FIELD: engines.
SUBSTANCE: first stage compressor disc (221) of gas turbine engine (100) and a method for balancing rotor (230) of gas turbine engine compressor (100). First stage compressor disc (221) of gas turbine engine compressor (100) comprises housing (240). Housing (240) has forward end (238), aft end (239) and outer surface (241). Housing (240) also includes a plurality of forward balancing holes (242) extending through outer surface (241). Forward balancing holes (242) are circumferentially aligned around housing (240). Housing (240) also includes a plurality of aft balancing holes (243) extending through the outer surface (241). Aft balancing holes (243) are circumferentially aligned around housing (240) and are located behind forward balancing holes (242). First stage compressor disc (221) also comprises radial flange (246) at the rear end of housing (240). Radial flange (246) extends radially outward from housing (240). Radial flange (246) includes grooves (247) for positioning blades (235).
EFFECT: as a result of extensive research and testing it has been found that for some large gas turbine engines, a more dynamic system and balancing method can be achieved.
10 cl, 6 dwg
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