Model T63-A-700(250-C18) Gas Turbine Engine
Model and type
T63-A-700. Turboshaft, 2-shaft, 6-'stage axial and 1-stage centrifugal compressor, 1 combustion chamber, 2-stage gas generator turbine, 2-stage free power turbine.
1-piece steel air intake casing. hot bleed air anti-icing.
2-piece steel axial casing with 6 row of stator blades, bolted to magnesium alloy centrifugal diffuser. Pressure ratio 6.2:1. Air flow 3.0 Ib/sec/51,600 rpm.
Reverse flow combustion chamber. 1 dual fuel nozzle.
Steel casing with hollow nozzle vanes. 1st and 2nd-stage (gas generator) turbine wheels, Maximum inlet temperature 1,825 F (996C).
3rd and 4th-stage free turbine wheels integral shrouded blades, (power) attached to main gear train pinion and reduction gear
Fixed area dual ducts, with 40o upward exhaust.
Offset-down reduction gearbox, ratio 0.171:1(5.83:1). Output shafts with Internal splines at front and rear, 6,000 rpm.
Pneumatic-mechanical. Gas generator governor. Acceleration control. Power turbine governor. Torquemeter. Constant speed.
1 pesco fuel pump 600psi, with integral filter. Bendix control.
Bendix high-energy ignition. 1 igniter.
Return system, 120 psi.
Width and height
9.0 in and 22.5 in
Length and frontal area
40.8 in and 1.9 ft
136 Ib; 2.33 shp/Ib
JP-4 or JP-5
Oil spec; consumption
MIL-L-7808: 0.05 Ib/hr
317 shp at 35,000 power turbine rpm.
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