Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Centrifugal Compressor Performance Characteristics Analysis with Impeller Leading Edge Location

임펠러 앞전 위치에 따른 원심압축기 성능특성 분석

  • Kim, Dongjun (Department of Aerospace Engineering, Pusan National University) ;
  • Kim, Kuisoon (Department of Aerospace Engineering, Pusan National University) ;
  • Choi, Jeongyeol (Department of Aerospace Engineering, Pusan National University)
  • Received : 2016.09.23
  • Accepted : 2016.11.12
  • Published : 2016.12.01
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Abstract

A study was conducted on the effect of leading edge location for the performance characteristics of a centrifugal compressor impeller. Five impellers with different leading edge location were selected for numerical analysis. The impeller with leading edge located 10% away from the inlet about meridional distance from entrance to exit showed the best total pressure ratio and efficiency. Also, this case showed relatively uniform flow distribution because of a weak intensity of the separation region at impeller exit. The impeller with leading edge located far from this location showed lowest total pressure ratio and efficiency. Performance of compressor also decreased due to non-uniform flow distribution at impeller exit.

본 논문은 원심압축기 임펠러의 앞전 위치가 성능특성에 어떠한 영향을 미치는지 알아보기 위한 연구를 수행하였다. 앞전의 위치가 다른 다섯 개의 임펠러를 계산 모델로 선정하여 전산해석을 수행하였다. 입구에서 출구까지의 자오면상 거리에 대해서 임펠러 날개 앞전이 입구로부터 10% 떨어진 위치에 있을 때 압력비 및 효율이 가장 좋은 결과를 보였다. 또한, 이 경우가 임펠러 출구에서 박리영역의 강도가 약하여 상대적으로 유동이 가장 균일한 결과를 보였다. 그리고 이 위치보다 멀어질수록 낮은 압력비와 효율을 보였다. 또한, 이 경우가 임펠러 출구에서 불균일한 유동을 가져 압축기의 성능이 감소하였다.

Keywords

References

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