PART PROTECTED WITH SURROUNDING BARRIER Russian patent published in 2022 - IPC C04B41/89 C23C4/10 C23C28/00 

FIELD: engine building.

SUBSTANCE: group of inventions relates to the field of protection of hot parts of gas turbine engines, such as combustion chamber walls or turbine rings, turbine nozzle blades or turbine working blades, for aircraft engines or industrial gas turbine engines. A part of a gas turbine engine contains substrate (20) made of composite material with a ceramic matrix or monolithic ceramic material, at least part of which, adjacent to surface (S) of substrate, is made of material containing silicon; coupling sublayer (30) located on surface (S) of substrate and containing silicon; surrounding barrier (40), which contains outer layer (42) of ceramic, covering coupling sublayer (30). Moreover, specified surrounding barrier (40) additionally contains self-healing inner layer (41) located between coupling sublayer (30) and outer layer (42). In this case, specified inner layer (41) contains a matrix, in which particles forming silicon dioxide are dispersed. Moreover, the specified particles can generate a phase to tighten cracks of the matrix in the presence of oxygen. The inner layer has a volumetric particle content ranging from 20% to 40%. A method for manufacturing the specified part includes stages of: applying coupling sublayer (30) containing silicon to surface (S) of substrate (20); applying inner layer (41) of surrounding barrier (40) to coupling sublayer (30); applying outer layer (42) of surrounding barrier (40) to inner layer (41), while specified outer layer (42) is made of ceramics.

EFFECT: reduction in corrosion of material, which affects the service life.

9 cl, 7 dwg