Article with surface structures for CMAS resistance
In some examples, article used as a component for a turbine engine that operates in a high temperature environment. The article may include: a ceramic or ceramic matrix composite (CMC) substrate; and a coating on the ceramic or the CMC substrate, wherein the coating defines an outer surface of the article. The coating includes a plurality of surface features defining channels on the outer surface of the article. The channels are configured to modify a flow of molten Calcia-Magnesia-Alumina Silicate (CMAS) over the outer surface of the coating in a gas flow over the outer surface of the article to reduce accumulation of the molten CMAS on the outer surface of the article.
1. An article comprising:
a ceramic or ceramic matrix composite (CMC) substrate; and
a coating on the ceramic or the CMC substrate, wherein the coating defines an outer surface of the article, wherein the coating includes a first portion which does not include surface features and a second portion adjacent to the first portion, the second portion defining a plurality of surface features, the plurality of surface features defining channels on the outer surface of the article, wherein the channels are configured to modify a flow of molten Calcia-Magnesia-Alumina Silicate (CMAS) over the outer surface of the coating in a gas flow over the outer surface of the article to reduce accumulation of the molten CMAS on the outer surface of the article, wherein:
the plurality of surface features includes one or more protrusions protruding out of a surface plane of the coating, wherein the surface plane of the coating is defined by the first portion of the coating, and wherein the one or more protrusions define the channels on the outer surface of the article,
respective channels on the outer surface of the coating are defined by neighboring individual protrusions of the one or more protrusions, and
the respective channels have a ramped surface between the neighboring individual protrusions, wherein the ramped surface is a planar surface and defines a first point and a second point on the planar surface, wherein the first point and the second point are at different distances away from the surface plane of the coating along a line substantially parallel to the gas flow over the outer surface of the article, wherein the ramped surface defines an elevation change in a Z-direction relative to the surface plane of the coating such that the respective channels are recessed into or protrude out of the surface plane of the coating.
2. The article of claim 1 , wherein the plurality of surface features includes one or more recesses recessed into the surface plane of the coating, wherein the one or more recesses define the channels on the outer surface of the article.
3. The article of claim 1 , wherein the channels are tapered in a direction of the gas flow over the outer surface.
4. The article of claim 1 , wherein at least a portion the plurality of surface features are located at a trailing edge of the article relative to the gas flow.
5. The article of claim 1 , wherein the coating includes an abradable coating, and wherein at least a portion the plurality of surface features are located adjacent a track formed into the abradable coating by the abrasion of an opposing abrasive member.
6. The article of claim 5 , wherein a first set of surface features of the plurality of surface features are located adjacent to the track at an upstream edge of the track, and wherein a second set of surface features of the plurality of surface features are located adjacent to the track at a downstream edge of the track.
7. The article of claim 6 , wherein the first set of surface features includes a plurality of protrusions protruding out of a surface plane of the article, and the second set of surface features includes a plurality of recesses recessed into the surface plane of the article.
8. The article of claim 1 , wherein the coating includes a first portion that is more susceptible to CMAS attack as compared to a second portion of the coating, wherein the first portion is configured to, during operation of the article in a high temperature environment, be removed from the coating to define at least a portion of the plurality of surface features with the second portion.
9. The article of claim 8 , wherein the first portion is more susceptible to CMAS attack based on at least one of a microstructure of the first portion or a composition of the first portion as compared to the second portion.
10. The article of claim 1 , wherein the article is a component of a gas turbine engine configured to operate in a high temperature environment in which the molten CMAS is present.
11. The article of claim 10 , wherein the component comprises at least one of a turbine blade, vane, or shroud.
12. The article of claim 1 , wherein the plurality of surface features are configured to modify the flow of molten Calcia-Magnesia-Alumina Silicate (CMAS) over the outer surface of the coating by at least one of accumulating the molten CMAS in the channels, raising the molten CMAS above the surface plane of the coating into the gas flow, or drawing the molten CMAS to a trailing edge of the article.
13. The article of claim 1 , wherein the coating includes an environmental barrier coating including a rare earth silicate.
14. A method comprising forming a coating on a ceramic or ceramic matrix composite (CMC) substrate on an outer surface of an article, wherein the coating includes a a first portion which does not include surface features and a second portion adjacent to the first portion, the second portion defining a plurality of surface features, the plurality of surface features defining channels on the outer surface of the article, wherein the channels are configured to modify a flow of molten Calcia-Magnesia-Alumina Silicate (CMAS) over the outer surface of the coating in a gas flow over the outer surface of the article to reduce accumulation of the molten CMAS on the outer surface of the article, wherein:
the plurality of surface features includes one or more protrusions protruding out of a surface plane of the coating, wherein the surface plane of the coating is defined by the first portion of the coating, and wherein the one or more protrusions define the channels on the outer surface of the article,
respective channels on the outer surface of the coating are defined by neighboring individual protrusions of the one or more protrusions, and
the respective channels have a ramped surface between the neighboring individual protrusions, wherein the ramped surface is a planar surface and defines a first point and a second point on the planar surface, wherein the first point and the second point are at different distances away from the surface plane of the coating along a line substantially parallel to the gas flow over the outer surface of the article, wherein the ramped surface defines an elevation change in a Z-direction relative to the surface plane of the coating such that the respective channels are recessed into or protrude out of the surface plane of the coating.
15. The method of claim 14 , wherein the plurality of surface features includes one or more recesses recessed into the surface plane of the coating, wherein the one or more recesses define the channels on the outer surface of the article.
16. The method of claim 14 , wherein the channels are tapered in a direction of the gas flow over the outer surface.
17. The method of claim 14 , wherein at least a portion the plurality of surface features are located at a trailing edge of the article relative to the gas flow.
18. The method of claim 14 , wherein the coating includes an abradable coating, and wherein at least a portion the plurality of surface features are located adjacent to a track formed into the abradable coating by the abrasion of an opposing abrasive member.
19. The method of claim 18 , wherein a first set of surface features of the plurality of surface features are located adjacent to the track at an upstream edge of the track, and wherein a second set of surface features of the plurality of surface features are located adjacent to the track at a downstream edge of the track.
20. The method of claim 19 , wherein the first set of surface features includes a plurality of protrusions protruding out of a surface plane of the article, and the second set of surface features includes a plurality of recesses recessed into the surface plane of the article.