• Transactions of the Korean Society of Mechanical Engineers A
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• v.41 no.10
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• pp.1005-1009
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• 2017

In this study, the shock resistance of a gas turbine package subjected to a shock load caused by non-contact underwater explosion was investigated using numerical analysis. To perform shock analysis, the time-history shock load was calculated according to BV-043 (German Navy Regulation). The direct transient response analysis in the time domain for the simplified Whole Engine Model (WEM) was performed using the calculated shock load. In addition, the structural integrity of a detailed model was evaluated by considering the shock load transferred to each component. As a result, it was confirmed that the safety factor was at least 1.0 as compared with the reference stress. Finally, the structural and functional integrity of the Engine Management System (EMS) of the gas turbine package was verified through an actual shock test.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.350-353
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• 2009

In the fatigue analysis and the components design, uncertainties are caused by the variances of geometry data and applied loads, and the scatter of material properties. In this paper, fatigue crack growth life of turbine is evaluated by fracture mechanics and the reliability analysis is accessed by the fist order second moment method and Monte Carlo simulation.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.864-870
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• 2017

The propellants are burned in the pre-burner of the staged combustion cycle engine, and the resulting hot gas drives the turbine, and the turbine operates the turbo pump. The burned gas passing through the turbo pump is supplied to the combustor at high temperature and high pressure, where the gas is supplied in an excess of fuel or an excess of oxidant depending on the amount of fuel or oxidant. When the cycle works at oxidizer-rich staged combustion, its metal pipe can ignite or explode by the impact of even small particles. In this study, we develop the powder combinations for anti-oxidation coating through the analysis of other coating materials and establish the coating process.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.5
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• pp.125-131
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• 2018

Some propellants in a liquid rocket engine are burned in the pre-burner of a staged combustion cycle engine, resulting hot gas drives the turbine. The burned gas passing through the turbine is supplied to the combustor at high temperature and pressure. The form of the gas can be fuel rich or oxidizer rich dependent upon the mixture ratio or the engine scheme. When the cycle works at oxidizer-rich condition, the metal pipes composing the engine can be ignited or even exploded by an impact of very a small particle. In this study, we developed the powder combination and processes for an anti-oxidation coating through the analysis of various coating materials.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.157-161
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• 2004

The colse type of engine system, in which the combustion gas after the gas-turbine with high temperature is supplied to the combustion chamber, was selected to increase the energy characteristics in making the rocket engine scheme which makes 1700kN thrust. The nozzle was designed with consideration of film cooling, nozzle efficiency, and the real state of cobmustion gas during the expansion in nozzle. The change of gas state and the composition of the gas through the nozzle was studied by the graphic, too.

• Proceedings of the KIEE Conference
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• 2006.07a
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• pp.539-540
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• 2006

소형 열병합 (CHP, Combined Heat & Power)은 발전 용량이 1MW 이하인 발전 시스템을 지칭하는 용어로, 전기와 더불어 원동기에서 발생한 폐열을 회수하여 사용한 수 있는 발전 시스템을 말한다. 대표적인 원동기로서는 가스 엔진, 터빈, 마이크로 터빈, 연료 전지 등이 있다. 소형 열병합 시스템은 폐열 회수의 특징으로 기존 시스템에 비해 50% 이상의 에너지 이용 효율이 높으며, 기존의 대형 발전 시스템에서 필연적으로 존재하는 송전 및 배전 손실이 존재하지 않는 수요지 발전의 특징도 갖고 있어서 연료 절약형 에너지 생산 시스템으로서의 높은 가치를 가지고 있다. 또 다른 장점으로 열병합 발전 시스템은 여름철의 최대 전력 부하를 제거하는 역할을 할 수 있음으로 국가 전력 수요 공급의 안정화에 기여하는 바가 크다. 본 논문에서는 최근에 개발된 325kW급 열병합 가스엔진 발전 시스템의 주제어를 담당하는 통합 제어 장치의 개발과 소형 열병합 시스템의 시험 결과에 대해서 소개한다.

• 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.87-91
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• 2004

It is definitely required to control dispersion of the rocket engine performance in order to accomplish the mission of launch vehicle successfully. We performed the dispersion analysis of gas generator cycle LRE (liquid rocket engine) accompanied with ANASYN. As a result, the vacuum thrust dispersion of the engine was $+5.34\%,\;-5.27\%$ and the mixture ratio deviated $+9.07\%,\;-9.82\%$ from the nominal value due to the errors of components and engine inlet condition of propellants. By applying the gas generator regulator only, the dispersion of the engine performance increases. Error in turbine efficiency is the most influential factor to the dispersion of engine performance.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.533-536
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• 2009

The power control system of Smart UAV is similar to the propeller pitch governing concept of turboprop aircraft. The pilot inputs the engine power directly and the pitch governor controls the rotational speed of proprotor. In this paper, the engine status data from ground test of Smart UAV, such as the relationship of PLA vs. Gas generator speed and power are compared with the result of engine performance calculation program.

• Journal of the Korean Society of Propulsion Engineers
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• v.27 no.1
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• pp.37-48
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• 2023

In this study, performance analysis modeling of two spool mixed flow type turbofan engine according to steady-state and transient is performed. The target engine is selected as F100-PW-229 from Pratt & Whitney, and main engine components including fan, high pressure compressors, combustion, high pressure turbines, low pressure turbines, mixer, convergent-divergent nozzle are modeled. The cooling effect of turbine through secondary flow path are considered in engine simulation model. We develop in-house Matlab/Simulink-based engine performance analysis program capable of analyzing internal engine state and compare it with GASTURB which is generally used as a commercial engine analysis program.