Journal of the Korean Society for Aviation and Aeronautics (한국항공운항학회지)

The Korean Society for Aviation and Aeronautics (한국항공운항학회)
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A Numerical Investigation of External and Internal Heat Transfer in A High Subsonic in Turbine Cascade

고 아음속 터빈 깃 주위의 열유동 및 내부 열전달에 관한 수치해석 연구

  • 김우진 (동서울대학 항공자동차기계공학부) ;
  • 김현식 (한국항공대학교) ;
  • 곽재수 (한국항공대학교) ;
  • 김학봉 (한국항공대학교 항공우주 및 기계공학부)
  • Received : 2010.03.03
  • Accepted : 2010.03.26
  • Published : 2010.03.31
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Abstract

Developments of numerical methods are very important to design and analysis for a high subsonic turbine blade. In general, Analysis by experimental investigation has needed a lot of human resources and required time, indispensably, and equipments still have a limit to measure in conditions of high temperature. Rapid technological developments of CPU and integration level of memory make it possible to advance computation with almost exactly simulation so, recent developments of numerical methods are in spotlight. In the present study, the panel method, which is well-known as relatively simplified numerical method, and 2-dimensional ordinary differential Falkner-Skan equation were computed in order to analyze the outer flow, and FVM-based solid heat transfer equation, was also computed to forecast the temperature distribution of the airfoil and the turbine blade. Unstructured grid was constructed in the turbine blade, which has double cooling holes, in order to analyze the internal heat transfer. Cooling fluid was assumed as fully-developed turbulent flow and that circulated in cooling holes.

Keywords

References

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