Seal geometries for reduced leakage in gas turbines and methods of forming
A turbomachine sealing component has: a substrate having circumferential surface; and a coating on the circumferential surface. The coating or a layer thereof is patterned to form circumferential sealing ridges.
1. A turbomachine sealing component comprising:
a substrate ( 63 ; 65 ) having a circumferential surface ( 61 ; 66 ); and
a coating ( 60 ) on the circumferential surface;
wherein:
the coating or a layer thereof is patterned to form circumferential sealing ridges ( 150 ; 170 ) effective to form grooves in something that is circumferentially rubbed against the turbomachine sealing component; and
an abradable material ( 180 ) of the coating is in gaps between the ridges.
2. The turbomachine sealing component of claim 1 wherein the patterning is patterning with varying thickness.
3. The turbomachine sealing component of claim 1 wherein the patterning comprises:
a layer formed of discrete ridges ( 170 ) physically discontinuous from each other so as to be separated from each other by axial gaps.
4. The turbomachine sealing component of claim 1 wherein the patterning comprises:
a layer formed of discrete ridges ( 160 ) physically continuous with each other via less thick portions of the same material.
5. The turbomachine sealing component of claim 1 wherein the coating comprises:
a bondcoat ( 62 ); and
an additional layer ( 64 ).
6. The turbomachine sealing component of claim 1 wherein:
the varying thickness is between 10 mil and 40 mil.
7. The turbomachine sealing component of claim 1 wherein:
the varying thickness is of ridges having widths of 60% to 250% of heights.
8. The turbomachine sealing component of claim 1 wherein:
the varying thickness comprises ridges of 5.0% to 30% of a blade-swept area.
9. The turbomachine sealing component of claim 1 being a turbomachine rotor having:
said substrate with said surface as an outer diameter surface; and
said coating on the outer diameter surface.
10. A method for manufacturing the turbomachine sealing component of claim 1 , the method comprising:
forming the pattern via an additive process.
11. A turbomachine sealing component comprising:
a substrate ( 63 ; 65 ) having a circumferential surface ( 61 ; 66 ); and
a coating ( 60 ) on the circumferential surface,
wherein:
the coating or a layer thereof is patterned to form circumferential sealing ridges ( 150 ; 170 )
an abradable material ( 180 ) of the coating is in gaps between the ridges;
the coating comprises a bondcoat ( 62 ) and an additional layer ( 64 ); and
the additional layer comprises a metallic matrix and an abrasive addition.
12. The turbomachine sealing component of claim 11 wherein the additional layer comprises:
a metallic alloy;
an intermetallic;
a ternary carbide; and/or
an oxide ceramic, a nitride ceramic or a carbide ceramic.
13. The turbomachine sealing component of claim 11 wherein:
the pattern is formed in the bondcoat and trace through along the additional layer to form the ridges.
14. The turbomachine sealing component of claim 11 wherein:
the pattern is formed in the additional layer.
15. The turbomachine sealing component of claim 11 wherein:
the additional layer comprises a ceramic.
16. The turbomachine sealing component of claim 11 wherein:
the additional layer comprises not more than 12% porosity.
17. A method for manufacturing and using a turbomachine sealing component, the turbomachine sealing component comprising:
a substrate ( 63 ; 65 ) having a circumferential surface ( 61 ; 66 ); and
a coating ( 60 ) on the circumferential surface,
wherein:
the coating or a layer thereof is patterned to form circumferential sealing ridges ( 150 ; 170 ), the method comprising:
forming said circumferential sealing ridges;
applying an abradable material ( 180 ) to at least partially embed the sealing ridges;
rubbing with an adjacent component; and
the rubbing causing the pattern to leave the ridges protruding from the abradable material and cut grooves in tips of blades or in inner diameter tips of vanes.
18. The method of claim 17 wherein:
the turbomachine sealing component is a blade outer airseal; and
the adjacent component comprises said tips of said blades.
19. The method of claim 17 wherein:
the grooves are in a blade substrate.
20. The method of claim 17 wherein:
the turbomachine sealing component is a turbomachine rotor; and
the adjacent component comprises said vane inner diameter tips.