METHOD FOR PRODUCING BLADED INTEGRATED DISC OF TURBINE FROM VARIOUS METAL ALLOYS FOR GAS TURBINE ENGINES Russian patent published in 2016 - IPC F01D5/34 B23P15/00 B22F3/15 

FIELD: engines.

SUBSTANCE: invention relates to propulsion engineering and can be used in making bladed integrated disc of turbine from various metal alloys for gas turbine engine. In making bladed integrated disc of turbine comprising a disk part from granulated alloy and blades from heat resistant alloy with equiaxial or directed structure, taper rollers are fitted with a certain mounting clearance between working faces mounting flanges in a special device. Between disc part and ends of legs gap is created, which is filled with powder of material of disc part. Process gap value is determined in range of 0.16-0.25 times width of blade shank in area of connection, based on shrinkage value of powder material during manufacture of bladed integrated disc of turbine while mounting gap between working faces of platforms is determined depending on process clearance. Part of legs and part of disc are hermetically encapsulated and capsule is placed in a geostatic extruder. Blade is connected with disc part in one part in zone with approximately same values of continuous static strength of both alloys by hot isostatic pressing. Shaped parts of blades, path and retaining flanges of blades and part of legs of latter are located outside capsule.

EFFECT: invention increases strength and reliability of bladed integrated disc turbine.

1 cl, 2 tbl, 4 dwg