MANUFACTURING METHOD OF INTEGRATED BLISK WITH COOLED MOVING BLADES, INTEGRATED BLISK AND COOLED BLADE FOR GAS TURBINE ENGINE Russian patent published in 2013 - IPC F01D5/30 F01D5/34 F01D5/18 B23P15/00 B22F3/15 

FIELD: engines and pumps.

SUBSTANCE: individual cooled blades from monocrystalline alloy is attached to a disc part from granulated alloy into a solid part by hot isostatic pressing (HIP) in the zone where long-term strengths of those alloys are similar at one and the same temperature in a continuous operating mode. Shaped part, path flange and some part of the root with a cooling air supply branch pipe via a shaped channel to any of the blades are located outside the HIP influence zone; blade roots are aligned with the disc, and mainly end-to-end. Zone of similar long-term strength of both alloys is pre-determined as per long-term strength curves of alloys. Cooled blade includes the air cooling system comprising the air supply device to the blade in the form of an inlet branch pipe or holes in the root, air distribution channels to the shaped part and in the blade shaped part itself, which are located above a certain zone equal approximately to long-term strength of alloys of blades and disc part.

EFFECT: increasing strength, service life and reducing the weight of the turbine impeller for full-size high-temperature gas turbine engines, including high-temperature gas turbine engines with long service life, which are used in aviation, space and ground facilities, and in industrial power engineering.

6 cl, 8 dwg