Turbine engine erosion coating repair
A patch has: a silicone body; a primer on an underside of the body; a silicone adhesive on the primer; and a release strip on the adhesive. The body has a plurality of perforations.
1 . A patch comprising:
a silicone body;
a silane primer on an underside of the body;
a silicone adhesive on the primer;
a first release strip on the silicone body; and
a second release strip on the adhesive,
wherein:
the adhesive is a peroxide-cured silicone; and
the body has a plurality of perforations.
2 . The patch of claim 1 wherein:
the perforations only partially penetrate the body.
3 . The patch of claim 2 wherein:
a density of the perforations is 2.0 perforations to 10.0 perforations per square centimeter.
4 . The patch of claim 3 wherein:
the first and second release strips are coated fabric.
5 . The patch of claim 2 wherein:
the first and second release strips are coated fabric.
6 . The patch of claim 5 wherein:
a density of the perforations is 2.0 perforations to 10.0 perforations per square centimeter.
7 . The patch of claim 2 wherein:
the perforations penetrate at least 50% of a thickness of the silicone patch material.
8 . The patch of claim 7 wherein:
the first and second release strips are coated fabric.
9 . The patch of claim 8 wherein:
a density of the perforations is 2.0 perforations to 10.0 perforations per square centimeter.
10 . The patch of claim 7 wherein:
a density of the perforations is 2.0 perforations to 10.0 perforations per square centimeter.
11 . The patch of claim 1 wherein:
the perforations penetrate at least 50% of a thickness of the silicone patch material.
12 . The patch of claim 11 wherein:
the first and second release strips are coated fabric.
13 . The patch of claim 12 wherein:
a density of the perforations is 2.0 perforations to 10.0 perforations per square centimeter.
14 . A method for patching a damaged polymeric erosion coating on a gas turbine engine component using the patch of claim 1 , the method comprising:
removing a portion of the coating around a damage site;
priming the component;
removing the second release strip to expose the adhesive;
applying the patch so that the adhesive contacts the component; and
rolling the patch with a roller.
15 . The method of claim 14 wherein:
the priming is with a silane primer.
16 . The method of claim 14 further comprising:
applying pressure to the patch; and
heating the patch while the pressure is applied.
17 . The method of claim 14 wherein:
the method is performed in situ with the engine on an aircraft.
18 . The method of claim 14 wherein:
the damage site is along a leading edge of a fan inlet strut or fan exit strut.
19 . The method of claim 14 wherein:
the damage site has a polymer matrix composite substrate.
20 . A method for manufacturing the patch of claim 1 , the method comprising:
forming the silicone body on a first release ply for forming the first release strip and at least partially curing the silicone body on the first release ply;
perforating the silicone body to form the perforations;
applying the adhesive to a second release ply for forming the second release strip;
applying the peroxide-cured primer to the perforated silicone body; and
marrying the primed perforated silicone body to the adhesive.