초록 ▼

A metallic component, which may be an airfoil, includes at least one treated patch, wherein the entire thickness of the component within the treated patch is in a state of residual compressive stress. A surface-treated area overlaps at least a boundary between the treated patch and the remainder of

A metallic component, which may be an airfoil, includes at least one treated patch, wherein the entire thickness of the component within the treated patch is in a state of residual compressive stress. A surface-treated area overlaps at least a boundary between the treated patch and the remainder of the component. The surface of the component within the surface-treated area is in a state of residual compressive stress, so as to resist crack initiation at the boundary between the treated patch and the remainder of the component. A method is also provided for making such a component.

대표청구항 ▼

What is claimed is: 1. A metallic component, comprising: at least one treated patch, wherein a majority of the thickness of said component within said treated patch is in a state of residual compressive stress applied by a low plasticity burnishing process; and a surface-treated area, said surface-

What is claimed is: 1. A metallic component, comprising: at least one treated patch, wherein a majority of the thickness of said component within said treated patch is in a state of residual compressive stress applied by a low plasticity burnishing process; and a surface-treated area, said surface-treated area overlapping at least a boundary between said treated patch and the remainder of said component, wherein the surface of said component within said surface-treated area is in a state of residual compressive stress applied by a mechanical peening process, so as to resist crack initiation at said boundary between said treated patch and the remainder of said component. 2. The metallic component of claim 1 wherein said component is bounded by at least one peripheral edge, and said treated patch is disposed adjacent to said peripheral edge. 3. The metallic component of claim 1 wherein said surface-treated area covers substantially all of the external surface of said component. 4. A metallic airfoil for a gas turbine engine, comprising: a root spaced apart from a tip, spaced-apart leading and trailing edges, a suction side extending from said leading edge to said trailing edge, and an opposed pressure side extending from said leading edge and said trailing edge, wherein a thickness of said airfoil is defined between said pressure side and said suction side; at least one treated patch, within which substantially the entire thickness of said airfoil is under residual compressive stress applied by a low plasticity burnishing process; and a surfaced-treated area within which the surface of said airfoil is under residual compressive stress applied by a mechanical peening process, said surface-treated area overlapping at least a boundary between said treated patch and the remainder of said airfoil. 5. The metallic airfoil of claim 4 wherein said treated patch is disposed adjacent to a selected one of said leading edge, said trailing edge, or said tip, such that said treated patch is adapted to resist the growth of cracks propagating from said selected leading edge, said trailing edge, or said tip, respectively. 6. The metallic airfoil of claim 5 wherein said surface-treated area covers substantially all of said pressure side and said suction side. 7. The metallic airfoil of claim 4 wherein said treated patch is disposed adjacent said tip. 8. A method of reducing crack propagation in metallic components, comprising: providing a metallic component having an external surface, said component including at least one crack-prone area and defining a thickness; creating at least one treated patch which covers said crack-prone area, wherein a majority of the thickness of said component within said treated patch is left a state of residual compressive stress applied by a low plasticity burnishing process; and creating a surface-treated area on said external surface of said component which overlaps at least a boundary between said treated patch and the remainder of said component; whereby crack initiation at the boundary between said treated patch and the remainder of said component is resisted by residual compressive stresses on said external surface produced by applying a mechanical peening process to said surface-treated area. 9. The method of claim 8 wherein said step of creating a surface-treated area comprises applying glass-bead peening to a selected portion of said external surface. 10. The method of claim 8 wherein said component is bounded by at least one peripheral edge, and said crack-prone area is disposed adjacent said peripheral edge. 11. The method of claim 8 wherein said surface-treated area covers substantially all of said external surface of said component.