Method for producing surface coatings on components

Abstract

A method for producing surface coatings on gas turbine components and/or for measuring abrasive material residues on gas turbine components, including: -abrasively blasting a surface of the component using an abrasive material, a portion of this abrasive material remaining on or in this surface of the component; -detecting abrasive material which has remained on or in the surface of the component; and -applying a coating to the surface of the component is disclosed.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

An exemplary embodiment is clarified in the following with reference to the figure:

FIG. 1: shows in a schematic view the steps of an exemplary method in accordance with the present invention.

DETAILED DESCRIPTION

As mentioned, FIG. 1 shows the steps of an exemplary method according to the present invention which, in this case, is a method for producing surface coatings on gas turbine components, in particular gas turbine components of aircraft engines, and for measuring abrasive material residues at or on gas turbine components, in particular gas turbine components of aircraft engines.

In step 10, a surface of the gas turbine component is abrasively blasted using an abrasive material, a portion of this abrasive material remaining on or in this surface of the component. In this context, an abrasive material is used which, in comparison to the material or base material of the gas turbine component, absorbs or reflects electromagnetic radiation in defined spectral regions in a different manner or at a different intensity.

In step 12, abrasive material is detected which has remained on or in the surface of the gas turbine component. For this purpose, the particular or previously abrasively blasted surface or surface section of the gas turbine component is irradiated with electromagnetic radiation, either abrasive material particles, which have remained on or in the surface of the gas turbine part, being individually detected at a geometrically high resolution, and the surface-area proportion being determined, or the integral change in the reflectivity and/or emissivity being recorded.

In step 14, a coating is applied to the surface of the gas turbine component, in particular to the surface of the gas turbine component previously abrasively blasted using the abrasive material. The coating is applied in a thermal spray-coating process.

It may be provided, however, for this coating process to only be carried out in step 14 when it has been previously verified and determined whether, respectively, that the abrasive material on or in the surface of the gas turbine component, respectively its (surface-area) proportion relative to this surface is smaller than a predefined limit.

As clarified, in particular, by the exemplary embodiment, the present invention provides the basis for a multiplicity of advantages, some of which are named in the following, it being noted that not all of the exemplary embodiments which come under the present invention need feature the or all of these advantages. By employing (the design approach in accordance with the exemplary embodiment of) the method according to the present invention, abrasive media residues are quantitatively determined. In contrast to previously known designs, it is possible to inspect the component to be coated, respectively the gas turbine component. In addition, a rapid, contactless measurement of the abrasive media residues (also described here as abrasive material residues) is made possible. The need for ground specimens is eliminated; the quality is known immediately following the abrasive blasting

LIST OF REFERENCE NUMERALS

• • 10 abrasively blast surface
  • 12 detect abrasive material
  • 14 apply coating

Claims

1. A method for producing surface coatings on components and/or for measuring abrasive material residues on components comprising the steps of: abrasively blasting a surface of the component using an abrasive material, a portion of the abrasive material remaining on or in the surface of the component;detecting abrasive material remaining on or in the surface of the component; and if the abrasive material is detected,applying a coating to the surface of the component.

2. The method as recited in claim 1 wherein the detecting step is a contactless process.

3. The method as recited in claim 1 wherein the detecting step is a nondestructive process.

4. The method as recited in claim 1 wherein the detecting step includes applying radiation to the blasted surface of the component.

5. The method as recited in claim 4 wherein the radiation is light radiation or infrared radiation.

6. The method as recited in claim 4 wherein the detecting step includes individually detecting particles of the abrasive material at a geometrically high resolution.

7. The method as recited in claim 1 wherein the detecting step includes determining or measuring a surface-area proportion of the abrasive material remaining on or in the surface of the component.

8. The method as recited in claim 1 wherein the detecting step includes measuring or recording an integral change in the reflectivity and/or emissivity in the region of the abrasively blasted surface of the component.

9. The method as recited in claim 1 wherein the applying step occurs only coating only when an amount or proportion of the abrasive material remaining on or in the surface of the component is smaller than a predefined limit.

10. The method as recited in claim 1 wherein the applying step includes a thermal spray-coating process.

11. The method as recited in claim 1 wherein the component is a gas turbine component.

12. The method as recited in claim 1 wherein the gas turbine component is an aircraft engine gas turbine component.