Experimental validation of a corner stall control methodology using parametrised guide fins

Corner separation is known to limit the operability of aeronautical compressors. Dedicated control devices such as guide fins are envisioned reduce its negative effects. This paper presents a methodology based on RANS (Reynolds- Averaged Navier-Stokes) computations enabling select efficient for that purpose. applied reference case linear compressor cascade operating at low Mach number (~0.11). A set 17 parameters used define two design spaces interest, from which generated. From then, an automated process generates and merges unstructured mesh built around each fin with fixed, structured representing single channel cascade. Finally, results resulting hybrid obtained using Computational Fluid Dynamics solver elsA. up has proven successful in evaluating automatically hundreds various shapes. Several geometries illustrate diversity space. selection then evaluated experimentally. Evolutions losses downstream compared their respective predictions, without fin. These experimental validate implemented show encouraging terms loss redistribution brought by device.