FIELD: production of composite materials.
SUBSTANCE: invention relates to a method of making a part from a thermo-structural composite material, which can be used as a gas turbine engine blade. Forming a fibrous structure of refractory fibers, performing first impregnation of fibrous structure with first slurry, containing first refractory particles, removing the liquid phase from the first slurry impregnating the fibrous structure so that only the first refractory particles remain inside said structure. Method comprises second impregnation of fibrous structure with second slurry containing second refractory particles, followed by removal of liquid phase. First and second refractory particles present in the fibrous workpiece are sintered to form a refractory matrix. Refractory particles of the first and second slip are different in size and/or chemical nature.
EFFECT: technical result of invention is obtaining part from composite material with high share of matrix and with characteristics, for example mechanical properties, which vary in thickness of material.
11 cl, 12 dwg
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Authors
Dates
2020-06-03—Published
2015-12-18—Filed