FIELD: engines and pumps.
SUBSTANCE: present invention relates to a method of creating frequency inconsistency between blades of the vane wheel of a gas turbine engine relative to a selected vibration mode of a vane wheel containing a disc and N blades. Method comprises selecting vibration mode of vane wheel with k nodal diameters, wherein k is a natural integer different from zero, and if N is an even number different from N/2, wherein said eigenmode is a vibration mode in the operating range of the gas turbine engine. Displacement of blades is determined along the whole circle of vane wheel for each of two stationary deformation waves of equal frequency, which in combination generate torsion modal deformation of vane wheel in selected proper vibration mode. Based on determined displacement of blades for each of two stationary deformation waves, blades are determined, for which antinode of oscillation of the first of said stationary deformation waves corresponds to oscillation unit of second stationary deformation wave. Vane wheel protrusion or recess is made opposite each of said blades to separate two stationary deformation waves and to create frequency inconsistency between vane wheel blades relative to selected vibration mode. Another invention of the group relates to the gas turbine engine vane wheel, containing multiple protrusions or recesses made during implementation of the said method.
EFFECT: group of inventions makes it possible to reduce vibration of vane wheel of gas turbine engine during its operation.
8 cl, 20 dwg
