TECHNIQUE D'ÉQUILIBRAGE D'UN ROTOR DE COMPRESSEUR D'UNE TURBINE À GAZ

摘要

A method for low-speed balancing of a rotor having at least one compressor stage blades assembly is presented. The assembly has a row of blades circumferentially arranged and includes a circumferential clearance. Two or more blades are identified as located blades, each having an angular position in the assembly, at which the located blades are maintained. The located blades define sectors in the assembly. Each sector includes movable blades and sectoral circumferential clearances, i.e. the circumferential clearance subdivided into sectors. The movable blades, for each sector, are circumferentially adjusted such that the sectoral circumferential clearance of the sector moves circumferentially downstream relative to the movable blades with respect to a rotational direction when the assembly is rotated. Relative position of the sectoral circumferential clearances and the movable blades within each sector is maintained by introducing inserts. Finally, a measure of unbalance is determined for the rotor in low-speed balancing conditions.