FIELD: turbines or turbomachines.
SUBSTANCE: invention relates to the field of turbine engineering, more specifically to methods of manufacturing compressor guide vanes from composite material for a gas turbine engine, mainly aircraft. Compressor guide vanes made of composite material, in which blades are made integral with support ring and rim, production of which includes cutting layers for blades, note here that material extends beyond blade contour on side of root section to a length greater than that of support ring arc between adjacent blades while, on side of peripheral section, it extends beyond that of rim arc between adjacent blades. Besides, layer including backrest, front edge and trough material is cut. Blade aerodynamic profile is formed in the mold, wherein its filling is started with the back material laying, then the remaining layers are laid, and completing the trough material laying; further, the blades are laid into the mold separator, on the root and peripheral supports of which a support ring and a rim are formed; then threads or bundles impregnated with binder are wound on the rim, and on the punch — at the point of contact with the support ring. Separator is placed in mold, puncheon is installed and pressing is performed, note here that outer surfaces of the rim are formed in the matrix, outer surfaces of the support ring are formed in the punch, and inner aerodynamic surfaces of the gas path of the support ring and the rim are formed in the separator.
EFFECT: thus, aircraft gas turbine engine is obtained, in which monolithic guide vane of compressor is made of composite material, which allows to reduce weight and labor intensity of item manufacturing.
1 cl, 11 dwg
