All-Russian Institute of Aviation Materials, Moscow, Russia:

O. S. Kashapov, Head of a Sector
T. V. Pavlova, Leading Engineer
A. R. Kondrateva, Engineer, e-mail: nasty.77@list.ru
V. S. Kalashnikov, Engineer

This article shows the main factors, defining the technical requirements to the blisk-type bladed integrated disks made of titanium alloys. Influence of thermal treatment modes on the phase composition, structure and complex of the material mechanical properties was investigated for the operating wheel of aviation gas-turbine engine compressor made of heat-resistant (α + β)-titanium alloy VT8-1 (ВТ8-1) (Ti – Al – Sn — Zr – Mo – Si). The investigations used several technical treatment modes, which differ from the serial one by the temperature increase on the first stage of annealing and its decreasing on the second stage. Material, annealed with the changed processing temperatures both on the first and on the second stages, has the best combination of mechanical properties. Investigation of the structure of material, annealed by the corrected mode, shows that annealing temperature increase leads to decreasing of the volume ratio of the primary -phase and some growth of α-grain. Reduction of temperature on the second annealing stage preliminates the residue of titanium silicides by the interphase borders, which makes the positive influence on material viscosity characteristics and tells about the increasing of the part of solid-solution strengthening of α- and β-phases. The given changes of the structure and phase composition provide the growth of the strength characteristics and heat resistance of the bladed integrated disk punching (VT8-1 alloy). At the same time, in spite of some increasing of the sizes of conventional β-grain, the fatigue life of the material is also increased, which is especially important for the design of blisk-type compressor wheel.

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