COMPRESSOR

    • Low Pressure Compressor - 8 Axial Flow Stages, Variable Inlet Guide Vanes
    • High Pressure Compressor - 9 Axial Flow Stages
    • Compression Ratio 13.7:1

    COMBUSTOR

    • Canular Reverse Flow with 10 Flame Tubes
    • Two Igniters
    • Natural Gas or Distillate Fuel

    COMPRESSOR TURBINES

    • One Axial Stage for each Rotor

    COMPRESSOR ROTOR
    BEARING SYSTEMS

    • Ball Radial/Thrust Bearing at the front and Radial Roller Bearing at the rear on LP Rotor
    • Ball Radial/Thrust Bearing at the front and Radial Roller Bearing with Squeeze Film Dampers at the rear on HP Rotor

    POWER TURBINE

    • 3 Axial Stages (7,200 RPM Nominal), or 6 Axial Stages (3,000/3,600 RPM Nominal)
    • Radial Roller Bearing at the front with Duplex Ball Radial/ Thrust Bearing Arrangement at the rear

    DATA AT RATED POWER
    AND ISO 2314 CONDITIONS

    • Mass Flow 30 kg/s (66.1 lbs/sec)
    • Exhaust Temperature 405 0C (761 0F)
    • Output Power: 6.7 MW at Shaft Flange
    • Efficiency: 31.5%

Copyright   © 2003 Magellan Aerospace Corporation