• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.62-67
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• 2004

This paper investigates the off-design performance of methane-fueled air turbo ramjet(ATR) engine in subsonic flight speed range. The ATR engine was modeled and simulated numerically. Each component was modeled to enable their off-design calculation. Compressor operating point was determined by flow matching with nozzle, and turbine by work matching. The ATR engine exhibited quite different off-design behavior compared to the conventional gas turbine engine.

• Aerospace Engineering and Technology
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• v.4 no.2
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• pp.27-35
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• 2005

In this study, a performance analysis code was developed for the off-design performance analysis of air turbo ramjet(ATR) engine, and the analyses were performed for the pre-designed ATR engine at several operating points in the envelope. Variable intake and thrust nozzle were assumed to cover the wide envelope. Mathematical models for each components were developed to calculate their off-design performance. Simple design formulas were introduced for some components to explore the performance variation versus the design parameters. As a result, the pre-defined engine couldn't cover the entire mission profile. And it was also found that the effect of the pre-cooler was not very great, especially in the region of low Mach number.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.219-224
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• 2012

In this work, a steady-state performance modeling and off-design performance analysis of the 2-spool separate jet turbofan engine named BR715-56 which is a power plant for the narrow body commercial aircraft is carried out for engine performance behaviors investigation and condition monitoring using a commercial code MATLAB/SIMULINK. Firstly, the engine component maps of fan, high pressure compressor, high pressure turbine and low pressure turbine are generated from similar component maps using the scaling method, and then the off-design performance simulation model is constructed by the mass flow matching and the work matching between components. The model is developed using SIMULINK, which has advantages of easy steady-stare and dynamic modelling and user friendly interface function. It is found that the off-design performance analysis results using the proposed model are well agreed with the performance analysis results by GASTURB at various operating conditions.

• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.1
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• pp.12-18
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• 2021

In this study, the performance modeling of MT30 gas turbine engine is performed. The design point is determined, and the component performance maps to which the scaling technique is applied are generated using standard maps provided by the commercial program. Off-design point performance analysis is performed with the generated performance model, and this is compared with the performance deck data of the engine. It is confirmed that the data of the performance maps generated by the one-point scaling method had some errors from the performance deck data, and it is determined that correction is necessary to increase the accuracy of the performance model. Therefore, the off-design point analysis is performed by creating the correction performance model in a manner that obtains the scaling factors for each operating point(off-design point) according to the high pressure spool speed.

• Proceedings of the Korea Society for Energy Engineering kosee Conference
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• 1997.10a
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• pp.99-104
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• 1997

기존의 천연가스 가스터빈 시스템을 IGCC 발전소에 적용함에 있어 야기되는 탈설계점효과를 고려할 수 있는 압축기 성능곡선의 예측방법을 제안하였다. 압축기 성능해석방법으로는 익렬요소방법에 전압력손실, 유동편차각 모델들을 결합하여 사용하였으며, 본 방법에 의한 예측결과와 실제 압축기 성능실험결과를 비교하였다. 예측결과가 다양한 압축기 운전조건에 대해 시험결과와 비교적 잘 일치하였으며, 이를 통해 본 예측방법이 IGCC 공정설계 및 성능평가시 가스터빈 탈설계점 효과를 분석할 수 있는 기본 모듈로 사용될 수 있을 것이다.

• Proceedings of the Korean Nuclear Society Conference
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• 1996.05b
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• pp.154-159
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• 1996

원자력발전소에는 원자로냉각재펌프와 같이 원심펌프가 많이 쓰이고 대부분의 펌프가 탈설계점에서 운전되고 있다. 이러한 펌프의 성능을 예측하거나 개선하고자 할 때 성능해석코드는 매우 유용하다. 본 연구에서는 기존성능해석프로그램의 문제점인 탈설계점에서의 성능예측 정확도가 많이 떨어지는 점을 개선하고 기존해석방법론을 검토하여 유량변화에 관계없이 일정한 값을 갖는 Slip factor의 문제점을 보안, 유량에 따라 적절히 보상하는 Slip factor를 고려하였고 각종 손실구조 및 적절한 손실모델을 도출하여 새로운 프로그램을 개발하였다. 또한 이 프로그램을 이용한 계산결과를 실험자료 및 기존의 상용코드 해석결과와 비교한 결과, 극저유량운전범위를 제외하고는 전유량 범위에 걸쳐 매우 양호한 결과를 얻었다.

• 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.

• Journal of Aerospace System Engineering
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• v.13 no.1
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• pp.38-46
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• 2019

There is a growing interest in engine diagnostic technology for gas turbine engines. An engine simulation program, precisely simulating the engine performance, is required in order to apply it to the engine diagnosis technology for engine health monitoring. In particular, the simulation program can predict not only design point performance but also off-design point and partial load performance in accurate. So the engine simulation program for the 2-spool separate flow type turbofan engine was developed and the JT9D-7R4G engine of PW(Pratt & Whitney) was analyzed. The steady-sate performance analysis is conducted at both design and off-design points in flight path and the differences between analysis results of takeoff and cruise conditions are compared. The effect of Reynold's correction method was analyzed as a scaling method of the engine component performance. The simulation results was compared with NPSS.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.201-204
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• 2004

In this study, the GSP and in-house numerical codes have been used for analyses of the on-design, static off-design and dynamic off-design performances. Through the various missions including altitude, velocity, and power variations static engine performance have been investigated. The dynamic engine performances based on these complicated variations have been also analysed. Especially, the power, engine rpm and heat overload characteristics of a turbine have been estimated with the response time through the control of a throttle setting rather than a power setting. It could be applied to the FADEC system as an engine control device.

• Journal of Energy Engineering
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• v.8 no.1
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• pp.159-165
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• 1999

복합화력 발전플랜트의 운전에서 특히 하절기의 첨두부하시에 외기온도의 상승으로 인한 가스터빈의 출력 감소를 해결하기 위한 방법으로 LNG 연료가 보유하고 있는 냉열을 이용하여 압축기로 유입되는 공기 온도를 감소시키는 냉각시스템의 개념을 개발하고자 복합화력 발전플랜트에 대한 설계점 및 외기온도 변화에 대한 탈설계점 모델링 연구를 수행하였다. 대상 프랜트는 940 MW 서인천 복합 발전플랜트 모듈의 단위 블록을 선택하였으며 발전플랜트 전용 해석코드인 GateCycle을 이용하여 가스터빈과 증기사이클의 주요 기기 들에 대한 모델을 개발하였다. 개발된 모델의 결과를 대상플랜트의 시운전결과와 비교하여 모델의 적정성을 검증하였다. 출력, 효율, 온도 및 유량 등 주요 설계인자들이 최대 ~1.3%의 상대오차 범위 안에서 만족할 만한 신뢰도를 갖는 것을 확인하였다. 탈설계점 성능해석은 본 논문과 관련한 연구의 주목적인 LNG 냉열에 의한 유입공기 냉각시스템 설계시의 경계변수인 외기온도 증가에 대한 각 사이클의 특성변화를 대상으로 하였다. 종합적으로 외기온도가 증가하면 압축기로 유입되는 공기의 양과 이에 대응하는 소요 연료량이 동시에 감소하므로 연소에 따른 가스터빈의 팽창비가 감소한다. 이로 인하여 외기온도 증가시에 가스터빈 출력감소율은 0.5%/$^{\circ}C$로서 배기가스를 이용하는 증기사이클의 출력감소율 0.2%/$^{\circ}C$에 비해 민감하므로 가스터빈 유입공기의 냉각시스템의 설계는 복합화력발전 플랜트의 효율 향상에 크게 기여할 것으로 예상된다.