Wasn't the Sioux City DC10 accident a result of uncontained failure of the LP compressor disc.
Sioux City was a fan disc, not a compressor disc. For purposes of rotor burst analysis, a 1/3 fan disc is assumed to have infinite energy - hence my earlier comment that it would go anywhere it wanted to. Nothing on the aircraft is going to stop it (or even slow it significantly).
While a compressor spool doesn't have the energy of a fan disc, a failed spool is effectively a burst rotor. As noted before, it's not going to be contained by the compressor case, at least not at high power. When we do uncontained burst analysis, there are certain assumptions that come into play. Blades and blade bits are considered 'low energy' - if they make it out of the engine case they won't penetrate 'protected' systems, however they can spread over a wider area (15 degree spread, vs. 5 degrees for high energy debris). Rotors and spools are considered 'high' energy, it's simply not practical to protect systems. Rather, systems are located to minimize (but not eliminate) the risk of catastrophic damage.
It really is an interesting question as to what would have happened had this failure occurred after V1 and they'd continued the takeoff. My gut feeling is it wouldn't have been catastrophic - assuming the fuel leak was from the engine fuel line (and not a wing penetration), most of the spilled fuel would have gone out the back. It would certainly have been exciting, and a return to land with a trans-Atlantic fuel load, but something a capable crew (which this one showed every sign of being) would have been able to handle.
Hopefully the final report will address those aspects of survivability had the failure occurred 30 seconds later.