METHOD OF POSITIONING OF BLADES IN MAKING OF INTEGRATED BLISK (BLADED INTEGRATED DISC) OF GAS TURBINE ENGINE Russian patent published in 2016 - IPC F01D5/34 B22F7/08 B22F5/04 

FIELD: engines.

SUBSTANCE: invention relates to propulsion engineering and can be used for positioning of blades in making of integrated BLISK of gas turbine engine. At positioning of blades blade roots are fitted in appropriate ports of process ring, which is made of low-carbon steel, wherein ports are made on the basis of guaranteed clearance along the perimeter of ports. On the inner surface of the latter and outer surface of blade roots are applied nickel coating with thickness of 6-15 µm. Position of blade roots is fixed in ports arranging in gaps mounting elements. Solder is applied along the whole perimeter of each of gaps on the inner side of process ring. Wherein mounting elements are made of nickel alloy, melting temperature of which is higher than melting point of solder. Connection of blade roots with a process ring is performed by diffusion soldering in vacuum furnace at temperature of homogenization of material of blades, residual pressure of 5-8×10^-5 mmhg and isothermal holding at temperature not less than 3 hours. Further, production tooling is assembled with disc part in tight capsule for further manufacturing of turbine BLISK by hot isostatic pressing.

EFFECT: invention provides higher accuracy of geometrical parameters of gas turbine BLISK channel and tightness of blades connections with process equipment.

1 cl, 6 dwg, 1 tbl