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Characterization of a Three-Dimensional Leading-Edge Separation Bubble on Swept, Low Aspect-Ratio Propeller Blades

[+] Author Affiliations
Ye-Bonne Koyama Maldonado

Safran Aircraft Engines / ONERA The French Aerospace Lab, Moissy-Cramayel, France

Gregory Delattre, Cedric Illoul, Laurent Jacquin

ONERA-The French Aerospace Lab, Meudon, France

Clement Dejeu

Safran Aircraft Engines, Moissy-Cramayel, France

Paper No. GT2017-64545, pp. V001T01A027; 15 pages
  • ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition
  • Volume 1: Aircraft Engine; Fans and Blowers; Marine; Honors and Awards
  • Charlotte, North Carolina, USA, June 26–30, 2017
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-5077-0
  • Copyright © 2017 by ASME


Leading-edge vortex flows are often present on propeller blades at take-off, however, their characteristics and aerodynamic impact are still not fully understood. An experimental investigation using Time Resolved Particle Image Velocimetry (TR-PIV) has been performed on a model blade in order to classify this flow with respect to both delta wing leading-edge vortices and the low Reynolds number studies regarding leading-edge vortices on rotating blades. A numerical calculation of the experimental setup has been performed in order to assess usual numerical methods for propeller performance prediction against TR-PIV results. Similar characteristics were found with non slender delta wing vortices at low incidence, which hints that the leading-edge vortex flow may generate vortex lift. The influence of rotation on the characteristics of the leading-edge vortex is compared to that of the pressure gradient caused by the circulation distribution. A discussion on the quality of the PIV reconstruction for close-wall structures is provided.

Copyright © 2017 by ASME



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