Gas turbine engine seal ring assembly
AssigneeRaytheon Technologies Corporation
InventorsPantcho P. Stoyanov, Mark B. Gossner
Life of this patent
Estimating the term…
Abstract
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 and a first layer disposed on the substrate. The first layer includes copper, and a second layer is disposed on the first layer and arranged to establish a sealing relationship with the rotor. The second layer includes a solid lubricant. A method of sealing is also disclosed.
Claims20
A rotor assembly for a gas turbine engine comprising:
- a rotor including a hub carrying one or more rotatable blades, the rotor mechanically attached to a shaft;
- and
- an annular seal carried by the shaft, wherein the annular seal comprises:
- a substrate;
- a first layer disposed on the substrate, the first layer comprising copper;
- and
- a second layer disposed on the first layer and arranged to establish a sealing relationship with the rotor along an interface, the second layer comprising a solid lubricant, and the solid lubricant comprising molybdenum disulfide (MoS2);
- and
- wherein the second layer of the seal abuts against an inner diameter portion of the hub along the interface, and the hub includes a solid lubricant disposed on the inner diameter portion of the hub to establish the interface.
A gas turbine engine comprising:
- a fan section including a fan;
- a compressor section including a compressor;
- a turbine section including a turbine driving the compressor;
- a shaft rotatable about an engine longitudinal axis;
- wherein the compressor section includes a rotor assembly, the rotor assembly comprising:
- a rotor including a hub carrying a plurality of rotatable blades, the rotor mechanically attached to the shaft;
- a piston ring carried by the shaft, the piston ring comprising a first layer of copper alloy disposed on a substrate, and a second layer that abuts against an inner diameter portion the hub along an interface to establish a sealing relationship, the second layer comprising a solid lubricant, and the solid lubricant comprising molybdenum disulfide (MoS2);
- and
- wherein the hub includes a solid lubricant disposed on the inner diameter portion of the hub to establish the interface.
A method of sealing for a gas turbine engine comprising:
- forming a piston ring comprising a first layer of copper alloy disposed on a substrate, and a second layer that abuts against a rotor to establish a sealing relationship, the second layer comprising a solid lubricant, and the solid lubricant comprises molybdenum disulfide (MoS2);
- mechanically attaching the rotor to a rotatable shaft, the rotor including a hub carrying one or more rotatable blades;
- and
- removing a layer of copper alloy from the piston ring prior to the forming step.
Dependencies are inferred from the claim text.