Th e paper investigates the process of intensifying the fi nishing treatment of full-scale gas turbine engine compressor disks
made of diffi cult-to-machine titanium (VT3-1, VT9) and heat-resistant (EI698-VD) alloys in an abrasive fl uidized bed (AFB).
Th e problem of replacing labor-intensive manual operations with automated methods to ensure high fatigue strength and
reliability of highly loaded complex-profi le parts is considered.
Th e regularities in the eff ects of abrasive medium composition and low-frequency vibrations on process productivity and
surface layer quality have been experimentally established. It is shown that using a multicomponent mixture of green silicon
carbide abrasive grains of 63C50 and 63C25 fractions at an equal mass ratio reduces machining time by 1.5 times compared
to the base single-fraction abrasive. Additional application of low-frequency vibrations at 20...55 Hz and an amplitude of 2...
3 mm to the workpiece ensures a further reduction in machining time.
It has been establ ished that the proposed method guarantees the preservation of the geometric dimensions of complex-profi
le parts within the drawing tolerances with minimal material removal on the disk web (0.01...0.04 mm). Th e process ensures
uniform rounding of sharp edges along the blade slot contour with a radius of 0.2...0.3 mm and eff ective polishing of the disk
web to a surface roughness of Ra = 0.63...1.25 μm.
It is experimentally proven that free abrasive machining does not lead to the degradation of the physical and mechanical
state of the surface: the microhardness remains unchanged, and the favorable compressive residual stresses formed during the
previous stages of fi nish turning are preserved at the level of 450...550 MPa at a depth of up to 140 μm.
It is noted that to eliminate the side eff ect of hole-chamfer erosion on the disk web, the technological process should include
their preliminary protection or postpone the chamfering operation to the fi nal stage.