FIELD: metallurgy.
SUBSTANCE: invention relates to metallurgy, namely to the production of ceramic composite materials used for the manufacture of parts of the combustion chamber, high and low pressure turbines of a gas turbine engine (GTE), operating at high temperatures under the influence of fuel combustion products. A ceramic composite material with a multilayer structure contains at least one ceramic layer and a reinforcing layer in the form of a foil. The ceramic layer is made of a powder mixture of the Si-B-Mo-C system, obtained as a result of joint grinding of SiB4, Mo, C, SiC with WC balls, and molybdenum foil 100-200 microns thick with a barrier coating is used as a reinforcing layer, with In this case, the content of components in the powder mixture is, wt.%: SiB4 10-40, Mo 20-50, C 5-10, SiC - the rest.
EFFECT: material is characterized by high resistance to oxidation in the operating temperature range up to 1500°C and high thermal stability compared to monolithic ceramics of the same phase composition.
5 cl, 1 tbl, 3 ex
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Authors
Dates
2022-10-12—Published
2022-01-27—Filed