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Etude phénoménologique du décrochage dynamique sur un rotor d'hélicoptère en vol d'avancement

Abstract : Dynamic stall occurs on helicopter rotors at high-thrust or high-speed forward flight. It induces large dynamic loads variations and vibrations, limiting the flight envelope. The objective of the present work is to use fluid/structure coupling computations to identify the mechanisms that trigger dynamic stall in rotor environment at high-thrust forward flight. First, experimental databases from ONERA have been evaluated, reinforced by low fidelity simulations, to select test cases undergoing stall events at different flight conditions and with different blade geometries. The analysis of the selected test cases has been made using a coupling procedure between the aerodynamic solver elsA and the comprehensive analysis code HOST. Post-processing tools have been developed and massively used to identify and characterize the flow-separation areas on the rotor-disk and the possible triggers of these flow-separations. Several flow-separation regions have been identified on the rotor-disk in the selected test cases. A subsonic separated flow has been observed in the third quadrant, which is influenced by the blade-vortex interaction occurring in this area. Shock-wave induced separations influenced by the blade elastic response have been observed at the end of the fourth quadrant and beginning of the first one. An investigation of these different mechanisms of dynamic stall, notably the blade vortex interaction, has been led by isolating the mechanisms. Therefore, simplified simulations on a single non-rotating blade have been run with and without the blade-vortex interaction. These computations show that the blade-vortex interaction plays an important part in triggering dynamic stall in several forward flight conditions.
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https://hal.archives-ouvertes.fr/tel-03462239
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Submitted on : Wednesday, March 17, 2021 - 10:00:06 AM
Last modification on : Monday, December 13, 2021 - 9:17:20 AM
Long-term archiving on: : Monday, June 21, 2021 - 8:56:22 AM

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DAAA21023.1615366461.pdf
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  • HAL Id : tel-03462239, version 1

Citation

Camille Castells. Etude phénoménologique du décrochage dynamique sur un rotor d'hélicoptère en vol d'avancement. Sciences de l'ingénieur [physics]. SORBONNE UNIVERSITE, 2020. Français. ⟨tel-03462239v1⟩

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