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Aerodynamic instabilities in transonic centrifugalcompressor

Published online by Cambridge University Press:  16 May 2014

N. Buffaz  and
I. Trebinjac
N. Buffaz
Affiliation:
TURBOMECA, Groupe SAFRAN, 64511 Bordes, France
I. Trebinjac*
Affiliation:
Laboratoire de Mécanique des Fluides et d’Acoustique, UMR CNRS 5509, Ecole Centrale de Lyon, 36 av. Guy de Collongue, 69134 Ecully Cedex, France
*
a Corresponding author:Isabelle.Trebinjac@ec-lyon.fr
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Abstract

This paper presents the analysis of the instabilities inception in a transoniccentrifugal compressor for different rotation speeds. The analysis was conducted fromexperimental results obtained with unsteady pressure sensors implanted in the inducer,vaneless diffuser and vaned diffuser. Beyond the stability limit the compressor entersinto a deep surge without any precursor, whatever the speed. The surge process isinitiated in the vaned diffuser by a massive boundary layer separation. For low speeds,together with the surge which remains triggered in the diffuser, aerodynamic instabilitiesare detected in the inducer. These instabilities can be understood as “tip clearancerotating disturbances” because they are generated at the leading edge of the impeller mainblades and move along the tip clearance trajectory.

Keywords

transonic centrifugal compressorinstabilitiessurgemild stallCompresseur centrifuge transsoniqueinstabilitéspompagedécollement tournant

Information

Type
Research Article
Information
Mechanics & Industry , Volume 15 , Issue 3 , 2014 , pp. 191 - 196
Copyright
© AFM, EDP Sciences 2014

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