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US 10,539,027 B2Granted
Gas turbine engine
AssigneeROLLS-ROYCE plc
InventorsSimon Read, Steven A Radomski
Life of this patent
Estimating the term…
Abstract
A blade or a vane for a gas turbine engine. The blade or vane having an aerofoil and a leading edge member attached to the aerofoil. The leading edge has an electrically conductive support member and a nano-coating formed on the support member.
Claims15
A blade or a vane for a gas turbine engine, the blade or vane comprising:
- an aerofoil;
- and
- a leading edge member attached to the aerofoil;
- wherein the leading edge member comprises a plurality of electrically conductive support members and a nano-crystalline metallic layer formed on the plurality of electrically conductive support members,
- wherein the leading edge member defines a general shape of a leading edge of the blade or vane, and the aerofoil defines a general shape of a remainder of the blade or vane,
- wherein the nano-crystalline metallic layer extends from a forward portion of the leading edge member to form first and second wings, the first wing extending a greater distance from the leading edge member toward a trailing edge of the aerofoil than does the second wing, and
- wherein each electrically conductive support member of the plurality of electrically conductive support members has a surface coated with the nano-crystalline metallic layer, the plurality of electrically conductive support members arranged to be stacked in a chordwise or in a spanwise direction.
4 more elements
A method of manufacturing a blade or vane, the method comprising:
- providing an aerofoil body;
- providing a plurality of electrically conductive support members each having a surface coated with a nano-crystalline metallic layer, wherein the plurality of electrically conductive support members are arranged to be stacked in a chordwise or in a spanwise direction;
- electroplating the plurality of electrically conductive support members to form a leading edge member;
- and
- bonding the leading edge member to the aerofoil body.
2 more elements
A blade or a vane for a gas turbine engine, the blade or vane comprising:
- an aerofoil;
- and
- a leading edge member attached to the aerofoil;
- wherein the leading edge member comprises a plurality of electrically conductive support members and a nano-crystalline metallic layer formed on the plurality of electrically conductive support members,
- wherein each of the plurality of electrically conductive support members has a surface coated with the nano-crystalline metallic layer, and
- wherein the plurality of electrically conductive support members are arranged to be stacked in a chordwise or a spanwise direction.
3 more elements
Dependencies are inferred from the claim text.