Abstract
An integrated process is considered for preparing gas turbine engine compressor blade workpieces made of alloy VT22, eutectically strengthened with titanium boride. The efficiency of two-stage extrusion for alloy of the Ti–TiB n system is demonstrated, with which in the first stage preliminary crushing of harder strengthening phase TiB n is provided by deformation under all-round compression conditions and large shear strains, and in the second stage there is direct extrusion of a blade vane under conditions close to isothermal. It is shown that the processes implemented provide an increase in workpiece mechanical property ultimate strength compared with a cast structure within the blade root by 10–16%, and by 17–20% within the body of the blade vane.
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