Fluid Mechanics and Acoustics Laboratory - UMR 5509

LMFA - UMR 5509
Laboratoire de Mécanique des Fluides et d’Acoustique

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Home > Teams > Turbomachinery Team > T1 - Instationnarités et Instabilités Aérodynamiques

Impact of passive flow control on the stability of a centrifugal compressor

Theme 1 - Instationnarités et Instabilités Aérodynamiques
Period 11/02/2019-10/02/2022
Contact(s) TREBINJAC Isabelle
PhD student POUJOL Nicolas
Partners Fabien Artus (SHE)

A research centrifugal compressor stage designed and built by Safran Helicopter Engines is tested at 3 IGV (Inlet Guide Vanes) stagger angles. The compressor stage includes 4 blade rows: axial inlet guide vanes, a backswept splittered impeller, a splittered vaned radial diffuser and axial outlet guide vanes. The shift of the surge line towards lower mass flow rate as the IGV stagger angle increases highly depends on the rotation speed. The surge line shift is very small at low rotation speeds whereas it significantly increases at high rotation speeds. At low rotation speeds below a given mass flow rate, rotating instabilities at the impeller inlet are detected at zero IGV stagger angle. Their occurrence is conditioned by the relative flow angle at the tip of the leading edge of the impeller. As the IGV stagger angle increases, the mass flow decreases to maintain a given inlet flow angle. Therefore, the onset of the rotating instabilities is delayed towards lower mass flow rates.

Figure 1 : Cartes compresseur en fonction du calage de l’IGV

Figure 2 : Lien entre l’apparition des instabilités tournantes et angle relatif en tête en entrée de rouet

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