Repairing a coating with a pre-configured coating patch

1. A method for repairing a component of an item of rotational equipment, the component including a coating and a component body, and the coating on the component body and including a defect, the method comprising:

arranging a first template with the component;

removing a portion of the coating from the component body thereby forming a coating aperture, the removed portion of the coating including the defect, wherein the portion of the coating is removed such that the coating aperture has a coating aperture configuration which substantially matches a first patch configuration of a first coating patch, wherein a first template aperture extends through the first template, wherein the first template aperture has a first template aperture configuration which substantially matches the first patch configuration, wherein the removing comprises removing the portion of the coating from the component body using the first template, and wherein the removing comprises abrasive wiping or media blasting the portion of the coating through the first template aperture;

preparing the component at the coating aperture to receive the first coating patch;

disposing the first coating patch within the coating aperture; and

attaching the first coating patch to the component body;

wherein the first coating patch has a thickness which is less than a thickness of the removed portion of the coating, and wherein an entirety of an exterior surface of the first coating patch is recessed inward from an exterior surface of coating adjacent the coating patch.

2. The method of claim 1 , wherein the portion of the coating is removed such that the coating aperture has a shape and a size which is the same as a shape and a size of the first coating patch, and the patch is pre-fabricated before performance of the method to have the size and the shape.

3. The method of claim 1 , wherein the item of rotational equipment is a gas turbine engine.

4. The method of claim 3 , wherein

the component is configured with the gas turbine engine during the removing, the disposing and the attaching; and

the gas turbine engine is configured on wing with an aircraft.

5. The method of claim 3 , wherein the component comprises a fan blade for the gas turbine engine.

6. The method of claim 3 , wherein the component comprises a guide vane for the gas turbine engine.

7. The method of claim 1 , wherein

the coating is an outer coating;

an intermediate coating is disposed between the outer coating and the component body; and

the first coating patch is disposed onto the intermediate coating.

8. The method of claim 1 , wherein the first coating patch is disposed directly onto the component body.

9. The method of claim 1 , further comprising:

selecting the first template from a group of available templates;

wherein a second template included in the group of available templates has a second template aperture with a second template aperture configuration which is different than the first template aperture configuration; and

wherein the first template is selected based on a configuration of the defect.

10. The method of claim 9 , further comprising:

selecting the first coating patch from a group of available coating patches;

wherein a second coating patch included in the group of available coating patches has a second patch configuration which is different than the first patch configuration; and

wherein the first coating patch is selected based on the selection of the first template.

11. The method of claim 1 , further comprising:

selecting the first coating patch from a group of available coating patches, wherein the first coating patch is selected based on a configuration of the defect; and

selecting the first template from a group of available templates, wherein the first template is selected based on the selection of the first coating patch;

wherein a second coating patch included in the group of available coating patches has a second patch configuration which is different than the first patch configuration;

wherein a second template included in the group of available templates has a second template aperture with a second template aperture configuration which is different than the first template aperture configuration.

12. The method of claim 1 , wherein the first coating patch is configured as a sticker.

13. The method of claim 1 , further comprising:

applying an adhesive to the first coating patch;

wherein the adhesive attaches the first coating patch to the component body.

14. The method of claim 1 , further comprising sealing a joint between the coating and the first coating patch with a sealing compound.

15. The method of claim 1 , wherein the coating comprises a first polymer material and the first coating patch comprises a second polymer material which is the same as the first polymer material.

16. A method for repairing an airfoil of an item of rotational equipment, the airfoil including a coating and an airfoil body, and the coating on the airfoil body and including a defect, the method comprising:

removing a portion of the coating from the airfoil body thereby forming a coating aperture by abrasive wiping or media blasting the portion of the coating through a first template aperture in a first template disposed next to the airfoil, the removed portion of the coating including the defect, wherein the portion of the coating is removed such that the coating aperture has a geometry that substantially matches, in shape and size, a geometry of a first coating patch;

disposing the first coating patch within the coating aperture; and

attaching the first coating patch to the airfoil body, wherein an entirety of an exterior surface of the first coating patch is recessed inward from an exterior surface of coating adjacent the coating patch.

17. The method of claim 1 , wherein the component body comprises fiber composite material and the coating comprises polymer material.

18. The method of claim 1 , wherein the first template comprises metal.

19. The method of claim 1 , wherein the first template comprises fiberglass composite material.

20. A method for repairing a component of an item of rotational equipment, the component including a coating and a component body, and the coating on the component body and including a defect, the method comprising:

removing a portion of the coating from the component body thereby forming a coating aperture by abrasive wiping or media blasting the portion of the coating through a first template aperture in a first template disposed next to the component, the removed portion of the coating including the defect, wherein the portion of the coating is removed such that a configuration of the coating aperture substantially matches a configuration of a first coating patch;

disposing the first coating patch within the coating aperture; and

attaching the first coating patch to the component body, wherein an entirety of an exterior surface of the first coating patch is recessed inward from an exterior surface of coating adjacent the coating patch.