Propeller ring made of composite material for a turbomachine
AssigneeSafran Aircraft Engines
InventorsSebastien Emile Philippe Tajan, Charles-Henri Michel Marie Derrez, Anthony Lafitte, Cyril Roger Yves Le Pecheur
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Abstract
A propeller ring of a turbomachine including an annular body substantially coaxial to a principal axis and a plurality of radial housings uniformly distributed about the principal axis, each radial housing being configured to receive a root of a blade, the annular body being made of composite material including a fibrous reinforcement densified by a polymer matrix and further including a plurality of metallic inserts configured to each receive the root of a blade, said metallic inserts being anchored in the composite material of the annular body.
Claims15
A propeller ring of a turbomachine comprising:
- an annular body coaxial to a principal axis and made of a composite material including a fibrous reinforcement densified by a polymer matrix;
- a plurality of radial housings uniformly distributed about the principal axis, each radial housing being configured to receive a root of a blade of variable pitch;
- and
- a plurality of metallic inserts each configured to receive the root of the blade of variable pitch, the plurality of metallic inserts being anchored in the composite material of the annular body and including an annular protuberance embedded in the composite material of the annular body, wherein at least one of the plurality of metallic inserts is a cylinder of revolution or conical, and has a geometry enabling the metallic inserts to be attached directly to the annular body and to be held inside the annular body by contact pressure.
A propeller ring of a turbomachine comprising:
- an annular body coaxial to a principal axis and made of a composite material including a fibrous reinforcement densified by a polymer matrix, the annular body including a plurality of radial housings and a plurality of metallic inserts, wherein
- the plurality of radial housings is uniformly distributed about the principal axis, each radial housing being configured to receive a root of a blade of variable pitch, and
- each of the plurality of metallic inserts including an annular protuberance embedded in the composite material of the annular body is configured to receive the root of the blade of variable pitch and anchored in the composite material of the annular body and, wherein at least one of the plurality of metallic inserts is a cylinder of revolution or conical, and has a geometry enabling the metallic inserts to be attached directly to the annular body and to be held inside the annular body by contact pressure, wherein a thickness of the annular protuberance at a radially outer part of the at least one of the plurality of metallic inserts is greater than the thickness at a radially inner part of the annular body, opposite the radially outer part of the at least one of the plurality of metallic inserts.
Dependencies are inferred from the claim text.