FIELD: turbine construction.
SUBSTANCE: invention relates to turbine construction, more specifically to methods for manufacturing compressor guide blades of a composite material for a gas turbine engine, predominantly for an aircraft engine. When manufacturing compressor guide blades, layers for the blades are cut out so that the material extends beyond the contour of the blades from the primary section side to a length, greater than the arc length of the support ring between adjacent blades, and from the peripheral section side to a length greater than the rim arc between adjacent blades. Aerodynamic profile of the blade is shaped in a mold. Blades are laid in the separator of the assembly mold, on the primary and peripheral supports of which a support ring and a rim are formed, after which the separator is placed in the mold and pressing is performed. Wherein the outer surfaces of the rim are formed in the matrix, outer surfaces of the support ring are formed in the punch, and the inner aerodynamic surfaces of the gas path of the support ring and rim are formed in the separator. Before assembling the mold, threads or bundles impregnated with a binder are wound onto the punch, at the point of its contact with the support ring, and onto the rim.
EFFECT: invention provides improved reliability of the compressor guide device by eliminating the layering of its support ring and rim.
1 cl, 9 dwg
