• Advances in materials Research
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• 제8권2호
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• pp.117-135
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• 2019

The lifetime of a gas turbine combustor is typically limited by the durability of its liner, the structure that encloses the high-temperature combustion products. The primary objective of the combustor thermal design process is to ensure that the liner temperatures do not exceed a maximum value set by material limits. Liner temperatures exceeding these limits hasten the onset of cracking which increase the frequency of unscheduled engine removals and cause the maintenance and repair costs of the engine to increase. Hot gas temperature prediction can be considered a preliminary step for combustor liner temperature prediction which can make a suitable view of combustion chamber conditions. In this study, the temperature distribution of ceramic panels for a V94.2 gas turbine combustor subjected to realistic operation conditions is presented using three-dimensional finite difference method. A simplified model of alumina ceramic is used to obtain the temperature distribution. The external thermal loads consist of convection and radiation heat transfers are considered that these loads are applied to flat segmented panel on hot side and forced convection cooling on the other side. First the temperatures of hot and cold sides of ceramic are calculated. Then, the thermal boundary conditions of all other ceramic sides are estimated by the field observations. Finally, the temperature distributions of ceramic panels for a V94.2 gas turbine combustor are computed by MATLAB software. The results show that the gas emissivity for diffusion mode is more than premix therefore the radiation heat flux and temperature will be more. The results of this work are validated by ANSYS and ABAQUS softwares. It is showed that there is a good agreement between all results.

• 한국연소학회:학술대회논문집
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• 한국연소학회 2007년도 제34회 KOSCO SYMPOSIUM 논문집
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• pp.118-125
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• 2007

The firtst-order conditional moment closure (CMC) model is applied to CH4/air swirl diffusion flame in a gas turbine model combustor. The flow and mixing fields are calculated by fast chemistry assumption with SLFM library and a beta function pdf for mixture fraction. RNG k-e model is used to consider the swirl flame in a confined wall. Reacting scalar fields are calculated by elliptic CMC formulation with chemical kinetic mechanism, GRI Mech 3.0. Validation is done against measurement data for mean flow and scalar fields in the model combustor [1]. Results show reasonable agreement with the mean mixture fraction and its variance, while temperature is overpredicted as the level of local extinction increases. The second-order CMC model is needed to consider local extinction with considerable conditional fluctuations near the nozzle.

• 대한기계학회논문집A
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• 제41권10호
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• pp.1005-1009
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• 2017

본 연구에서는 수중폭발에 의한 가스터빈 패키지에 작용하는 충격하중을 평가하고, 충격하중에 대한 가스터빈 패키지의 내충격 안전성을 검토하였다. 이를 위해 먼저 BV043에 따른 시간이력 충격하중을 산출하고, 산출된 충격하중을 바탕으로 이상화된 WEM(Whole Engine Model, 전체시스템)에 대한 시간영역에서의 과도응답해석을 수행하였다. 이를 통해 가스터빈 패키지의 주요구성품에 전달되는 하중을 평가하였으며, 평가된 전달하중을 바탕으로 주요구성품의 상세모델에 대한 내충격 안전성 검토를 수행하였다. 검토결과 가스터빈 패키지는 기준응력 대비 최소 1.0 이상의 안전율을 가지는 것을 확인하였다. 그리고 실물테스트를 통해 가스터빈 패키지 엔진제어시스템(EMS : Engine Management System) 구조 및 제어기능의 내충격 건전성을 검증하였다.

• 한국유체기계학회 논문집
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• 제11권4호
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• pp.52-62
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• 2008

All forecasts of a future energy demand anticipate an increase across the globe. With the increase of energy demand, the emission of $CO_2$ is also likely to increase by at least the same amount because energy supply will be based on fossil fuels, which is more apparent in a number of developing countries. In this context, the Micro Gas Turbine (MGT) is being considered as a promising solution. In order to propose a feasible concept of those technologies such as improving environmental effect and economics, we performed a sensitivity study for a biomass fueled MGT using a simulation model. The study consists of 1) the fundamental modeling using manufacturer's technical specifications, 2) the correction with the experimental data, and 3) the sensitivity study for system parameters. The simulation model was developed by PEPSE-GT 72, commercial steam/gas turbine simulation toolbox.

• 한국추진공학회지
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• 제22권5호
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• pp.13-21
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• 2018

항공기용 엔진의 건전성 관리를 위한 탑재장비 및 지상 장비 소프트웨어의 발전 동향을 살펴보았다. 과거에는 지상 장비 중심의 결함 검출 및 식별기법에서 탑재 소프트웨어를 이용한 모델 기반의 건전성 식별 기법으로 변화해 왔고, 현재는 지상과 탑재장비 소프트웨어의 통합된 구조로 발전해 가고 있다. 이러한 진보된 기법이 선진국을 중심으로 기술발전을 이루어 가고 있음에 비해 국내의 연구는 초보적인 수준에 머물러 있다. 본 논문에서는 국내외 기술개발 현황을 고려하여 최적의 발전 방향을 제시하였다.

• 대한기계학회논문집A
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• 제37권6호
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• pp.769-774
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• 2013

가스터빈엔진의 핵심 부품인 디스크와 블레이드는 고효율, 수명주기 동안의 운용비 최소화 등의 요구조건으로 고온의 터빈입구 온도, 고압축비, 고속 환경에서 지속적으로 운용된다. 이러한 가혹한 환경에서의 구조 안전성을 평가하기 위해서는 재료 모델링과 유한요소해석 기법 등이 필수적이며 더 나아가 형상최적화가 반드시 요구된다. 본 연구에서는 터빈 디스크의 구조 건전성을 평가하기 위해 2 차원 축 대칭 및 섹터 모델을 생성하고, 열-구조 연성해석과 접촉 해석을 포함한 유한요소 해석을 수행하고자 한다. 이를 근거로 터빈 디스크에서 구조적으로 취약한 2 개의 영역인 디스크 보어와 디스크와 블레이드의 연결 부위인 도브테일에 대해 형상변수 고찰을 하고자 한다. 최종적으로 형상변수 결과를 기초로 한 개선된 디스크 형상을 제안함과 동시에 좀 더 정교한 형상최적화가 필요함을 확인한다.

• International Journal of Aeronautical and Space Sciences
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• 제15권4호
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• pp.434-443
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• 2014

A turbo fan engine performance analysis and the optimization using particle swarm optimization(PSO) algorithm have been conducted to investigate the effects of major performance design parameters of an aircraft gas turbine engine. The FJ44-2C turbofan engine, which is widely used in the small business jet, CJ2 has been selected as the basic model. The design parameters consists of the bypass ratio, burner exit temperature, HP compressor ratio, fan inlet mass flow, and nozzle cooling air ratio. The sensitivity analysis of the parameters has been evaluated and the optimization of the parameters has been performed to achieve high net thrust or low specific fuel consumption.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 춘계학술대회논문집D
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• pp.989-994
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• 2001

Numerical simulations of high temperature catalytic combustion have been performed for the application to a gas turbine combustor. Dependences of inlet temperature and pressure on the distributions of temperature and species concentrations were investigated using plug flow model with detailed homogeneous and heterogeneous chemistries of methane-air mixtures. Honeycomb typecombustor deposited with Pt catalyst of 100mm in length and 26mm in diameter is used. The results show that rapid increase of temperature profile occurs earlier with the increase of inlet temperature and the decrease of inlet pressure. The condition which catalytic combustion is stabilized exists at certain range of inlet temperature and pressure. The state of catalytic combustion is also confirmed by the distributions of species concentration.

• 한국신재생에너지학회:학술대회논문집
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• 한국신재생에너지학회 2005년도 춘계학술대회
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• pp.273-276
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• 2005

Performance analysis of a solid oxide fuel cell/micro gas turbine hybrid system is conducted at design-point and part-load conditions and its results are discussed in this study. With detailed considerations of the heat and mass transfer phenomena along various flow streams of the SOFC, the analysis based on a quasi-2D model reasonably predicts its performance at the design-point operating conditions. In case of part-load operations, performance of the hybrid system to three different operation modes(fuel only control, speed control, and VIGV control) is compared. It is found that the simultaneous control of both supplied fuel and air to the system with a variable MGT rotational speed mode is the optimum choice for the high performance operation. And then, the dynamic characteristics of a solid oxide fuel cell are briefly introduced.

• Journal of Mechanical Science and Technology
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• 제18권6호
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• pp.895-903
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• 2004

In this paper are presented the blade vibration characteristics at the starting conditions of the low pressure multistage axial compressor of heavy-duty 100 MW gas turbine. Vibration data have been collected through strain gauges during aerodynamic tests of the model compressor. The influences of operating modes at the starting conditions are investigated upon the compressor blade vibrations. The exciting mechanisms and features of blade vibrations are investigated at the surge, rotating stall, and buffeting flutter. The influences of operating modes upon blade dynamic stresses are investigated for the first and second stages. It is shown that a high dynamic stress peak of 120 MPa can occur in the first stage blades due to resonances with stall cell excitations or with inlet strut wake excitations at the stalled conditions.