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A Study on the Numerical Analysis Methodology for Thermal and Flow Characteristics of High Pressure Turbine in Aircraft Gas Turbine Engine

항공기용 가스터빈 엔진의 고압터빈에서 열유동 특성해석을 위한 전산해석기법 연구

  • Kim, Jinuk (Dept. of Mechanical engineering, Graduate School of Hanyang University) ;
  • Bak, Jeonggyu (Dept. of Mechanical engineering, Graduate School of Hanyang University) ;
  • Kang, Youngseok (Korea Aerospace Research Institute) ;
  • Cho, Leesang (Dept. of Mechanical & System Engineering, Hansung University) ;
  • Cho, Jinsoo (School of Mechanical Engineering, Hanyang University)
  • 김진욱 (한양대학교 대학원 기계공학과) ;
  • 박정규 (한양대학교 대학원 기계공학과) ;
  • 강영석 (한국항공우주연구원 엔진요소기술팀) ;
  • 조이상 (한성대학교 기계시스템공학과) ;
  • 조진수 (한양대학교 기계공학부)
  • Received : 2013.12.05
  • Accepted : 2014.01.03
  • Published : 2014.06.01

Abstract

In this study, a numerical analysis methodology is studied to predict thermal and flow characteristics of C3X vane with internal cooling. Effects of turbulence models, transition models and viscous work term on temperature and pressure distributions on the vane surface are investigated. These optional terms have few effects on the pressure distributions over the vane surface. However, they have great influence on prediction of the temperature distributions on the vane surface. The combination of k-${\omega}$ based SST turbulence model, ${\gamma}$ transition model and viscous work term are better than RSM turbulence model on prediction of the surface temperature. The average temperature difference between CFD results and experimental results is calculated 2 % at the pressure side and 1 % at the suction side. Furthermore computing time of this combination is half of the RSM turbulence model. When k-${\omega}$ based SST turbulence model and ${\gamma}$ transition model with viscous work term are applied, more accurate predictions of thermal and internal flow characteristics of high pressure turbine are expected.

Keywords

References

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