PhD defense : Maxime FIORE – Influence of inter-disc cavity flow on turbine aerodynamics
In order to deal with high temperatures encountered by the components downstream of the combustion chamber, some relatively cold air is bled at the compressor.
This air feeds the cavities underneath the turbine main annulus and cool down the rotor disks ensuring a proper and safe operation of the turbine. This thesis manuscript introduces a numerical study of the effect of the cavity flow close to the turbine hub on its aerodynamic performance. The interaction phenomena between the cavity and main annulus flow are not currently fully understood. The study of these phenomena is performed based on different numerical approaches (RANS, LES and LES-LBM) applied to two configurations for which experimental results are available. A linear cascade configuration with upstream cavity and various rim seal geometries (interface between rotor and stator platform) and cavity flow rate available. A rotating configuration that is a two stage turbine including cavities close to realistic industrial configurations. Additional losses incurred by cavity flow are measured and studied using a method based on exergy (energy balance in the purpose to generate work).
Paul Tucker University of Cambridge Referee
Vittorio Michelassi BAKER HUGHES (GE) Referee
Isabelle Trébinjac Ecole Centrale Lyon Member
Jean-François Boussuge CERFACS Member
Eric Lippinois Safran Aircraft Engine Member
Nicolas Gourdain ISAE Advisor
Pierre Ginibre Safran Aircraft Engine Invited
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