The main design parameters was examined in the aspect ratio, solidity, as well as reaction, diffusion factor, incidence angle, etc. The results in case of a small compressor are showed a regular pattern but there were not found any specific design patterns for a large class compressor.