Substrate edge configurations for ceramic coatings

Patent metadata

Field	Value
Publication number	US-11131206-B2
Application number	US-201816184108-A
Country	US
Kind code	B2
Filing date	Nov 8, 2018
Priority date	Nov 8, 2018
Publication date	Sep 28, 2021
Grant date	Sep 28, 2021

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. 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, the first bevel extending continuously between the first channels; and
a plurality of second channels along the second bevel extending from the inner diameter surface to the second circumferential end, the second bevel extending continuously between the second channels; and

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

2. The blade outer airseal of claim 1 wherein:
the ceramic coating comprises a stabilized zirconia.

3. The blade outer airseal of claim 1 wherein:
the body comprises a metallic substrate and a metallic bondcoat.

4. The blade outer airseal of claim 3 wherein:
the metallic substrate is a nickel-based superalloy; and
the ceramic coating comprises a stabilized zirconia.

5. The blade outer airseal of claim 1 wherein:
the ceramic coating has a by weight majority of at least one of yttria stabilized zirconia (YSZ) and gadolinia stabilized zirconia (GSZ).

6. The blade outer airseal of claim 1 , wherein the body further comprises: A turbine engine component comprising:
a leading bevel surface extending from the inner diameter surface to the first axial end; and
a plurality of leading bevel surface first channels in the leading bevel surface extending from the inner diameter surface wherein:
the ceramic coating is along the leading bevel surface and in the leading bevel surface first channels.

7. The blade outer airseal of claim 6 wherein:
the ceramic coating has a by weight majority of at least one of yttria stabilized zirconia (YSZ) and gadolinia stabilized zirconia (GSZ).

8. The blade outer airseal of claim 6 wherein:
the plurality of first recesses are in a pattern along the inner diameter surface;
the leading bevel surface 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; and

the ceramic coating is in the first recesses.

9. The blade outer airseal of claim 8 wherein:
the pattern is a hexagonal array;
the hexagonal array has a first row along the leading bevel surface;
the channels of the first group are longer than the channels of the second group;
the channels of the first group comprise a first portion corresponding to a portion of a first recess and a second portion extending from the first portion away from the leading row;
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.

10. The blade outer airseal of claim 6 wherein:
the plurality of first recesses are in a pattern along the inner diameter surface; and
the leading bevel surface 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.

11. The blade outer airseal of claim 8 wherein:
the pattern is a hexagonal array; and
the hexagonal array has a first row along the leading bevel surface.

12. The blade outer airseal of claim 11 wherein:
the ceramic coating comprises a stabilized zirconia.

13. A gas turbine engine including a plurality of blade outer airseals of claim 1 in a circumferential array.

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

15. The gas turbine engine of claim 13 wherein:
the gas turbine engine has a gaspath; and
for each of the plurality of blade outer airseals, a leading bevel surface is at the first axial end of the body along the gaspath.

16. The gas turbine engine of claim 15 wherein for each of the plurality of blade outer airseals:
a plurality of leading bevel surface first channels are in the leading bevel surface extending from the inner diameter surface; and
the ceramic coating is along the inner diameter surface and the leading bevel surface and in the leading bevel surface first channels.

Assignees

• United Technologies Corp
• Raytheon Tech 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