Journal of Thermal Science

, Volume 26, Issue 4, pp 289–296 | Cite as

An experimental description of the flow in a centrifugal compressor from alternate stall to surge

  • V. Moënne-Loccoz
  • I. Trébinjac
  • E. Benichou
  • S. Goguey
  • B. Paoletti
  • P. Laucher


The present paper gives the experimental results obtained in a centrifugal compressor stage designed and built by SAFRAN Helicopter Engines. The compressor is composed of inlet guide vanes, a backswept splittered unshrouded impeller, a splittered vaned radial diffuser and axial outlet guide vanes. Previous numerical simulations revealed a particular S-shape pressure rise characteristic at partial rotation speed and predicted an alternate flow pattern in the vaned radial diffuser at low mass flow rate. This alternate flow pattern involves two adjacent vane passages. One passage exhibits very low momentum and a low pressure recovery, whereas the adjacent passage has very high momentum in the passage inlet and diffuses efficiently. Experimental measurements confirm the S-shape of the pressure rise characteristic even if the stability limit experimentally occurs at higher mass flow than numerically predicted. At low mass flow the alternate stall pattern is confirmed thanks to the data obtained by high-frequency pressure sensors. As the compressor is throttled the path to instability has been registered and a first scenario of the surge inception is given. The compressor first experiences a steady alternate stall in the diffuser. As the mass flow decreases, the alternate stall amplifies and triggers the mild surge in the vaned diffuser. An unsteady behavior results from the interaction of the alternate stall and the mild surge. Finally, when the pressure gradient becomes too strong, the alternate stall blows away and the compressor enters into deep surge.


centrifugal compressor alternate stall mild surge deep surge 


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Copyright information

© Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany 2017

Authors and Affiliations

  • V. Moënne-Loccoz
    • 1
  • I. Trébinjac
    • 2
  • E. Benichou
    • 3
  • S. Goguey
    • 2
  • B. Paoletti
    • 2
  • P. Laucher
    • 2
  1. 1.Safran Helicopter EnginesBordesFrance
  2. 2.Laboratoire de Mécanique des Fluides et d’Acoustique, UMR CNRS 5509Ecole Centrale de Lyon, UCBLyon, INSAEcully CedexFrance
  3. 3.FRATECH RP S.A.S, Seconded to BELGATECH Engineering Services SP Woluwe Gate Boulevard de la Woluwelaan, 2BrusselsBelgium

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