COMPRESSOR

    • 9 Axial Flow Stages (Variable Inlet Guide Vanes) plus one Centrifugal Stage
    • Compression Ratio 12:1

    COMBUSTOR

    • Two Tubular Radial Flame Tubes (each with an Igniter)
    • Natural Gas or Distillate Fuel

    TURBINE

    • Three Axial Stages

    ROTOR

    • Speed: 14,000 RPM
    • Tilt Pad Thrust & Journal Bearings at the front and Radial Roller Bearing at the rear
    • Integral Epicyclic Speed Reduction Gearbox

    DATA AT RATED POWER
    AND ISO 2314 CONDITIONS

    • Mass Flow 15 kg/s (33 lbs/sec)
    • Exhaust Temperature 435 0C (815 0F)
    • Output Power: 2.85 MW at Shaft Flange
    • Efficiency: 28.5%

Copyright   © 2003 Magellan Aerospace Corporation