Is this merely indicative that most of the compression is coming from the inlet rather than the compressor?
That question is exactly what is discussed in the reddit link i posted. So it was perfectly on topic.
Regarding the thrust load i get the impression we need to clarify what the rotor is, i would assume it's the complete rotating spool of the engine yes?
In normal operational circumstances of a turbojet I'd expect a fairly large axial drag component on the rotor (negative thrust if you like, since the turbine is driving the compressor)
Now we are discussing the direction/magnitude of the load on the thrust bearing of the spool of a turbojet.
That's equal to the combined aerodynamic axial load of compressor and turbine.
Turbine will be pulled backwards and the compressor will be pulled forwards.
Now why would you expect a large axial drag component?
Check the picture on this page:
http://aeromodelbasic.********.com/2...bution-of.html
Edit: why would this forum censor ********? anyway via link shortener
http://goo.gl/RbZFpY
Now if you shove air down the compressor as in the SR71 the forward thrust load on the compressor reduces so that the forces on the spool eventually sum up in the other direction.
The overall forces as described in the picture still need to sum up as a force thats forward for thrust to be produced. But there are forward components on other parts of the engine that take care of that.
If any turbojet is at idle or while the aircraft is at high speed i would also expect the thrust load on the rotor to become negative.
This could still happen while the engine as a whole is producing thrust as the combustion chamber for example is being pushed forwards while the rotor is being pushed backwards a bit.
Anyhow clarify what exactly it is you are asking or what you are not clear about and i'm sure there will be some more answers.