• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.31-35
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• 2008

This test cell is developed to provide the fundamentals of operational mechanism and structural configuration, and further to verify thermodynamic calculation with this test data to the institutes or laboratories research and study gas turbine engine for academic purpose. The test cell is installed to monitor and collect real-time data as to temperature, pressure, thrust, fuel flow, and air flow etc. using by NI DAQ(Data acquisition)device and LabVIEW program based on 30lbf-micro turbojet engine.

• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.5
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• pp.22-30
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• 2015

A gas generator which generates turbine driving gas by burning a part of propellants is used in an open cycle liquid rocket engine and as a main component of an open cycle liquid rocket engine autonomous hot firing tests are required to investigate the combustion performance and characteristics of the gas generator. However, since the combustion gas generated by a gas generator is choked at the turbine nozzle in the turbine manifold, it is necessary to consider the internal volume of turbine manifold as well as that of the gas generator for correct investigation of the combustion performance, characteristics, and acoustic characteristics of the gas generator. Therefore, in the paper hot firing test results of a gas generator with a turbine manifold simulator are described and characteristic prediction using the autonomous test of a gas generator is explained.

• Plant Journal
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• v.13 no.1
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• pp.37-43
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• 2017

This study analyzed the change of gas turbine performance with air temperature decrease by the evaporation cooling system in summer season. Gas turbine performance was tested on the condition that ambient temperature is $29{\pm}1^{\circ}C$. As a result, Air temperature at the compressor inlet was decreased by $4.12^{\circ}C$ after the installation of evaporation cooling system. Decreased air temperature followed by increased air density affected gas turbine performance, Which increased compressor pressure ratio by 0.27, improved compressor efficiency of 0.29 %p, improved gas turbine enthalpy drop efficiency of 0.31 %p, improved the gas turbine efficiency by 0.44 %p, improved electric power output by 4,489 kW. On the other side, the influence of the humidity increase and flow resistance increase was negligible.

• 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.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.36 no.8
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• pp.791-796
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• 2012

Small gas turbine engines are used in aircraft as an auxiliary power unit (APU) to supply compressed air to start the main engine and for emergency electricity. When an aircraft is operating in an environment in which sand and dust is present in the ambient air, the engines as well as the APU ingest the sand and dust. This causes erosion of the engine and a degradation in its performance. The present study investigated the effect of sand and dust ingestion on small gas turbine engines. The concentration of sand and dust was $4.4{\times}10^{-5}kg$ per unit kg of air, which follows the specification in MIL-E-8593. The test was conducted for 10 h, and the engine performance before and after the test was compared. In addition, a tear-down inspection was conducted to examine the erosion patterns of sub-components such as the impeller and turbine wheel.

• JOURNAL OF ELECTRICAL WORLD
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• s.313
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• pp.75-80
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• 2003

에너지와 환경을 조화시킨 자원순환형 사회의 실현을 위해 하수처리장에서도 하수열이나 소화가스 등의 미이용(未利用)네어지의 유효활용이 기대되고 있다. 소화가스는 하수처리장에서 발생하는 에너지 중에서는 큰 비중을 차지하고 있으나 소화조의 가온을 위해 사용되고 있는 정도로 반드시 유효하게 활용되고 있다고는 말할 수 없다. 또 가스엔진의 코제너레이션에 의해 유효하게 할용되고 있는 처리장도 있으나 메인터넌스 비용 등의 문제로 보급되고 있지 않은 것이 실제의 상황이다. 한편, 마이크로가스터빈은 그 구조의 심풀성 때문에 가스엔진과 비교하여 메인터너스 비용의 저감이 기대되고 있어, 소화가스를 연료로 하는 코제너레이션 시스템으로서 앞으로의 보급이 기대되는 발전시스템이다. 그래서 소화가스의 마이크로가스터빈용 연료로서의 적용을 위한 검증과 운영상의 과제를 밝힐 것을 목적으로 북견시 정화센터의 처리장 내에 설치하여 실증시험을 하고 있다. 지금까지 약 4,000시간의 운전실적에서 소화가스에 기인하는 본질적인 문제도 없고 시스템이 안정되게 동작하는 것을 확인하였다. 또한 실증시험설비에는 마이크로가스터빈의 운전상태를 24시간 리모트 감시하는 리모트감시장치를 설치하고 있는데, 운전데이터의 파악과 이상 발생시의 고장진단/기술검토에 유효하게 사용되었다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1997.11a
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• pp.23-23
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• 1997

다목적으로 활용할 수 있는 분리축 방식의 터보축 엔진 개발을 위한 정상상태 해석 프로그램의 개발과 함께 동일 형식의 가스터빈엔진 시험장치를 이용한 실험을 통해 프로그램의 해석결과와 비교, 그 타당성을 입증하였다. 실험에 이용된 시험장치는 1단 원심형 압축기, Can형 연소기, 1단 Radial형 압축기 터빈 및 동력터빈으로 구성되어 있으며 출력은 3상 교류발전기를 통해 획득된다. 해석에 사용된 주요 구성품의 성능곡선은 시험장치 제작자로부터 획득된 자료를 이용하였으며, 경우에 따라 시험장치를 이용한 실험을 통하여 보정하였다. 시험장치를 이용한 실험결과를 프로그램 해석결과와 비교한 결과, 시험장치의 운용제한에 의해 실제 자동영역이 제한되기는 했으나, 압력비, 출력 등 주요 변수들에서 10% 미만의 오차를 보였다.

• Proceedings of the Korea Society for Energy Engineering kosee Conference
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• 1996.10b
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• pp.98-103
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• 1996

석탄가스화복합발전소내 공기분리장치와 연계된 가스터빈 공기압축기의 성능병화를 예측할 수 있는 해석방법을 제안하였다. 공기분리장치와 연계된 가스터빈용 공기압축기의 성능변화는 유선곡률방법과 압력손실모델을 결합한 해석방법을 사용하였으며, 예측결과들을 실제 압축기성능 시험 결과와 비교하여 예측정확도를 검증하였다. 제안된 압축기성능 해석방법을 근간으로, 압축기와 공기분리장치의 연계조건인 열교환기의 핀치포인트 온도차, 추출공기량 및 추출 공기압력이 압축기 성능변화에 미치는 영향을 정량적으로 예측하였다. 공기추출량이 늘어나거나 핀치포인트 온도차가 커질수록, 압축기의 압축비 및 소요동력은 증가하나, 압축기 효율은 공기추출량의 증가에 따라 고압공기추출시에는 저하되고, 저압공기추출시에는 향상되었다. 더 나아가, 압축기의 일반화된 성능특성곡선의 제시를 통해, 압축기 효율을 극대화 할 수 있는 압축기/공기분리장치 간 연계조건의 최적화를 시도하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.345-349
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• 2009

This test cell is developed to the institutes or laboratories research and study gas turbine engine for academic purpose with this test data to provide the fundamentals of operational mechanism and structural configuration, and further to verify thermodynamic calculation The test cell is installed to monitor and compare real-time data with reference engine model performance simulation data. using by NI DAQ(Data acquisition)device and LabVIEW program based on 30lbf-micro turbojet engine.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.495-498
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• 2010

This test cell is developed to the institutes or laboratories research and study gas turbine engine for academic purpose with this test data to provide the fundamentals of operational mechanism and structural configuration, and further to verify thermodynamic calculation The test cell is installed to monitor and compare real-time data with reference engine model performance simulation data. using by NI DAQ(Data acquisition)device and LabVIEW program based on 80 lbf-micro turbojet engine.