Fan blade with root through holes
AssigneeUnited Technologies Corporation
InventorCharles H. Roche
Life of this patent
Estimating the term…
Abstract
A lightweight fan blade for use in turbofan gas turbine engines is disclosed. The fan blade includes a metallic airfoil connected to a root. The airfoil has a pressure side and a suction side. The suction side of the airfoil includes one or more cavities for weight reduction purposes. A cover is attached to the suction side of the body to cover or enclose the one or more cavities. In addition to the one or more cavities, through holes are formed from the inner face of the root into one or more of the cavities for further weight reduction. The through holes may be covered by a spacer and one or more through holes may be extended from the inner face of the root into each of the cavities.
Claims19
A fan blade comprising:
- an airfoil connected to a root;
- the airfoil including a pressure side and a suction side, the suction side including at least one cavity;
- at least one through hole extending through the root to the cavity;
- and
- a cover disposed over the cavity and adhered to the suction side of the airfoil.
A fan blade comprising:
- an airfoil connected to a root;
- the airfoil including a pressure side and a suction side, the suction side including at least one cavity;
- at least one through hole extending through the root to the cavity, wherein the root includes an inner face disposed between and connected to a pair of pressure faces that extend from the inner face to the airfoil;
- and
- the through hole extending from the inner face of the root to the cavity, wherein the through hole is plugged with a plug at the inner face.
A fan blade assembly comprising:
- a hub coupled to a plurality of radially outwardly extending fan blades, each fan blade including an airfoil connected to a root, the airfoil including a pressure side and a suction side;
- the suction side including at least one cavity;
- at least one through hole extending from the root to the cavity;
- and
- at least one hole that extends from the root into the airfoil but which terminates short of the cavity.
A method for fabricating a fan blade of a gas turbine engine, the method comprising:
- manufacturing a body including an airfoil connected to a root, the airfoil including a pressure side and a suction side, the suction side including at least one cavity;
- forming at least one through hole through the root and into the cavity;
- and
- covering the cavity with a cover.
Dependencies are inferred from the claim text.