Two-layer abrasive coating for rotor-blade tips, method, component, and turbine assembly

Patent metadata

Field	Value
Publication number	US-11788422-B2
Application number	US-202017434751-A
Country	US
Kind code	B2
Filing date	Feb 13, 2020
Priority date	Mar 5, 2019
Publication date	Oct 17, 2023
Grant date	Oct 17, 2023

Abstract

An excellent abrasive blade tip is provided by a two-layer coating system consisting of a brazing solder coating and an NiCoCrAlY coating containing cBN (cubic Boron Nitride).

First claim

The invention claimed is:

1. A process for producing an abrasive coating on a substrate, or on a blade tip of a rotor blade, the process comprising:
applying two layers for the abrasive coating, namely a bottom solder layer and an outer, second layer of a coating comprising abrasive particles as tapes, to the substrate, and
joining the bottom solder layer to the substrate by a soldering process, as a result of which the outer, second layer is also bonded-on,
where a material of the bottom solder layer has a melting point which is at least 10K lower than that of a material of the substrate, and also has a melting point which is at least 10K lower than that of a material of the outer, second layer, and
wherein the abrasive particles are present in the outer, second layer and partly in the bottom solder layer.

2. The process as claimed in claim 1 ,
wherein the outer, second layer comprising the abrasive particles comprises NiCoCrAlY or a nickel or cobalt-based alloy as matrix material.

3. The process as claimed in claim 1 ,
wherein the abrasive coating is firstly applied and soldered, a remaining area of the rotor blade is then coated with a NiCoCrAlY-based alloy.

4. The process as claimed in claim 1 ,
wherein the soldering of the bottom solder layer occurs during a solution heat treatment of the substrate.

5. The process as claimed in claim 4 ,
wherein the solution heat treatment of the substrate takes place at from 1477K to 1516K for from 1 hour to 4 hours.

6. The process as claimed in claim 5 ,
wherein a first annealing heat treatment up to ≥365K for 4 hours, takes place after the soldering process and before coating with NiCoCrAlY.

7. The process as claimed in claim 6 ,
wherein a bonding heat treatment, from ≥350K to ≤1360K, for from 1 hour to 6 hours, takes place after coating with the NiCoCrAlY.

8. The process as claimed in claim 7 ,
wherein a second annealing heat treatment ≤1145K for 24 hours, takes place after the NiCoCrAlY bonding heat treatment.

9. The process as claimed in claim 1 ,
wherein the two layers together comprise a thickness in a range from 0.1 mm to 0.7 mm.

10. The process as claimed in claim 1 ,
wherein the abrasive particles, comprise -cBN particles, and have a diameter in a range from 50 μm to 200 μm.

11. The process as claimed in claim 1 ,
where the material of the bottom solder layer has a melting point which is at least 20K lower, than that of the material of the substrate, and also has a melting point which is at least 20K lower, than that of the material of the outer, second layer.

12. A component, comprising:
an abrasive coating on a substrate composed of a nickel or cobalt-based superalloy, wherein a bottom solder layer is present on the substrate, and
an outer, second layer comprising abrasive particles,
where a material of the bottom solder layer has a melting point which is at least 10K lower than that of a material of the substrate, and also has a melting point which is at least 10K lower than that of a material of the outer, second layer, and
wherein the abrasive particles are present in the outer, second layer and partly in the bottom solder layer.

13. The component as claimed in claim 12 ,
wherein the abrasive particles project from the outer, second layer to an extent of not more than 50%.

14. A turbine assembly, comprising:
at least one rotor blade row comprising rotor blades,
wherein the rotor blades are configured like the component as claimed in claim 12 at a blade tip.

15. The turbine assembly as claimed in claim 14 ,
wherein only part of the rotor blades of the least one rotor blade row comprise the abrasive coating.

16. The component as claimed in claim 12 ,
wherein the outer, second layer comprising the abrasive particles comprises NiCoCrAlY or a nickel or cobalt-based alloy as matrix material.

17. The component as claimed in claim 12 ,
wherein the two layers together comprise a thickness in a range from 0.1 mm to 0.7 mm.

18. The component as claimed in claim 12 ,
wherein the abrasive particles comprise cBN particles, and have a diameter in a range from 50 μm to 200 μm.

19. The component as claimed in claim 12 ,
where the material of the bottom solder layer has a melting point which is at least 20K lower, than that of the material of the substrate, and also has a melting point which is at least 20K lower, than that of the material of the outer, second layer.

Assignees

• Siemens Energy Global Gmbh & Co Kg

Inventors

• Schumann Eckart
• Stöhr Britta
• Flores Renteria Arturo
• Ladru Francis
• Schulz Thorsten
• Wollnik Adrian

Classifications

• F01D5/288 Primary

  Protective coatings for blades · CPC title

• B23K1/0018

  Brazing of turbine parts · CPC title

• B23K1/19 Primary

  taking account of the properties of the materials to be soldered · CPC title

• B23K2101/001

  Turbines · CPC title

• B23K2103/26

  Alloys of Nickel and Cobalt and Chromium · CPC title