Substrate Edge Configurations for Ceramic Coatings

Patent metadata

Field	Value
Publication number	US-2024254889-A1
Application number	US-202418596421-A
Country	US
Kind code	A1
Filing date	Mar 5, 2024
Priority date	Nov 8, 2018
Publication date	Aug 1, 2024
Grant date	—

Abstract

An article has a body having: a first face; and a first bevel surface extending from the first face. A plurality of first channels along the first bevel surface extending from the first face. A ceramic coating is along the inner diameter surface and the first bevel surface.

First claim

What is claimed is:

1 . An article comprising:
a body having:
a first face; and
a first bevel surface extending from the first face; and
a plurality of first channels along the first bevel surface extending from the first face; and
a ceramic coating along the first face and the first bevel surface.

2 . The article of claim 1 being a gas turbine engine component.

3 . The article of claim 1 wherein:
the ceramic coating comprises a stabilized zirconia.

4 . The article of claim 1 wherein:
the body is metallic.

5 . The article of claim 4 wherein:
the body comprises a metallic substrate and a metallic bondcoat.

6 . The article of claim 5 wherein:
the metallic substrate is a nickel-based superalloy; and
the ceramic coating comprises a stabilized zirconia.

7 . The article of claim 1 wherein:
the body has:
a plurality of first recesses in a pattern along the first face;

the first channels comprise a first group of channels and a second group of channels:
the channels of the first group being of different size than the channels of the second group; and
the channels of the first group being of different registry with the pattern than are the channels of the second group.

8 . The article of claim 7 wherein:
the pattern is a hexagonal array; and
the hexagonal array has a first row along the first bevel surface;
the channels of the first group are longer than the channels of the second group;
the channels of the first group are in-phase with the recesses of the first row; and
the channels of the second group are out-of-phase with the recesses of the first row.

9 . The article of claim 1 being a blade outer airseal wherein:
the first face is a transversely concave inner diameter surface;
the body comprises:
a first circumferential end;
a second circumferential end;
a first axial end;
a second axial end;
said first bevel between the first circumferential end and the inner diameter surface;
a second bevel between the second circumferential end and the inner diameter surface;
said plurality of first channels along the first bevel extending from the inner diameter surface to the first circumferential end; and
a plurality of second channels along the second bevel extending from the inner diameter surface to the second circumferential end; and

said ceramic coating along the inner diameter surface, the first bevel surface, and the second bevel surface.

10 . The blade outer airseal of claim 9 wherein:
the body has:
a plurality of first recesses along the inner diameter surface.

11 . The blade outer airseal of claim 9 wherein:
the ceramic has a by weight majority of at least one of YSZ and GSZ.

12 . A gas turbine engine including a plurality of articles of claim 1 in a circumferential array.

13 . The gas turbine engine of claim 12 further comprising:
a blade stage encircled by the circumferential array.

14 . The gas turbine engine of claim 12 wherein:
the gas turbine engine has a gaspath; and
the first bevel is at an upstream end of the body along the gaspath.

15 . The gas turbine engine of claim 12 wherein:
the first bevel is at first circumferential end of the body; and
the body has a second circumferential end and a second bevel extending from the first face to the second circumferential end.

16 . A method for manufacturing the article of claim 1 , the method comprising:
machining the first channels in the body; and applying the coating.

17 . The method of claim 16 further comprising:
grinding the coating to remove artifacts of the first channels.

18 . The method of claim 16 further comprising machining each of the first channels by:
plunging a rotating bit into the first surface; and
drawing the rotating bit down the bevel surface.

19 . The method of claim 18 wherein the machining each of the first channels further comprises:
between the plunging and the drawing, turning the bit transverse to its rotation.

20 . A blade outer airseal comprising:
a body having:
a transversely concave inner diameter surface;
a first circumferential end;
a second circumferential end;
a first axial end;
a second axial end;
a first bevel between the first circumferential end and the inner diameter surface;
a second bevel between the second circumferential end and the inner diameter surface;
a plurality of first recesses along the inner diameter surface;
a plurality of first channels along the first bevel extending from the inner diameter surface to the first circumferential end; and
a plurality of second channels along the second bevel extending from the inner diameter surface to the second circumferential end; and
a ceramic coating along the inner diameter surface, the first bevel surface, and the second bevel surface.

Assignees

• Rtx Corp

Inventors

• Strock Christopher W

Classifications

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title

• B23P15/04

  turbine or like blades from several pieces · CPC title

• F05D2230/14

  Micromachining · CPC title

• F05D2250/191

  perforated · CPC title

• F05D2250/192

  bevelled · CPC title