| 摘要 |
FIELD: machine building.SUBSTANCE: drum rotor of an axial-flow compressor is designed for gas turbine engines, mainly, aircraft engines. Working blades (4) of the rotor are installed in grooves (2) arranged along the drum (1) length in circular rows by their butts (3). The blades (4) are fitted by the lower platform (6) of an airfoil (5) and a root (7). The root (7) is set between the platform (6) and the butt (3) with cross division of the upper butt (3) surface into two parts. The grooves (2) and the butts (3) installed in them are stretched along the outer drum (1) surface and are made as a right prism with its longitudinal section widening in the direction of the root (7). Strong rings (9) from composite material are mounted on the upper surfaces of the butts (3) with pretension, one ring is provided at least per every circular row of parts of upper butt surfaces.EFFECT: reduced radial and circumferential stresses in the drum material in the course of operation, provision for the reduction of the drum weight at design stage and significant increase of rotor tip speeds.4 dwg |
