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US 2014/0112797 A1Published application
Blade for a thermal turbomachine
AssigneeSiemens Aktiengesellschaft
InventorDetlef Haje
Life of this patent
Estimating the term…
Abstract
A blade for a thermal turbomachine is provided. The blade has a blade airfoil having a first extent in a substantially radial orientation in relation to a rotational axis of the turbomachine and a second extent which is configured transversely with respect to the first extent, and comprising a blade root which adjoins the rotor blade and rounds off the rotor blade in the first extent. The blade has graphene at least in regions. A method for producing a blade of this type is also provided.
Claims16
A blade for a thermal turbomachine, comprising
- a blade airfoil with a first extent in a substantially radial orientation in relation to a rotational axis of the turbomachine and a second extent, which is formed transversely to the first extent, and comprising a blade root, which adjoins the blade airfoil and terminates the blade airfoil in the first extent, wherein the blade comprises graphene at least in some region or regions.
A method for producing a blade for a thermal turbomachine, comprising
- providing a blade airfoil with a first extent in a substantially radial orientation in relation to a rotational axis of the turbomachine and a second extent, which is formed transversely to the first extent, and a blade root, which adjoins the blade airfoil and terminates the blade airfoil in the first extent,
- furnishing the blade with graphene at least in some region or regions.
Dependencies are inferred from the claim text.