A seal assembly for a gas turbine engine, having a seal formed of a carbon material; and a seal seat positioned for rotation relative to the seal, wherein the seal and the seal seat each have a sealing surface which together define a sliding seal, and wherein at least the sealing surface of the seal seat is made of the same carbon material as the sealing surface of the seal.

A turbofan having a dilution rate of at least 10 and including a fan having a disc provided with blades at the periphery thereof, a distance between the head of the blades and the housing of the fan being less than or equal to ten millimeters; a primary flow space and secondary flow space that are concentric; a turbine, housed in the primary flow space and in fluid communication with the fan; and a reduction mechanism coupling the turbine and the fan.

A propeller blade comprises a root, a tip distal from the root, a trailing edge extending from the root to the tip, a trailing edge, e.g. foam, insert, a shell forming an outer surface of the propeller blade and a plurality of stitches of yarn extending through two parts of the shell adjacent the trailing edge, wherein the yarns do not extend through the trailing edge insert.

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 gas turbine engine according to an exemplary aspect of this disclosure includes, among other things, a compressor section, a combustor section, a turbine section, and at least one rotatable shaft. The gas turbine engine further includes a seal assembly including a static structure and a rotatable structure configured to meet to form a contact area. The seal assembly includes an abradable coating on one of the static structure and the rotatable structure, and the seal assembly further includes a cutter on the other of the static structure and the rotatable structure.

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 gas turbine engine according to an exemplary aspect of this disclosure includes, among other things, a compressor section, a combustor section, a turbine section, and at least one rotatable shaft. The gas turbine engine further includes a seal assembly including a static structure and a rotatable structure configured to meet to form a contact area. The seal assembly includes an abradable coating on one of the static structure and the rotatable structure, and the seal assembly further includes a cutter on the other of the static structure and the rotatable structure.

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 further includes an abradable coating adjacent the contact area. The abradable coating includes magnetic particles embedded in a polymer material.

A ring-shaped thermomechanical part for a turbine engine, comprising at least one coating including a polymeric matrix and fillers in non-deflagrating carbon exclusively comprising the chemical element C. A turbine engine comprising such a part.