ABRADABLE LAYER FOR A TURBO-ENGINE AND A MANUFACTURING PROCESS

摘要

2096435 9306341 PCTABS00021 The invention relates to running-in lining for labyrinth seals of a turbomachine, especially a gas turbine, consisting of a laminate with a core and a covering and intermediate layers, and a process for producing the running-in lining. Here, the core is made of a felted or three-dimensionally cross-linked fibre body of iron, nickel or cobalt-based alloys and the covering of one or more noble metals or noble metal alloys and each core is completely surrounded by the covering material, the intermediate layers consisting of oxidation-resistant sliding materials from the group consisting of oxides, carbides or nitrides with a hexagonal crystal lattice structure.