Structure of diffuser stall and unsteady vortices in a centrifugal compressor with vaned diffuser

研究成果: Conference contribution

7 被引用数 (Scopus)

抄録

The characteristics of a diffuser rotating stall and the evolution of a vortex generated on the diffuser leading edge (i.e., leading-edge vortex (LEV)) in a centrifugal compressor were investigated using experiments and numerical analyses. The experimental results showed that both impeller and diffuser rotating stalls occurred at 55 and 25 Hz during off-design flow operation. Both the stall cells existed only on the shroud side of the flow passages, which is in close proximity to the source location of the LEV. The numerical results showed that the LEV is a combination of a separated vortex near the leading edge and the extended tip-leakage flow from the impeller. In the partial flow operation, the LEV develops as the velocity decreases in the diffuser passages and forms a huge flow blockage within the diffuser passages. Therefore, the LEV may be considered to be one of the causes of diffuser stall in the centrifugal compressor.

本文言語English
ホスト出版物のタイトルTurbomachinery
出版社American Society of Mechanical Engineers (ASME)
ISBN(電子版)9780791849729
DOI
出版ステータスPublished - 2016
イベントASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition, GT 2016 - Seoul, Korea, Republic of
継続期間: 2016 6 132016 6 17

出版物シリーズ

名前Proceedings of the ASME Turbo Expo
2D-2016

Other

OtherASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition, GT 2016
CountryKorea, Republic of
CitySeoul
Period16/6/1316/6/17

ASJC Scopus subject areas

  • Engineering(all)

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