Journal of the Korean Society for Precision Engineering (한국정밀공학회지)

Korean Society for Precision Engineering (한국정밀공학회)
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Investigation of the High Cycle Fatigue Crack of the Gas Turbine Compressor Blade Using Finite Element Analysis

유한요소해석을 이용한 가스터빈 압축기 블레이드 피로균열 해석

  • 윤완노 (한국전력공사 전력연구원) ;
  • 김준성 (한국전력공사 전력연구원)
  • Received : 2010.06.24
  • Accepted : 2010.09.28
  • Published : 2010.12.01
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Abstract

A gas turbine consists of an upstream compressor and a downstream turbine with a combustion chamber, and also the compressor and the turbine are generally coupled using a single shaft. Large scale gas turbine compressor is designed as multi-stage axial flow and the blade is fan-type which is thick and wide. Recently radial cracking happens occasionally at the compressor blade tip of large scale gas turbine. So, FEM was performed on the compressor blade and vibration modes and dynamic stresses were analyzed. According to the analysis, 9th natural frequency mode of the blade, which is 2 strip mode, is near the vane passing frequency by the vane located at the upstream of the blade.

Keywords

References

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