Found a pdf that I think you will sorry if this has bin posted.
http://www.dtic.mil/cgi-bin/GetTRDoc?Location=U2&doc=GetTRDoc.pdf&AD=AD0378498
PRATT & WHITNEY JTF17A
Type: Two-shaft axial turbofan with duct heater.
Intake: Annular, titanium, no inlet guide vanes.
Compressor: Low pressure system consists of titanium case, two fan stages, titanium & Waspaloy blades & disks, bypass ratio 1.3:1, mass flow 687 lbs/sec.
High pressure system consists of titanium case, six compressor stages, titanium and Waspaloy blades & disks, compression ratio 13:1.
Combustor: Gas generator and duct heater combustors are advanced annular ram induction burner designs housed in Waspaloy cases. No diffusers - - velocity head of air provides a turbulent burning zone.
Turbine: High Pressure turbine is one stage, air cooled, with cobalt-nickel alloy disk and cobalt-nickel alloy blades, directionally solidified precision cast method, in Waspaloy case. Turbine Inlet Temperature is 2,200 degrees F, 2,300 degrees F for takeoff only.
Low Pressure turbine is two stages; otherwise same as high pressure turbine.
Exhaust: Reverser/Suppressor section with fixed convergent-divergent exhaust nozzle for primary gas stream, variable nozzle on duct exhaust, variable ejector, clamshell doors inside R/S section, aerodynamically actuated flaps at end of R/S section, tertiary air blow-in doors at front of R/S section, integrated advanced thrust reversal and noise suppression system.
Dimensions: Inlet diameter - 69.3", Reverser/Suppressor diameter - 80", Length - 215"
Weight: 10,500 lbs
Performance:
Thrust Conditions Rating SFC
Takeoff - augmented, SLS: 61,000 lbs 1.78
Takeoff - dry, SLS: 38,300 lbs 0.76
M2.7 Cruise - partial augmentation: 12,770 lbs 1.56
M0.9 Cruise - partial power: 5,010 lbs 1.10