Airfoil with leading edge protector for a fan assembly
AssigneeGeneral Electric Company
InventorsLeonardo Ajdelsztajn, Jeffrey Jon Schoonover
Life of this patent
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Abstract
An airfoil for an aircraft engine includes a blade body and a leading edge protector operably coupled to the blade body. The leading edge protector includes a preformed sheet defining a nose portion and two flange portions. The nose portion and the flange portions are arranged in the chordwise direction. The preformed sheet further defines a defined point located on the nose portion. An X-axis and a Y-axis are defined relative to the defined point. A deposit is operably coupled with the nose portion of the preformed sheet and extends from the nose portion along the flange portions on opposing sides of the defined point in the X-axis direction.
Claims26
An airfoil for an aircraft engine, the airfoil defining a chordwise direction, the airfoil comprising:
- a blade body;
- and
- a leading edge protector operably coupled to the blade body, the leading edge protector comprising:
- a preformed sheet defining a nose portion and two flange portions, wherein the nose portion and the flange portions are arranged along the chordwise direction, the preformed sheet further defining a defined point located on the nose portion, wherein an X-axis and a Y-axis are defined relative to the defined point;
- and
- a deposit operably coupled with the nose portion of the preformed sheet and extending from the nose portion and along the flange portions on opposing sides of the defined point in the X-axis direction.
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Dependencies are inferred from the claim text.