Thanks everyone for the quick reaction (
). I'm nearly there, but I need some more information.
A special thank you to Capt Pit Bull who made my day:
Rocket engineering on the other hand is quite tricky
PBL, I had discovered the NASA site after I posted and it is very helpful.
On the first page, the EPR formula is quoted:
EPR = pt8 / pt2 = (pt3 / pt2) * (pt4 / pt3) * (pt5 / pt4) * (pt8 / pt5)
EPR = compressor pressure ratio * burner pressure ratio * turbine pressure ratio * nozzle pressure ratio
I can see that the compressor pressure ratio is greater than 1.0 and therefore exerts a forward force. The compressor forces are transmitted through thrust bearings and the stator blade tip forces directly to the engine casing. What about the stator root forces? Through the thrust bearing support structure?
I can also see that the turbine will exert a backward force on the engine, again through thrust bearings (and stators?).
What about the burner cans and the nozzle? The NASA Java model default settings show no thrust for either of these (
PR = 1.0). I thought the nozzle in particular was carefully designed to provide a thrust increment. If so, what does this thrust react against?