摘要:
A gas turbine engine includes a plurality of circumferentially-spaced blades (62). The blades (62) have a polymeric coating (62a) thereon. An abradable seal (64) circumscribes the blades and includes a polymeric matrix (68) with a dispersion of a nanolayer material (70).
摘要:
A gas turbine engine includes a plurality of circumferentially-spaced blades (62). The blades (62) have a polymeric coating (62a) thereon. An abradable seal (64) circumscribes the blades and includes a polymeric matrix (68) with a dispersion of a nanolayer material (70).
摘要:
A method of manufacturing a gas turbine engine air seal (26) comprises forming at least one MAX phase particle (34). The method includes coating the at least one MAX phase particle (34) with a metallic shell (36). The method includes applying the at least one MAX phase metallic coated particle (38) to a surface (20) of a substrate of the air seal (26) to form an abradable layer (32) of a MAXMET composite abradable material from the at least one MAX phase metallic coated particle (38).