Journal of computational fluids engineering (한국전산유체공학회지)

Korean Society of Computational Fluids Engineering (한국전산유체공학회)
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DESIGN OPTIMIZATION AND PERFORMANCE ANALYSIS OF INTERNAL COOLING PASSAGE WITH VARIOUS TYPE OF RIB TURBULATOR FOR HIGH PRESSURE TURBINE NOZZLE

전산유체해석을 이용한 다양한 요철 형상에 대한 고압터빈 노즐 냉각유로 최적화 및 냉각 성능 비교

  • Lee, S.A. (Dept. of Mechanical and Aerospace Engineering, Seoul National Univ.) ;
  • Rhee, D.H. (Korea Aerospace Research Institute, Engine component technology team) ;
  • Kang, Y.S. (Korea Aerospace Research Institute, Engine component technology team) ;
  • Yee, K.J. (Dept. of Mechanical and Aerospace Engineering, Seoul National Univ.) ;
  • Kim, K.H. (Dept. of Mechanical and Aerospace Engineering, Seoul National Univ.)
  • 이상아 (서울대학교 기계항공공학부) ;
  • 이동호 (한국항공우주연구원 엔진요소기술팀) ;
  • 강영석 (한국항공우주연구원 엔진요소기술팀) ;
  • 이관중 (서울대학교 기계항공공학부) ;
  • 김규홍 (서울대학교 기계항공공학부)
  • Received : 2014.08.29
  • Accepted : 2014.10.22
  • Published : 2014.12.31
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Abstract

This study conducts shape optimization of rib turbulator on the internal cooling passage that has triangular cross-section of high pressure turbine nozzle. During optimization, various types of rib turbulator including angled, V-shaped, A-shaped and angled rib with intersecting rib are considered. Each type of rib turbulator is parameterized with attack angle(s), rib height, spacing ratio and bending/intersecting location. For optimization, Design of Experiment (DOE) and Kriging surrogate model are used to utilize computational resource more efficiently and Genetic Algorithm (GA) is used to search the optimum points. As a result, Pareto front of each type of rib turbulator with friction factor that relates to pressure drop in cooling passage and spatially averaged Nusselt number that relates to heat transfer on the wall is drawn and optimum points on the Pareto front are suggested.

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References

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