• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1996.05a
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• pp.29-37
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• 1996

항공기 가스터빈 엔진은 폭넓은 운용 영역에서 다양한 임무 수행을 하도록 요구되어짐에 따라 항공기 전체의 성능과 직관되는 엔진의 성능에 대한 정밀한 동적 모사와 제어는 매우 중요하다. 본 연구에서는 대표적인 동적 모사 프로그램인 DYNGEN을 이용하여 비선형 동적 모사를 하였고, 이를 바탕으로 엔진의 제어를 위해 비선형 엔진에 대한 Piecewise 선형화를 통해 선형 동적 모사를 수행하였으며, 엔진의 최적 제어 기법으로 LQR 방법을 이용하여 성능 제어를 수행하였다.

• 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.

• 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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• 2010.11a
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• pp.733-736
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• 2010

Korea Aerospace Research Institute (KARI) performed the preliminary design of liquid rocket engine high-altitude simulation firing test facility for the development and qualification of LRE for the 2nd stage of KSLV-II. The engine high-altitude simulation firing test facility, which are to be constructed at Goheung Space Center, will provide liquid oxygen and kerosene to enable the high-altitude simulation firing test of 2nd stage engine at ground test facility. The high-altitude environment is obtained using a supersonic diffuser operated by the self-ejecting jet from the liquid rocket engine.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.383-387
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• 2008

To design a high altitude test facility for testing liquid rocket engine optimal technical solutions with general understanding about characteristics of engines and test stands, mission of a rocket and the financial aspects of tests are required. In this paper conditions and requirements needed at the stage of conceptual design of high altitude engine test facility were suggested, and preliminary calculations of the sizes of a supersonic diffuser and volume of cooling water were carried out.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.11a
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• pp.12-12
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• 2000

국내에서 최초로 개발된 초등훈련기 KT-1의 추진기관인 터보프롭 엔진(PT6A-62)을 위한 정상상태 성능모사 및 진단 프로그램을 개발하였다. 개발된 정상상태 성능해석 프로그램의 검증을 위해 해석 결과를 엔진 제작사에서 제공한 성능 데이터 및 가스터빈 엔진의 성능모사 프로그램으로 잘 알려진 GASTURB와 비교하였다.(중략)

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.12
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• pp.1180-1185
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• 2008

In-house code which simulates the performance of pre-burner in staged-combustion liquid-fueled rocket engine was developed and demonstrated. Chemical reaction of pre-burner was modeled based on analytic algorithm of CEA (Chemical Equilibrium with Applications) and gas dynamics model was incorporated with it. Comparison results between in-house code and CEA have shown small relative errors except at very high or very low O/F ratio. Also the performance curve obtained by in-house code revealed that the calculated values follow the overall trend of real engine (RD-8) performance quite well and at steady-state operation, the deviation became very small.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1996.11a
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• pp.97-104
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• 1996

DYGABCD 프로그램을 이용해 선형모델의 구성에 필요한 시스템 행렬을 구하고 최소자승법을 이용하여 실시간 선형모사를 행한 후 DYNGEN 프로그램을 이용한 비선형 모사와 비교하여 그 타당성을 입증하였다. 그리고 가제어성과 가안정성을 시험하여 시스템에 대해 제어기설계가 가능한지 확인하고 엔진의 성능과 직결되는 터빈입구 온도의 Overshoot 제어를 위해 고전적 제어기법인 PI제어기와 현대적 최적제어기법인 LQR 제어기를 설계하여 각각의 성능을 비교해 보았다.

• Aerospace Engineering and Technology
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• v.5 no.2
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• pp.37-46
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• 2006

The outside environment is very severe while aircraft is cruising. Especially small particle of icing in cold air condition can have negative influence on aircraft performance. If ice particle is attached to leading edge of wing, it can change wing configuration and decrease flight quality. If icing particle is attached to inlet of engine, it can damage compressor blade and have negative influence to aircraft safety. We make icing simulation device with liquid air system for analyzing about variation of engine performance due to incoming of icing to engine.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.358-361
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• 2007

Most aircraft cruise in the stratosphere at which temperature is below $-50^{\circ}C$ md, as a result, the surface of aircraft can be iced up. Ice on the wing can change aerodynamic characteristic and results in the deterioration of its performance. Ice on the engine inlet increases the possibility of compressor blade damage and affects the performance and safety of the engine. This paper focused on the development of icing simulation device for analyzing effect of icing on engine performance. Icing simulation tests were conducted with a liquid air system and a icing simulation device and results show that icing could be simulated with this system.