Method for repairing vane of gas turbine engine
A method for repairing a component of a gas turbine engine is provided. The method includes perforating apertures through a braze tape based on a shape of a degraded region of the component, and applying the braze tape to the component such that the braze tape covers the degraded region and the apertures surround a perimeter of the degraded region. The method also includes bonding the braze tape and the component via a thermal brazing treatment, and contouring the braze tape to conform to an original profile of the component based on monitoring depths of the apertures.
1 . A method for repairing a component of a gas turbine engine, the method comprising:
perforating apertures through a braze tape based on a shape of a degraded region of the component;
applying the braze tape to the component such that the braze tape covers the degraded region and the apertures surround a perimeter of the degraded region;
bonding the braze tape and the component via a thermal brazing treatment; and
contouring the braze tape to conform to an original profile of the component based on monitoring depths of the apertures.
2 . The method of claim 1 , further comprising:
sizing and cutting the braze tape to cover the degraded region.
3 . The method of claim 1 , further comprising:
applying a braze-resist coating to interior surfaces of the apertures to block migration of a braze alloy of the braze tape into to the apertures during the thermal brazing treatment.
4 . The method of claim 3 , wherein the braze tape comprises a diffusion braze tape, and bonding the braze tape and the component via the thermal brazing treatment comprises:
heating the diffusion braze tape and the component to a brazing temperature to diffuse the braze alloy into the component; and
cooling the diffusion braze tape and the component from the brazing temperature to an ambient temperature.
5 . The method of claim 1 , wherein, in applying the braze tape, the apertures overlie an undamaged surface of the component.
6 . The method of claim 5 , wherein contouring the braze tape comprises:
grinding excess material from the braze tape based on the original profile of the component while monitoring the depths of the apertures; and
ceasing the grinding based on an increased exposure of the undamaged surface of the component at locations of the apertures.
7 . The method of claim 6 , wherein contouring the braze tape further comprises:
blending a ground area of the braze tape between the locations of the apertures to restore the original profile of the component.
8 . The method of claim 1 , wherein perforating the apertures comprises:
determining a number of the apertures based on the shape of the degraded region.
9 . The method of claim 8 , wherein the number of the apertures correlates with a magnitude of curvature variation in the shape of the degraded region.
10 . The method of claim 1 , wherein the component comprises a vane of the gas turbine engine or an airfoil of the vane.
11 . A method for repairing a component of a gas turbine engine, the method comprising:
perforating apertures through a braze tape based on a shape of a degraded region of the component;
applying the braze tape to the component such that the braze tape covers the degraded region and the apertures overlie an undamaged surface of the component;
bonding the braze tape and the component;
grinding excess material from the braze tape based on an original profile of the component while monitoring depths of the apertures; and
ceasing the grinding based on an increased exposure of the undamaged surface of the component at locations of the apertures.
12 . The method of claim 11 , further comprising:
sizing and cutting the braze tape to cover the degraded region.
13 . The method of claim 11 , further comprising:
applying a braze-resist coating to interior surfaces of the apertures to block migration of a braze alloy of the braze tape into to the apertures during bonding.
14 . The method of claim 13 , wherein the braze tape comprises a diffusion braze tape, and bonding the braze tape and the component comprises:
heating the diffusion braze tape and the component to a brazing temperature to diffuse the braze alloy into the component; and
cooling the braze tape and the component from the brazing temperature to an ambient temperature.
15 . The method of claim 11 , further comprising:
blending a ground area of the braze tape between the locations of the apertures to restore the original profile of the component.
16 . The method of claim 11 , wherein perforating the apertures comprises:
determining a number of the apertures based on the shape of the degraded region.
17 . The method of claim 16 , wherein the number of the apertures correlates with a magnitude of curvature variation in the shape of the degraded region.
18 . The method of claim 11 , wherein the component comprises a vane of the gas turbine engine or an airfoil of the vane.
19 . The method of claim 11 , wherein the degraded region comprises a thermally degraded region.
20 . A method for repairing a component of a gas turbine engine, the method comprising:
perforating apertures through a braze tape based on a shape of a degraded region of the component;
applying the braze tape to the component such that the braze tape covers the degraded region;
applying a braze-resist coating to interior surfaces of the apertures;
bonding the braze tape and the component via a thermal brazing treatment, wherein the braze-resist coating blocks migration of a braze alloy of the braze tape into the apertures; and
contouring the braze tape to conform to an original profile of the component based on monitoring depths the apertures.