Wear resistant turbine blade tip
A gas turbine engine includes: a turbine section including a casing extending circumferentially about a plurality of turbine blades and having at least one seal member coated with an abradable coating. At least one turbine blade has sides and a tip and at least one seal member is located adjacent to the tip of the at least one turbine blade. The tip of the at least one turbine blade has a wear resistant layer and an abrasive coating disposed on the wear resistant layer. The wear resistant layer has a thickness less than or equal to 10 mils (254 micrometers) and includes metal boride compounds.
1. A gas turbine engine comprising: a turbine section comprising a casing extending circumferentially about a plurality of turbine blades and having at least one seal member coated with an abradable coating; wherein at least one turbine blade is formed from a parent metal comprising nickel or a nickel alloy, and has sides and a tip and the at least one seal member is located adjacent to the tip of the at least one turbine blade, wherein the turbine blade sides have a thermal barrier coating and the tip of the at least one turbine blade has a wear resistant layer and an abrasive coating disposed on the wear resistant layer, wherein wear resistant layer has a hardness at least an order to two orders of magnitude higher than the blade parent metal and comprises metal boride compounds;
wherein the wear resistant layer has a hardness of 1500 to 2500 HV 0.05 g.
2. The gas turbine of claim 1 , wherein the wear resistant layer is formed in a parent metal surface of the blade and the metal boride compounds comprise M 3 B 4 and M can be titanium, vanadium, chromium, zirconium, niobium, molybdenum, tantalum, tungsten, or a combination thereof.
3. The gas turbine engine of claim 1 , wherein the parent metal comprises titanium, titanium alloy, steel, nickel, cobalt, nickel alloy, cobalt alloy, iron- or nickel- or cobalt-based superalloys or a combination thereof.
4. The gas turbine engine of claim 1 , wherein the parent metal comprises a microstructure and the microstructure comprises equiaxed grains, directionally solidified grains, or a single crystal structure.
5. The gas turbine engine of claim 1 , wherein the blade comprises internal cooling structures.
6. A method of forming a seal between at least one seal member having an abradable coating, and at least one metal blade having sides and a tip, the method comprising: forming a wear resistant layer on the tip of the at least one metal blade; disposing an abrasive coating on the wear resistant layer; and coating the at least one seal member with an abradable coating, wherein the wear resistant layer comprises metal boride compounds and has a hardness at least an order to two orders of magnitude higher than the blade metal;
wherein the wear resistant layer has a hardness of 1500 to 2500 HV 0.05 g.
7. The method of claim 6 , wherein the wear resistant layer is formed in a metal surface of the blade and the metal boride compounds comprise M 3 B 4 and M can be titanium, vanadium, chromium, zirconium, niobium, molybdenum, tantalum, tungsten, or a combination thereof.
8. The method of claim 6 , wherein the blade comprises titanium, titanium alloy, steel, nickel, cobalt, nickel alloy, cobalt alloy, iron- or nickel- or cobalt-based superalloys or a combination thereof.
9. The method of claim 6 , wherein the blade comprises a microstructure and the microstructure comprises equiaxed grains, directionally solidified grains, or a single crystal structure.
10. The method of claim 6 , wherein the blade comprises internal cooling structures.
11. The method of claim 6 , wherein the wear resistant layer is formed in a metal surface of the blade by gaseous boronizing, liquid boronizing, powder boronizing, paste boronizing, chemical vapor deposition, plasma-assisted chemical vapor deposition, plasma vapor deposition, electron-beam plasma vapor deposition, glow discharge or a combination thereof.
12. The method of claim 6 , wherein the wear resistant layer is formed by surrounding the blade with a source of metal atoms followed by surrounding the blade with a source of boron atoms.
13. The method of claim 6 further comprising depositing a thermal barrier coating on the sides of the blade after the wear resistant layer is formed and prior to depositing the abrasive coating.
14. An abrasive coating system on the tip of at least one metal turbine blade wherein the coating system comprises an abrasive coating disposed on a wear resistant layer and the wear resistant layer comprises metal boride compounds and has a hardness at least an order to two orders of magnitude higher than the blade metal;
wherein the wear resistant layer has a hardness of 1500 to 2500 HV 0.05 g.
15. The coating system of claim 14 , wherein the wear resistant layer is formed in a metal surface of the blade and metal boride compounds comprise M 3 B 4 and M can be titanium, vanadium, chromium, zirconium, niobium, molybdenum, tantalum, tungsten, or a combination thereof.
16. The coating system of claim 14 , wherein the blade comprises titanium, titanium alloy, steel, nickel, cobalt, nickel alloy, cobalt alloy, iron- or nickel- or cobalt-based superalloys or a combination thereof.
17. The coating system of claim 14 , wherein the blade comprises a microstructure and the microstructure comprises equiaxed grains, directionally solidified grains, or a single crystal structure.