FIELD: turbine construction.
SUBSTANCE: invention relates to the field of turbine construction. Impeller of the aviation gas turbine engine contains blades, connected to the support ring, the front and rear flanges. Blade root is additionally clamped by the inter-blade fastening, integrally made with the support ring, by the front and rear flanges. At the entrance edge, the metal lining is clamped by the blade root, the front flange and the inter-blade fastener, which are tightly in contact with the metal latch stopper. In the manufacture of the specified impeller carry out cutting of the layers of material of the blades and single blanks for the support ring, front and rear flanges; in the latter, an incision is made from the point where the back edge of the blade touches the diameter to the outer circumference. Cutting for the blades is carried out with ensuring the release of material, intended for interscapular attachment, outside the shank contour. Blades are pressed together with a metal lining on the entrance edge. Put the blanks into the mold separator for the design of the front flange and the aerodynamic profile of the support ring. Install the blades in the cavity of the separator, impregnated with a binder and put the material beyond the contour of the shank, while the composite material is in tight contact with the stopper of the metal lining. Elastic punch is installed in the mold, and layers of material between the shoulder blade and the rear flange are laid thereon. Install the pressure punch and apply pressure to the elastic punch.
EFFECT: group of inventions allows to increase the strength and rigidity of the impeller while reducing the specific gravity.
2 cl, 12 dwg
