The modifications of meridional form and blade thickness of the impeller of an industrial radial compressor stage (impeller outlet blade angle 32 deg., relative width parameter 0.05) have been designed to extend the operating range of the stage in the area of higher flow rates and to reduce aerodynamic losses in this region. Quasi-3D calculations of the flow pattern in both original and modified impeller flow channels have been carried out to assess the influence of channel form change. The aerodynamic performance of the stage operating with both impellers has been tested on a test rig. The original stage was equipped with varied diffuser only, the modified one was tested with both vaned and vaneless diffusers. Detailed measurements of the flow field behind the impeller outlet have also been carried out. The results of these investigations are presented. Aerodynamic performance and losses in individual flow parts of the stages are compared and discussed.
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ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition
June 2–5, 1998
Stockholm, Sweden
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-7862-0
PROCEEDINGS PAPER
The Influence of Impeller Flow Channel Modification on Aerodynamic Performance of a Centrifugal Compressor Stage
Jan Paroubek,
Jan Paroubek
AHT Energetics Ltd., Prague, Czech Republic
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Jiří Kynčl
Jiří Kynčl
ČKD Energo, a.s., Prague, Czech Republic
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Jan Paroubek
AHT Energetics Ltd., Prague, Czech Republic
Jiří Kynčl
ČKD Energo, a.s., Prague, Czech Republic
Paper No:
98-GT-040, V001T01A013; 8 pages
Published Online:
December 23, 2014
Citation
Paroubek, J, & Kynčl, J. "The Influence of Impeller Flow Channel Modification on Aerodynamic Performance of a Centrifugal Compressor Stage." Proceedings of the ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. Volume 1: Turbomachinery. Stockholm, Sweden. June 2–5, 1998. V001T01A013. ASME. https://doi.org/10.1115/98-GT-040
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