FIRST STAGE COMPRESSOR DISK CONFIGURED FOR BALANCING THE COMPRESSOR ROTOR ASSEMBLY

摘要

A first stage compressor disk (221) of a gas turbine engine (100) includes a body (240). The body (240) includes a forward end (238) an aft end (239) and an outer surface (241). The body (240) also includes a plurality of forward balancing holes (242) through the outer surface (241). The forward balancing holes (242) align circumferentially about the body (240). The body (240) further includes a plurality of aft balancing holes (243) through the outer surface (241). The aft balancing holes (243) align circumferentially about the body (240) and are located aft of the forward balancing holes (242). The first stage compressor disk (221) also includes a radial flange (246) at the aft end of the body (240). The radial flange (246) extends radially outward from the body (240). The radial flange (246) includes slots (247) for mounting airfoils (235).