INTERMETALLIC ALLOY BASED ON THE γ-TiAl PHASE FOR THE MANUFACTURE OF A LOW-PRESSURE TURBINE BLADE OF A GAS TURBINE ENGINE AND A METHOD FOR MANUFACTURING A BLADE BLANK FROM AN INTERMETALLIC ALLOY BASED ON THE γ-TiAl PHASE Russian patent published in 2022 - IPC C22C14/00 B21K3/04 C22F1/18 

FIELD: metallurgy.

SUBSTANCE: invention relates to the field of metallurgy, namely to intermetallic alloys based on the γ-TiAl phase and can be used in the manufacture of a low-pressure turbine blade (LPT) of a gas turbine engine (GTE) of a new generation of aircraft. An intermetallic alloy based on the γ-TiAl phase for the manufacture of a low-pressure turbine blade of a gas turbine engine contains, at. %: aluminum 44.0, niobium 3.0, zirconium 2.0, hafnium 1.0, boron 0.15, titanium the rest, while in the cast state the amount of β(β₀)-phase is no more than 7, vol. %, and after heat treatment, the amount of β(β₀)-phase is 2, vol. %, or less. The method for manufacturing a low-pressure turbine blade blank of a gas turbine engine from an intermetallic alloy based on the γ-TiAl phase includes providing a cast blade blank, isothermal stamping and subsequent heat treatment. Isothermal stamping is carried out at a temperature of 950-1000°C with a degree of deformation of 30-50% and a speed selected in the range of 10^-4-5×10^-3 s^-1, and heat treatment is carried out twice by annealing with the provision in the structure of the amount of β(β₀)-phase, 2, vol. %, or less, and the first annealing is carried out at a temperature of 1270°C for 2 hours, followed by cooling with a furnace up to 900°C, and the second annealing is carried out at a temperature of 900°C for 4 hours, followed by cooling with a furnace.

EFFECT: increase in the heat resistance and ductility of the alloy is provided, as well as simplification of the manufacture of the GTE LPT blade blank.

2 cl, 2 dwg, 1 ex