FIELD: turbine construction.
SUBSTANCE: invention relates to the field of turbine construction, more specifically to methods for manufacturing compressor guide vanes for a gas turbine engine, mainly for aircraft. The guide vanes of the compressor are made of a composite material, the manufacture of which includes cutting the layers for the blades, their final design is made in a mold. The finished blade on the peripheral side has a shank for fastening in the rim, on the opposite side of the blade for fastening in the support ring there is a shank with the profile of the last root section of the blade, such a shank simplifies the manufacture of composite material layers and a mold for pressing the blades. The rim is formed by winding from threads or bundles with subsequent polymerization, the holes for the blade shanks are made by punching or milling. The support ring consists of inlet and outlet half rings, for the manufacture of which layers of composite material are cut, they are placed in a mold, the mold is pressed, polymerized and disassembled, thus obtaining inlet and outlet support half rings, which have grooves for attaching the blade root. The assembly of the guide vane apparatus is carried out by installing the blade roots in the holes of the rim, then after installing all the blade roots in one of the support semi-rings, the second support semi-ring is laid, aligning the grooves of the latter with the blade roots. Both supporting half rings are compressed, for example, by bolts, while the blade roots are firmly fixed in the support ring.
EFFECT: significant simplification of the technological process and reduction of labor intensity.
1 cl, 7 dwg
