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US 12,624,640 B2Granted
Turbine engine element comprising at least one blade obtained by additive manufacturing
AssigneeSafran Helicopter Engines
InventorsSylvain Pierre Votie, Denis Daniel Jean Boisseleau, Xavier Roger Betbeder-Laüque
Life of this patent
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Abstract
The present invention relates to a turbomachine element (1), comprising at least one blade (2) obtained by additive manufacturing, the blade (2) having a skin (4) and an internal lattice (6) allowing air circulation in the blade (2) and having an additive manufacturing support function for the skin (4).
Claims11
A turbine engine element,
- the turbine engine element comprising at least one blade obtained by additive manufacturing, the at least one blade comprising:
- a skin;
- and
- an internal lattice comprising a mesh formed by a network of solid structures and empty regions connected together and arranged in a closed pattern to form a grid,
- the lattice being configured for allowing air circulation in the blade and for supporting the skin during the additive manufacturing, wherein
- the at least one blade further comprises at least one insert positioned in the lattice, and
- the lattice further comprises an inner portion and an outer portion, separated by the insert.
4 more elements
Dependencies are inferred from the claim text.