| 摘要 |
FIELD: mechanical engineering; gas-turbine engines. ^ SUBSTANCE: invention relates to compressors of gas-turbine engines of aircraft and ground application. According to invention, in compressor of gas-turbine engine whose rotor includes splined shaft and fitted-on disks tightened on hubs by nuts, part of disks is provided with one row of splines made for hubs of adjacent disks, spline of at least one disk of first stage with one row of splines is made form side of compressor outlet and D/L-2-8; L/l=3-12 where D is inner diameter of disk hub; L is distance from splines to disk plate; 1 is axial length of disk spline in middle diameter. ^ EFFECT: improved reliability and reduced weight of compressor owing to increase of radial rigidity and reduction of rotor weight by decreasing distance between compressor support and optimization of arrangement of rotor disk splines in non-loaded zone. ^ 3 dwg |
