Blades and vanes for gas turbine engines and the manufacture thereof
AssigneeROLLS-ROYCE plc
InventorBrynley CLARK
Life of this patent
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Abstract
A method of forming a blade or vane for a gas turbine engine comprising: attaching a first outer layer to a first two-dimensional array of attachment areas on a first surface of an intermediate layer; attaching a second outer layer to a second two-dimensional array of attachment areas on a second surface of the intermediate layer opposite the first surface; and increasing a separation between at least a portion of the first and second outer layer to thereby deform the intermediate layer into a corrugated structure having corrugations in first and second directions.
Claims20
A method of forming a blade or vane for a gas turbine engine comprising:
- attaching a first outer layer to a first two-dimensional array of attachment areas on a first surface of an intermediate layer;
- attaching a second outer layer to a second two-dimensional array of attachment areas on a second surface of the intermediate layer opposite the first surface;
- and
- increasing a separation between at least a portion of the first and second outer layer to thereby deform the intermediate layer into a corrugated structure having corrugations in first and second directions.
A blade or vane for a gas turbine engine comprising:
- a first outer layer;
- a second outer layer;
- and
- a corrugated structure formed between the first and second outer layers, the corrugated structure being attached to the first outer layer at a first two-dimensional array of attachment areas and attached to the second outer layer at a second two-dimensional array of attachment areas such that corrugations of the corrugated structure extend in two directions.
Dependencies are inferred from the claim text.