Physical explanations of tip leakage flow field in an axial compressor rotor

Masahiro Inoue, Masato Furukawa, Kazuhisa Saiki, Kazutoyo Yamada

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Citation (Scopus)

Abstract

Structure of a tip leakage flow field in an axial compressor rotor has been investigated by detailed numerical simulations and appropriate post-processing. Physical explanations of the structure are made in terms of vortex-core identification, normalized helicity, vortex-lines, limiting streamlines, etc. The onset of the discrete tip leakage vortex is located on the suction surface at some distance from the leading edge. The vortex core with high vorticity is generated from a shear layer between the leakage jet flow and the main flow. The streamlines in the leakage flow are coiling around the vortex core. All the vortex-lines in the tip leakage vortex core link to ones in the suction surface boundary layer. The other vortex-lines in the suction surface boundary layer link to the vortex-lines in the pressure surface boundary layer and in the casing wall boundary layer. There are two mechanisms to reduce intensity of the tip leakage vortex: one is reduction of discharged vorticity caused by the linkage of vortex-lines between the suction surface and casing wall boundary layers, and another is diffusion of vorticity from the tip leakage vortex. Relative motion of the endwall has a substantial influence on the structure of the leakage flow field. In the case of a compressor rotor, it intensifies streamwise vorticity of the leakage vortex but reduces leakage flow loss.

Original languageEnglish
Title of host publicationTurbomachinery
PublisherAmerican Society of Mechanical Engineers (ASME)
ISBN (Electronic)9780791878620
DOIs
Publication statusPublished - Jan 1 1998
EventASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition, GT 1998 - Stockholm, Sweden
Duration: Jun 2 1998Jun 5 1998

Publication series

NameProceedings of the ASME Turbo Expo
Volume1

Other

OtherASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition, GT 1998
CountrySweden
CityStockholm
Period6/2/986/5/98

Fingerprint

Compressors
Flow fields
Vortex flow
Rotors
Leakage (fluid)
Boundary layers
Vorticity

All Science Journal Classification (ASJC) codes

  • Engineering(all)

Cite this

Inoue, M., Furukawa, M., Saiki, K., & Yamada, K. (1998). Physical explanations of tip leakage flow field in an axial compressor rotor. In Turbomachinery (Proceedings of the ASME Turbo Expo; Vol. 1). American Society of Mechanical Engineers (ASME). https://doi.org/10.1115/98-GT-091

Physical explanations of tip leakage flow field in an axial compressor rotor. / Inoue, Masahiro; Furukawa, Masato; Saiki, Kazuhisa; Yamada, Kazutoyo.

Turbomachinery. American Society of Mechanical Engineers (ASME), 1998. (Proceedings of the ASME Turbo Expo; Vol. 1).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Inoue, M, Furukawa, M, Saiki, K & Yamada, K 1998, Physical explanations of tip leakage flow field in an axial compressor rotor. in Turbomachinery. Proceedings of the ASME Turbo Expo, vol. 1, American Society of Mechanical Engineers (ASME), ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition, GT 1998, Stockholm, Sweden, 6/2/98. https://doi.org/10.1115/98-GT-091
Inoue M, Furukawa M, Saiki K, Yamada K. Physical explanations of tip leakage flow field in an axial compressor rotor. In Turbomachinery. American Society of Mechanical Engineers (ASME). 1998. (Proceedings of the ASME Turbo Expo). https://doi.org/10.1115/98-GT-091
Inoue, Masahiro ; Furukawa, Masato ; Saiki, Kazuhisa ; Yamada, Kazutoyo. / Physical explanations of tip leakage flow field in an axial compressor rotor. Turbomachinery. American Society of Mechanical Engineers (ASME), 1998. (Proceedings of the ASME Turbo Expo).
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