0
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
Your Session has timed out. Please sign back in to continue.

References

Greitzer, E. M. , 1981, “ The Stability of Pumping Systems—The 1980 Freeman Scholar Lecture,” ASME J. Fluids Eng., 103(2), pp. 193–242. [CrossRef]
Skoch, G. J. , 2003, “ Experimental Investigation of Centrifugal Compressor Stabilization Techniques,” ASME Paper No. GT2003-38524.
Camp, T. R. , and Day, I. J. , 1998, “ 1997 Best Paper Award—Turbomachinery Committee: A Study of Spike and Modal Stall Phenomena in a Low-Speed Axial Compressor,” ASME J. Turbomach., 120(3), pp. 393–401.
Mailach, R. , Lehmann, I. , and Vogeler, K. , 2001, “ Rotating Instabilities in an Axial Compressor Originating From the Fluctuating Blade Tip Vortex,” ASME J. Turbomach., 123(3), pp. 453–460. [CrossRef]
Marz, J. , Hah, C. , and Neise, W. , 2002, “ An Experimental and Numerical Investigation Into the Mechanisms of Rotating Instability,” ASME J. Turbomach., 124(3), pp. 367–374. [CrossRef]
Inoue, M. , Kuroumaru, M. , Tanino, T. , Yoshida, S. , and Furukawa, M. , 2001, “ Comparative Studies on Short and Long Length-Scale Stall Cell Propagating in an Axial Compressor Rotor,” ASME J. Turbomach., 123(1), pp. 24–30. [CrossRef]
Trebinjac, I. , Bulot, N. , Ottavy, X. , and Buffaz, N. , 2011, “ Surge Inception in a Transonic Centrifugal Compressor Stage,” ASME Paper No. GT2011-45116.
Toyama, K. , Runstadler, P. , and Dean, R. , 1977, “ An Experimental Study of Surge in Centrifugal Compressors,” ASME J. Fluids Eng., 99(1), pp. 115–124. [CrossRef]
Mizuki, S. , and Oosawa, Y. , 1991, “ Unsteady Flow Within Centrifugal Compressor Channels Under Rotating Stall and Surge,” ASME Paper No. 91-GT-085.
Tomita, I. , Ibaraki, S. , Furukawa, M. , and Yamada, K. , 2013, “ The Effect of Tip Leakage Vortex for Operating Range Enhancement of Centrifugal Compressor,” ASME J. Turbomach., 135(5), p. 051020. [CrossRef]
Spakovszky, Z. , and Roduner, C. , 2009, “ Spike and Modal Stall Inception in an Advanced Turbocharger Centrifugal Compressor,” ASME J. Turbomach., 131(3), p. 031012. [CrossRef]
Emmons, H. , Pearson, C. , and Grant, H. , 1955, “ Compressor Surge and Stall Propagation,” Trans. ASME, 77(4), pp. 455–469.
Dufour, G. , Carbonneau, X. , Arbez, P. , Cazalbou, J.-B. , and Chassaing, P. , 2004, “ Mesh-Generation Parameters Influence on Centrifugal Compressor Simulation for Design Optimization,” ASME Paper No. HT-FED2004-56314.
Cambier, L. , and Gazaix, M. , 2002, elsA: An Efficient Object-Oriented Solution to CFD Complexity, Office National d Etudes et de Recherches Aerospatiales Onera-Publications-Tp(15).
Spalart, P. R. , and Allmaras, S. R. , 1994, “ A One-Equation Turbulence Model for Aerodynamic Flows,” La Rech. Aérospaciale, 1, pp. 5–21.
Jameson, A. , 1991, “ Time Dependent Calculations Using Multigrid, With Applications to Unsteady Flows Past Airfoils and Wings,” AIAA Paper No. 1596.
Yoon, S. , and Jameson, A. , 1987, “ An Lu-SSOR Scheme for the Euler and Navier–Stokes Equations,” AIAA Paper No. 600.
Sicot, F. , Dufour, G. , and Gourdain, N. , 2012, “ A Time-Domain Harmonic Balance Method for Rotor/Stator Interactions,” ASME J. Turbomach., 134(1), p. 011001. [CrossRef]
Fillola, G. , Le Pape, M.-C. , and Montagnac, M. , 2004, Numerical Simulations Around Wing Control Surfaces, Office National d Etudes et de Recherches Aerospatiales Onera-Publications-Tp(186).
Dufour, G. , Carbonneau, X. , Cazalbou, J.-B. , and Chassaing, P. , 2006, “ Practical Use of Similarity and Scaling Laws for Centrifugal Compressor Design,” ASME Paper No. GT2006-91227.
Cumpsty, N. A. , 1989, Compressor Aerodynamics, Longman Scientific & Technical, Essex, UK.
Jeong, J. , and Hussain, F. , 1995, “ On the Identification of a Vortex,” J. Fluid Mech., 285, pp. 69–94. [CrossRef]
Michalke, A. , 1964, “ On the Inviscid Instability of the Hyperbolictangent Velocity Profile,” J. Fluid Mech., 19(4), pp. 543–556. [CrossRef]

Figures

Grahic Jump Location
Fig. 1

Three-dimensional sketch of the compressor stage

Grahic Jump Location
Fig. 2

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

Grahic Jump Location
Fig. 3

Pressure ratio of the compressor stage

Grahic Jump Location
Fig. 4

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

Grahic Jump Location
Fig. 5

Illustration of the flow mechanism in the blade tip region

Grahic Jump Location
Fig. 6

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

Grahic Jump Location
Fig. 7

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

Grahic Jump Location
Fig. 8

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

Grahic Jump Location
Fig. 9

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

Grahic Jump Location
Fig. 10

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

Grahic Jump Location
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

Grahic Jump Location
Fig. 12

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

Grahic Jump Location
Fig. 13

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

Grahic Jump Location
Fig. 14

Theoretical representation of the velocity profile in a shear layer

Grahic Jump Location
Fig. 15

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

Grahic Jump Location
Fig. 16

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

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In