The KSFM Journal of Fluid Machinery (한국유체기계학회 논문집)

Korean Society for Fluid machinery (한국유체기계학회)
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Conjugate Heat Transfer Analysis for High Pressure Cooled Turbine Vane in Aircraft Gas Turbine

항공기용 가스터빈의 고압 냉각터빈 노즐에 대한 복합열전달 해석

  • Kim, Jinuk (Dept. of Mechanical Engineering, Hanyang Univ.) ;
  • Bak, Jeonggyu (Dept. of Mechanical Engineering, Hanyang Univ.) ;
  • Kang, Young-Seok (Engine Component Research Team, Korea Aerospace Research Institute) ;
  • Cho, Jinsoo (Dept. of Mechanical Engineering, Hanyang Univ.)
  • 김진욱 (한양대학교 기계공학과) ;
  • 박정규 (한양대학교 기계공학과) ;
  • 강영석 (한국항공우주연구원 엔진부품연구팀) ;
  • 조진수 (한양대학교 기계공학과)
  • Received : 2014.10.20
  • Accepted : 2015.02.13
  • Published : 2015.04.01
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Abstract

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 %.

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References

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