METHOD FOR MANUFACTURING AN AIRCRAFT ENGINE IMPELLER FROM A COMPOSITE MATERIAL Russian patent published in 2022 - IPC F04D29/26 F01D5/00 

FIELD: turbine engineering.

SUBSTANCE: invention relates to the field of turbine engineering, more precisely to the method for manufacturing the impeller of an aviation gas turbine engine containing blades permanently connected to the support ring, front and rear flanges. The shanks of the blades are additionally pinched by an inter-blade attachment, monolithic with a support ring, front and rear flanges. A hub is placed between the front and rear flanges, solidly assembled with them. In the manufacture of the impeller, layers of composite material of the blades, single blanks for the support ring, front and rear flanges and annular layers for the hub are cut. The cutting for the blades is performed to ensure that the material intended for the inter-blade attachment goes beyond the contour of the shank. The blades are pressed and placed in a mold separator, impregnated with a binder and a material is formed that goes beyond the contour of the shank. An elastic punch is installed in the mold, layers of inter-blade mounting material and a rear flange are laid on it. A pressure punch is installed and pressure on the elastic punch is created. Then the elastic punch is removed, a replaceable centering retainer is placed in the mold, the annular area of the front and rear flanges in contact with the hub is impregnated with a binder. The retainer provides the nominal arrangement of the annular layers of the composite material of the hub strung on it, on which the rear flange is laid sequentially and an annular pressure punch is installed, the necessary pressure is created and the polymerization process is carried out.

EFFECT: impeller of increased strength and rigidity with a decrease in specific gravity is obtained.

1 cl, 10 dwg