Peening coated internal surfaces of turbomachine components
AssigneeGeneral Electric Company
InventorsArthur S. Peck, Gabriel DellaFera, Paul Stephen Dimascio, Jon Conrad Schaeffer
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Abstract
A method of treating a substrate of a turbomachine component includes applying a coating to a surface of the substrate of the turbomachine component and peening the substrate after applying the coating to the surface by directing a peening force onto the coating whereby the peening force on the coating is transferred through the coating to the substrate. A method of treating an internal surface of a turbomachine component includes directing a peening force at the internal surface within a cooling passage of the turbomachine component.
Claims20
A method of treating a substrate of a rotor blade for a turbomachine, the method comprising:
- applying a coating to a surface of the substrate of the rotor blade, wherein the rotor blade is hollow and the surface is an internal surface of a cooling passage of the rotor blade;
- applying a mask within the cooling passage at a location generally radially aligned with a platform of the rotor blade;
- and
- peening the internal surface of the rotor blade after applying the coating to the internal surface by directing a peening force onto the coating whereby the peening force on the coating is transferred through the coating to the substrate and whereby the substrate exhibits residual compressive stress from the peening force transferred through the coating to the substrate, wherein the peening force is an impact force of a peening media, whereby the peening media is obstructed by the mask from entering a portion of the cooling passage within an airfoil portion of the rotor blade during peening, wherein peening the substrate comprises shot peening the substrate using a lance to direct the peening media onto the coating.
A method of treating a rotor blade for a turbomachine, the method comprising:
- applying a mask within a cooling passage defined within the rotor blade at a location generally radially aligned with a platform of the rotor blade;
- directing a peening force at a coating on an internal surface of the cooling passage;
- and
- whereby the peening force is transferred through the coating to the internal surface and whereby the internal surface exhibits residual compressive stress from the peening force transferred through the coating, wherein the peening force is an impact force of a peening media on the coating, and wherein the peening media comprises shot and directing the peening force at the coating on the internal surface comprises directing the peening media at the internal surface using a lance, whereby the peening media is obstructed by the mask from contacting a portion of the cooling passage within the airfoil portion of the rotor blade while directing the peening media at the coating on the internal surface.
Dependencies are inferred from the claim text.