Gas turbine engine components and methods for their manufacture using additive manufacturing techniques
AssigneeHoneywell International Inc.
InventorsDonald G. Godfrey, Mark C. Morris, Andy Szuromi
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Abstract
In accordance with an exemplary embodiment, a method for manufacturing a component using additive manufacturing techniques includes providing a 3D design model for the component, adding one or more crack resistant features to the 3D design model of the component to produce an enhanced design model, and manufacturing the component using an additive manufacturing technique in accordance with the enhanced design model. The one or more crack resistant features are provided to reduce or eliminate the incidence of cracking in the manufactured component.
Claims13
A method for manufacturing a metallic superalloy gas turbine engine component using additive manufacturing techniques, the method comprising the steps of:
- providing a 3D design model for the gas turbine engine component, the 3D design model comprising an airfoil portion and a base portion, wherein the base portion comprises an attachment surface to which the airfoil portion is attached;
- adding at least two crack resistant features to the 3D design model of the component to produce an enhanced design model, wherein the at least two crack resistant features are selected from two or more of the group consisting of:
- (a) a buttress having a first end and a second end, wherein the first end is connected to and metallurgically integral with the base portion, and wherein the second end is disconnected from the base portion,
- (b) a lattice structure that is connected to and metallurgically integral with the base portion, said lattice structure extending along one or more surfaces of the base portion, and
- (c) one or more holes that extend entirely through the base portion in a direction substantially parallel with the attachment surface;
- and
- manufacturing the gas turbine engine component using an additive manufacturing technique in accordance with the enhanced design model to form a manufactured gas turbine engine component,
- wherein the at least two crack resistant features are provided to reduce or eliminate the incidence of cracking in the manufactured gas turbine engine component.
A metallic superalloy gas turbine engine component manufactured using an additive manufacturing technique comprising:
- an airfoil portion;
- and
- a base portion having an attachment surface to which the airfoil portion is attached, wherein the base portion comprises at least two crack resistant features, the at least two crack resistant features being configured to reduce or eliminate the incidence of cracking in the manufactured gas turbine engine component, wherein the at least two crack resistant features are selected from two or more of the group consisting of:
- (a) a buttress having a first end and a second end, wherein the first end is connected to and metallurgically integral with the base portion, and wherein the second end is disconnected from the base portion,
- (b) a lattice structure that is connected to and metallurgically integral with the base portion, said lattice structure extending along one or more surfaces of the base portion, and
- (c) one or more holes that extend entirely through the base portion in a direction substantially parallel with the attachment surface.
Dependencies are inferred from the claim text.