Guide vane assembly for an aircraft turbine engine
AssigneeSafran Aircraft Engines
InventorRemi Merlin
Life of this patent
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Abstract
A guide vane assembly of an aircraft turbine engine, the guide vane assembly being segmented into a plurality of segments arranged circumferentially next to one another about an axis. The guide vane assembly includes two annular rings connected together by vanes and the geometry of the inner ring is modified to reduce the vibrational responses of the guide vane assembly.
Claims10
A guide vane assembly for an aircraft turbine engine, this guide vane assembly comprising two annular shells, an internal and an external respectively, extending around a common axis and connected together by blades, said internal shell having, in axial cross-section, an I shape and comprising two cylindrical walls, respectively internal and external, and connected to each other by an annular core, the guide vane assembly being sectorized and comprising a plurality of sectors arranged circumferentially next to each other about said axis, wherein each of the sectors comprises a core segment which comprises at least one concavity, corresponding to a variation of an axial position of the core segment along a longitudinal extent of each of the sectors, oriented in the axial direction.
Dependencies are inferred from the claim text.