A method of applying an additive to an abrasive coated blade tip comprises applying the additive to the abrasive coated blade tip and wicking the additive into the abrasive coated blade tip, wherein the additive is configured to prevent adhesion of an organic component of an abradable seal onto the abrasive coated blade tip.

An abradable seal comprises an organic matrix composite comprising an additive and an organic component, the additive is configured to prevent adhesion of the organic component onto an abrasive blade tip.

A centrifugal pump, and components thereof, operable at high speeds, is described under the present disclosure. A hard polymer sleeve can be applied to certain surfaces of a seal casing within the pump. If the sleeve is applied along surfaces near the center shaft, then the hard polymer will withstand the forces and pressures of the system. The hard polymer might not be used along the outer diameter, farther from the shaft, because velocities are higher the further out one goes. The current disclosure allows for the use of fluoropolymer in the lining sleeve. The benefits of fluoropolymer have been unavailable in high speed centrifugal pumps because the forces are too great on the periphery of the seal casing. However, the lower speeds along the interior, near the shaft, allow fluoropolymer to be used.

A coating for a blade root/disk interface includes a layer of soft metal matrix, and a solid lubricant distributed through the soft metal matrix. Examples of materials include CuAl as the soft metal matrix and MoS.sub.2 as the solid lubricant, although others are also disclosed.

A labyrinth seal for sealing a sealing region between a rotor and stator of a rotary machine includes, a base, and a plurality of sealing rings. The sealing rings are formed on the base, project into the sealing region and form, between them labyrinth valleys bounded, laterally, by the sealing rings and, in the floor of the valleys, by the base. The sealing rings, in at least one region, include at least one material which is different from that of the base.

A component for a gas turbine engine includes an airfoil. A first trunnion has an outer surface and extends from a first end of the airfoil. A first bushing at least partially surrounds the outer surface. At least one of the first bushing or the first trunnion includes a plurality of surface irregularities.

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a compressor section, a combustor section, a turbine section, and at least one rotatable shaft. The engine further includes a seal assembly including a seal plate mounted for rotation with the rotatable shaft and a face seal in contact with the seal plate at a contact area. The seal assembly includes an abradable coating adjacent the contact area, and the abradable coating includes magnetic particles.

A variable vane assembly includes a variable vane; a trunnion arranged on one end of the variable vane; a bushing mated to the trunnion to define an interface between the trunnion and the bushing; and a surface modification on at least one of the trunnion and the bushing at the interface, whereby frictional heating at the interface during operation of the assembly is reduced.

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a compressor section, a combustor section, a turbine section, and at least one rotatable shaft. The engine further includes a seal assembly including a seal plate mounted for rotation with the rotatable shaft and a face seal in contact with the seal plate at a contact area. The seal assembly includes an abradable coating adjacent the contact area, and the abradable coating includes magnetic particles.

A seal assembly for a gas turbine engine includes a seal composed of a nickel-based superalloy; a component in contact with the seal and defining a seal-counterface; and a coating on the seal at the seal-counterface, wherein the coating is a ternary oxide.