• 한국유체기계학회 논문집
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• 제18권2호
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• pp.60-66
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• 2015

Conjugate heat transfer analysis was performed to investigate the flow and cooling performance of the high pressure turbine nozzle of gas turbine engine. The CHT code was verified by comparison between CFD results and experimental results of C3X vane. The combination of k-${\omega}$ based SST turbulence model and transition model was used to solve the flow and thermal field of the fluid zone and the material property of CMSX-4 was applied to the solid zone. The turbine nozzle has two internal cooling channels and each channel has a complex cooling configurations, such as the film cooling, jet impingement, pedestal and rib turbulator. The parabolic temperature profile was given to the inlet condition of the nozzle to simulate the combustor exit condition. The flow characteristics were analyzed by comparing with uncooled nozzle vane. The Mach number around the vane increased due to the increase of coolant mass flow flowed in the main flow passage. The maximum cooling effectiveness (91 %) at the vane surface is located in the middle of pressure side which is effected by the film cooling and the rib turbulrator. The region of the minimum cooling effectiveness (44.8 %) was positioned at the leading edge. And the results show that the TBC layer increases the average cooling effectiveness up to 18 %.

• 한국연소학회지
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• 제18권1호
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• pp.1-6
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• 2013

Authors' previous works on thermoacoustic(TA) model development showed good results in predicting combustion instability characteristics in a gas turbine combustor. However, they also suggested there were some limitations in growth rate estimation, which might be related with over-simplification of flame structure. As a first trial for improving the model accuracy, the current paper introduces the modified TA model considering the actual flame location in the combustor. The combustor is divided into the unburned and the burned area before and after the flame location, and then acoustic equations are re-organized. The modified TA model results show a better accuracy in predicting the growth rate of instabilities comparing with the previous results. However, obtained results still overestimate the conditions where the combustor goes unstable. Further researches considering heat release distribution through flames are required.

• 한국연소학회:학술대회논문집
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• 한국연소학회 2004년도 제28회 KOSCO SYMPOSIUM 논문집
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• pp.192-198
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• 2004

A numerical study was conducted to determine the effects of high temperature air, including equivalent ratio on flow field, temperature, evaporation, and overall temperature distribution in gas turbine combustor. A sector model of a typical wall jet can combustor, featuring introduction of primary air and dilution air via wall jet, was used in calculations. Flow field and temperature distribution were analyzed. Operating conditions such as inlet temperature and overall equivalent ratio were varied from 373 to 1300 K, and from 0.3 to 0.6, respectively, while any other operating conditions were fixed. The RNG ${\kappa}-{\varepsilon}$ model and eddy breakup model were used for turbulence and combustion model respectively. It was found that the increase with the inlet air temperature, velocity in the combustor is accelerated and evaporation of liquid fuel is not affected in primary zone, high temperature inlet air enhances the evaporation and improves overall temperature distribution factor.

• 한국추진공학회지
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• 제13권2호
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• pp.42-53
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• 2009

가스터빈 엔진을 모사하기 위한 프로그램을 2차원 CFD 코드를 기반으로 개발 하였다. 압축기와 터빈은 k-$\omega$ SST 난류 모델의 2차원 NS(Navier Stokes) 코드를 이용하였고, 연소기는 lumped method 화학 평형 코드를 바탕으로 완전 혼합 상태에서 연소효율 100%로 가정된 케로신 공기 반응의 생성물 중 대표적인 10종류를 몰분율을 계산, 당량비에 따른 연소기 온도를 예측하였다. 압축기, 터빈에서 로터의 회전에 의한 비정상 유동 현상은 mixing-plane 기법을 이용한 경계면 처리로 그 효과를 나타내었고, 압축기는 연소기로 온도 압력을 주고, 연소기는 터빈으로 온도와 질유량을 전달하나 압력의 변화가 없는 것으로 가정하였다. 이를 바탕으로 아음속 조건에서의 압축기 입구 조건과 터빈 출구 조건, 회전수, 연소기의 당량비를 주는 것만으로 엔진의 성능이 계산 될 수 있는 통합 코드를 구성하였다.

• 에너지공학
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• 제18권2호
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• pp.93-100
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• 2009

습식압축으로 압축소요동력을 줄이고 재생기로 배기가스 에너지를 회수함으로써 열효율을 향상시킬 수 있는 습식압축 재생 브레이튼 사이클에 대하여 엑서지 해석을 수행하였다. 해석모델을 통하여 시스템의 엑서지 효율과 요소별 엑서지 파괴비 및 배기가스로 인한 엑서지 손실비에 미치는 압력비와 물분사율의 영향을 조사하였다. 전형적인 운전조건에 대한 계산 결과 습식압축 재생 가스터빈 사이클에 의하여 엑서지 효율을 상당히 향상시킬 수 있음을 확인하였다. 물 분사 효과는 배기가스의 엑서지 손실의 감소와 출력 동력의 증가로 나타난다.

• 대한기계학회논문집B
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• 제36권2호
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• pp.225-232
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• 2012

희박 예혼합 가스터빈 연소기에서 배출되는 NOx, CO 와 같은 오염물질을 예측하기 위해서 화학반응기 네트워크 모델을 개발했다. 본 연구에서는 CHEMKIN 코드와 4 가지 NO 생성 메커니즘을 포함한 GRI 3.0 메탄-공기 연소 메커니즘을 이용해서 가스터빈의 부하조건을 변화시키며 NOx 및 CO 배출의 예측을 수행하였다. 모델의 검증을 위해서 계산된 결과를 모사연소기의 실험 데이터와 비교하였다. 여러부하조건에 따른 4 가지 NO 경로의 기여도를 조사하였다. 또한 인젝터의 질량유동 및 당량비의 불균일성이 NOx 배출이 끼치는 영향을 고찰하고 10ppm 이하의 저 NOx 연소기 개발을 위한 저감 방법을 제안했다.

• Nuclear Engineering and Technology
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• 제41권7호
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• pp.875-884
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• 2009

We present three nuclear/hydrogen-related R&D activities being performed at KAIST: air-ingressed LOCA analysis code development, gas turbine analysis tool development, and hydrogen-production system analysis model development. The ICE numerical technique widely used for the safety analysis of water-reactors is successfully implemented into GAMMA, with which we solve the basic equations for continuity, momentum conservation, energy conservation of the gas mixture, and mass conservation of 6 species (He, N2, O2, CO, CO2, and H2O). GAMMA has been extensively validated using data from 14 test facilities. We developed a tool to predict the characteristics of HTGR helium turbines based on the throughflow calculation with a Newton-Raphson method that overcomes the weakness of the conventional method based on the successive iteration scheme. It is found that the current method reaches stable and quick convergence even under the off-normal condition with the same degree of accuracy. The dynamic equations for the distillation column of HI process are described with 4 material components involved in the HI process: H2O, HI, I2, H2. For the HI process we improved the Neumann model based on the NRTL (Non-Random Two-Liquid) model. The improved Neumann model predicted a total pressure with 8.6% maximum relative deviation from the data and 2.5% mean relative deviation, and liquid-liquid-separation with 9.52% maximum relative deviation from the data.

• 한국추진공학회지
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• 제25권4호
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• pp.43-52
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• 2021

본 연구에서는 기계식 추진 시스템인 CODOG 구조의 통합 제어를 위하여 구성 모듈인 가스터빈 엔진의 성능 모델링 및 시뮬레이션을 수행하였다. 엔진 모델은 상위 제어기 및 타 구성 모듈과의 통합이 용이하도록 MATLAB/Simulink를 이용하였으며, 시스템의 구성 및 목적에 맞는 입/출력 설정이 가능하도록 구성하였다. 일반적으로 엔진 제작사는 엔진 및 구성요소의 성능 데이터를 제공하지 않는다. 따라서 가스터빈 엔진에 대한 모델링 기법으로 구성요소의 맵을 스케일링하여 성능 데이터를 확보하는 CMF 기법을 적용하였다. 생성한 모델 및 시뮬레이션 프로그램을 이용하여 정상상태 및 동적 해석 시험을 수행하였으며, 최종 출력 결과에 대해 최대 오차 5% 이내의 신뢰성을 확보하였다.

• 수산해양기술연구
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• 제59권1호
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• pp.55-64
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• 2023

Gas turbine engines are widely used as prime movers of generator and propulsion system in warships. This study addresses the problem of designing a DS-based PID controller for speed control of the LM-2500 gas turbine engine used for propulsion in warships. To this end, we first derive a dynamic model of the LM-2500 using actual sea trail data. Next, the PRC (process reaction curve) method is used to approximate the first-order plus time delay (FOPTD) model, and the DS-based PID controller design technique is proposed according to approximation of the time delay term. The proposed controller conducts set-point tracking simulation using MATLAB (2016b), and evaluates and compares the performance index with the existing control methods. As a result of simulation at each operating point, the proposed controller showed the smallest in %OS, which means that the rpm does not change rapidly. In addition, IAE and IAC were also the smallest, showing the best result in error performance and controller effort.

• 한국연소학회지
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• 제17권2호
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• pp.17-23
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• 2012

In this study, thermoacoustic analysis model was developed in order to predict both eigenfrequencies and initial growth rate of combustion instabilities for lean premixed gas turbine combustors. As a first step, a model combustor and nozzle were selected and analytical linear equations for thermoacoustic waves were derived for a given combustion system. Then, methods showing how the equations can be used for analysis of the combustion instability were suggested. It was found that the prediction results showed a good agreement with the measurements. However, there were some limitation in growth rate predictions, which were related with over-simplification of flame structure, acoustic boundary conditions, and temperature distribution in the combustor.