COMPRESSOR

    • Low Pressure Compressor - 9 Axial Flow Stages (1st Stage is Supersonic), Variable IGV, Stage 1 and 2 Stator Vanes
    • High Pressure Compressor - 9 Axial Flow Stages
    • Compression Ratio 21.8:1

    COMBUSTOR

    • Canular Reverse Flow with 16 Flame Tubes
    • Two Igniters
    • Natural Gas or Distillate Fuel

    COMPRESSOR TURBINES

    • One Axial Stage for each Rotor
    • Air-Cooled Turbine Blades and Stator Segments

    COMPRESSOR ROTOR
    BEARING SYSTEMS

    • Ball Radial/Thrust Bearing  at the front and Roller Radial Bearing arrangement at the rear on LP and HP Rotors, both with Squeeze Film Dampers
    • Squeeze Film Dampers are used to reduce the dynamic bearing loads and casing vibration level

    POWER TURBINE

    • 4 Axial Stages (Electrical Generator Drive)
    • Radial Roller Bearing at the front and Radial Ball and Oil Film Thrust Bearing arrangement at the rear

    DATA AT RATED POWER
    AND ISO 2314 CONDITIONS

    • Mass Flow 88 kg/s (194 lbs/sec)
    • Exhaust Temperature 475 0C (887 0F)
    • Output Power: 27.5 MW at Shaft Flange
    • Efficiency: 36.0%

Copyright   © 2003 Magellan Aerospace Corporation