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Research Papers

Numerical Investigation of Kelvin–Helmholtz Instability in a Centrifugal Compressor Operating Near Stall

[+] Author and Article Information
Y. Bousquet

Département Aérodynamique,
Energétique et Propulsion,
Université de Toulouse, ISAE,
10, Avenue Edouard Belin BP 54032,
Toulouse Cedex 4 31055, France
e-mail: Yannick.Bousquet@isae.fr

N. Binder

Département Aérodynamique,
Energétique et Propulsion,
Universite de Toulouse, ISAE,
10, Avenue Edouard Belin BP 54032,
Toulouse Cedex 4 31055, France
e-mail: Nicolas.Binder@isae.fr

G. Dufour

Département Aérodynamique,
Energétique et Propulsion,
Universite de Toulouse, ISAE,
10, Avenue Edouard Belin BP 54032,
Toulouse Cedex 4 31055, France
e-mail: Guillaume.Dufour@isae.fr

X. Carbonneau

Département Aérodynamique,
Energétique et Propulsion,
Universite de Toulouse, ISAE,
10, Avenue Edouard Belin BP 54032,
Toulouse Cedex 4 31055, France
e-mail: Xavier.Carbonneau@isae.fr

I. Trebinjac

Laboratoire de Mécanique des Fluides et
d'Acoustique,
Ecole Centrale de Lyon,
UCBLyon 1, INSA,
36 Avenue Guy de Collongue,
Ecully Cedex 69134, France
e-mail: Isabelle.Trebinjac@ec-lyon.fr

M. Roumeas

Département aéroacoustique,
Liebherr-Aerospace Toulouse SAS,
408 Avenue des Etats-Unis,
Toulouse 31016, France
e-mail: Mathieu.Roumeas@Liebherr.com

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received December 4, 2015; final manuscript received December 15, 2015; published online February 17, 2016. Editor: Kenneth C. Hall.

J. Turbomach 138(7), 071007 (Feb 17, 2016) (9 pages) Paper No: TURBO-15-1292; doi: 10.1115/1.4032457 History: Received December 04, 2015; Revised December 15, 2015

The present work details the occurrence of the Kelvin–Helmholtz instability in a centrifugal compressor operating near stall. The analysis is based on unsteady three-dimensional simulations performed on a calculation domain covering the full annulus for the impeller and the vaned diffuser. A detailed investigation of the flow structure is presented, together with its evolution consequent to the mass flow reduction. It is demonstrated that this reduction leads to an enlargement of the low-momentum flow region initially induced by the combination of the secondary and leakage flows. When the compressor operates near stall, the shear layer at the interface between the main flow and this low-momentum flow becomes unstable and induces a periodic vortex shedding. The frequency of such an unsteady phenomenon is not correlated with the blade-passing frequency. Its signature is thus easily isolated from the deterministic rotor/stator interaction. Its detection requires full-annulus simulations with an accurate resolution in time and space, which explains why it has never been previously observed in centrifugal compressors.

Copyright © 2016 by ASME
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References

Figures

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Fig. 1

Three-dimensional sketch of the compressor stage

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Fig. 2

Meridional view of the compressor stage with the position of the numerical probes in a blade-to-blade representation

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Fig. 9

Contours of instantaneous reduced meridional velocity in the impeller inducer at 90% span for the NS operating point

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Fig. 8

Contours of time-averaged magnitude vorticity at 90% span for OP1 and NS operating points

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Fig. 11

Amplitude of the discrete Fourier transform of static pressure signals extracted in the relative frame in the impeller inducer for the operating point NS

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Fig. 12

Phase of the vortex shedding frequency extracted from the height numerical probes positioned in the impeller blade channels at shroud

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Fig. 13

Contour of instantaneous reduced static pressure in the impeller at 90% span for the NS operating point

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Fig. 14

Theoretical representation of the velocity profile in a shear layer

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Fig. 15

Amplitude of the discrete Fourier transform of a static pressure signal in the fixed frame in the impeller inducer

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Fig. 16

Amplitude of the discrete Fourier transform of a treated static pressure signal in the fixed frame in the impeller

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Fig. 7

Contours of time-averaged reduced meridional velocity at 90% span for OP1 and NS operating points

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Fig. 6

Contours of time-averaged reduced meridional velocity at section B for OP1 and NS operating points

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Fig. 5

Illustration of the flow mechanism in the blade tip region

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Fig. 4

Line integral convolution of the skin friction pattern on the impeller blade suction side for OP1 and NS operating points

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Fig. 3

Pressure ratio of the compressor stage

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Fig. 10

Isosurface of positive axial velocity (blue), isosurface of negative axial velocity (red), and isosurface of λ2 vortex criteria (golden)

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