Aeroacoustics of an axial ducted low Mach-number stage: numerical and experimental investigation

Miguel Pestana (1, 2) , Antonio A. Pereira (1) , Edouard Salze (1) , Johan Thisse (1, 2) , Marlène Sanjose (3) , Emmanuel Jondeau (1) , Pascal Souchotte (1) , Michel Roger (1) , Stéphane Moreau (3, 1) , Josselin Regnard (2) , Mathieu Gruber (2)

1 LMFA - Laboratoire de Mecanique des Fluides et d'Acoustique
2 Safran Aircraft Engines
3 UdeS - Université de Sherbrooke

This paper presents an experimental and numerical investigation of a ducted low-speed axial fan. The stator row is heterogeneous with 3 thickened vanes expected to have a non-negligible impact on the radiated noise. A good agreement for pressure ratio / mass flow rate characteristics is obtained between numerical and experimental results up to the onset of rotating stall. Hot-wire velocity profiles at the inlet assessed the effectiveness of a turbulence control screen added to prevent from inflow distortions. Induct acoustic measurements allowed a detailed description from wall-pressure spectra up to modal decompositions upstream and downstream of the fan. Acoustic modes were identified at the first two blade passing frequencies, which should be cut-off with a homogeneous stator row.

Domaines: Sciences de l'ingénieur [physics]; Acoustique [physics.class-ph]

Miguel Pestana, Antonio A. Pereira, Edouard Salze, Johan Thisse, Marlène Sanjose, et al.. Aeroacoustics of an axial ducted low Mach-number stage: numerical and experimental investigation. 23rd AIAA/CEAS Aeroacoustics Conference, Jun 2017, Denver, United States. ⟨10.2514/6.2017-3215⟩. ⟨hal-02407230⟩