FIELD: machine building.
SUBSTANCE: invention relates to the field of turbine construction. Impeller of gas turbine engine comprises blades, which are permanently connected to support ring, front and rear flanges. Vane shank is additionally restrained by inter-blade fastening, monolithic with support ring, front and rear flanges. Protective metal pad on input edge is clamped by shank of blade, front flange and inter-blade fastening. On the front flange the cowling is installed permanently through the centring retainer, and the power fixture is made with the composite material passing along the aerofoil profile of the fairing and the support ring and laid on the rear flange. Cutting of blades is performed with provision of material intended for inter-blade fastening, beyond contour of tail. Blades are pressed together with a metal lining on the entrance edge. Material is laid for power fastening of fairing to mould cavity, fairing is installed with centring retainer, on ledge of which string is threaded, intended for formation of front and rear flanges and support ring. Blades are installed in cavity of separator, impregnated with binder and material is placed, which goes beyond contour of shank. Elastic punch is installed in the mould, and layers of material between the shoulder blade and the rear flange are laid thereon. A pressure male die is installed.
EFFECT: higher strength and stiffness of impeller at reduced specific weight and labour intensity.
2 cl, 14 dwg
