Seal ring assembly for a gas turbine engine
A rotor assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor that has a hub carrying one or more rotatable blades. The rotor is mechanically attached to a shaft, and an annular seal is carried by the shaft. The annular seal includes a substrate, a first layer disposed on the substrate, and a second layer disposed on the first layer and arranged to establish a sealing relationship with the rotor. The second layer includes a solid lubricant that has molybdenum trioxide (MoO3). A method of sealing for a gas turbine engine is also disclosed.
1. A method of sealing for a gas turbine engine comprising:
forming a piston ring comprising a first layer disposed on a substrate, and a second layer disposed on the first layer, the second layer comprising a solid lubricant including molybdenum trioxide (MoO3);
mechanically attaching a rotor to a rotatable shaft such that the piston ring establishes a sealing relationship between the rotor and the shaft, the rotor including a hub carrying one or more rotatable blades; and
wherein the step of forming includes depositing molybdenum disulfide (MoS2) on the first layer, and heating the molybdenum disulfide (MoS2) to a predetermined temperature threshold to form the solid lubricant.
2. The method as recited in claim 1 , wherein the step of forming includes depositing the second layer directly on the first layer.
3. The method as recited in claim 1 , wherein the first layer has a composition, by weight percent, 85% to 95% copper, and at least 5% aluminum.
4. The method as recited in claim 1 , wherein the piston ring includes a seal body extending between a first end and a second, opposed end that engages with the first end along an outer diameter portion of the shaft.
5. The method as recited in claim 1 , wherein the hub defines a seal land that establishes the sealing relationship with the second layer.
6. The method as recited in claim 1 , wherein:
the rotor is an integrally bladed rotor; and
the second layer is dimensioned to abut against an inner diameter portion of the hub to establish the sealing relationship.
7. The method as recited in claim 1 , wherein the first layer comprises copper.
8. The method as recited in claim 7 , wherein the first layer has a composition, by weight percent, 8% to 12% aluminum, and at least 85% copper.
9. The method as recited in claim 1 , wherein the rotor is a compressor rotor.
10. The method as recited in claim 9 , wherein the substrate of the piston ring is seated in an annular groove extending inwardly from an outer diameter portion of the shaft, and the second layer abuts against an inner diameter portion of the hub.
11. The method as recited in claim 10 , wherein the first layer has a composition, by weight percent, 60% to 95% copper, and aluminum.
12. The method as recited in claim 11 , wherein the substrate comprises a nickel alloy.
13. The method as recited in claim 10 , wherein the compressor rotor is an integrally bladed rotor.
14. The method as recited in claim 10 , wherein the piston ring is a split ring including a seal body extending between a first end and a second, opposed end that engages with the first end.
15. The method as recited in claim 14 , wherein the first layer has a composition, by weight percent, 60% to 95% copper, and aluminum.
16. The method as recited in claim 14 , wherein the compressor rotor is an integrally bladed rotor.
17. The method as recited in claim 16 , wherein the first layer comprises copper.
18. The method as recited in claim 17 , wherein the substrate comprises a nickel alloy.
19. The method as recited in claim 17 , wherein the first layer has a composition, by weight percent, 60% to 95% copper, and aluminum.
20. The method as recited in claim 19 , wherein the substrate comprises a nickel alloy.