The KSFM Journal of Fluid Machinery (한국유체기계학회 논문집)

Korean Society for Fluid machinery (한국유체기계학회)
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Numerical Investigation on Internal Flow Field of a Single-Stage Transonic Axial Compressor

수치해석을 활용한 1단 천음속 압축기 내부 유동장 분석

  • 송지한 (과학기술연합대학원대학교) ;
  • 황오식 (한국항공우주연구원 항공추진기관팀) ;
  • 박태춘 (한국항공우주연구원 항공추진기관팀) ;
  • 임병준 (한국항공우주연구원 항공추진기관팀) ;
  • 양수석 (한국항공우주연구원 항공추진기관팀) ;
  • 강영석 (한국항공우주연구원 항공추진기관팀)
  • Received : 2012.10.23
  • Accepted : 2012.11.19
  • Published : 2012.12.01
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Abstract

Numerical simulations on a single stage transonic compressor which is developed by Korea Aerospace Research Institute are carried out and their results are compared with experimental data for cross validations. Comparisons between experimental data and numerical simulation results show good agreements on a performance curve, static pressure and total pressure distributions. CFD results show that there is a clear interaction between tip leakage flow and normal shock in the rotor passage. Tip leakage flows are almost dissipated after the strong normal shock and it forms a strong recirculation near the blade tip. Also a large separation region grows on the suction surface just after the normal shock. As the pressure ratio and blade loading increase, the normal shock line moves upstream and it starts to deviate from the blade leading edge. Then the tip leakage flow does not overcome the strong adverse pressure gradient and flow blockage originated from the tip recirculation region. As a result, the tip leakage flow heads for the neighboring blade leading edge, which results in a compressor stall.

Keywords

References

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