Very interesting post above from Micahael Birbeck with all the great links
A couple of comments.
The engine surging shown in the model testing ain't the same as what was first discussed in this thread, but it's entertaining just the same. The model testing shown in the first links is with a centrifugal impeller and not an axial flow compressor with blades and vanes. hence the aerodynamic effects of aifoil stall leading to surging are unlikely. The gross surge event seen in the early video might be only a burner stability issue
The dependence on rotating stall (in the document link) of the axial compressor to limit turbine overspeed in a shaft separation event does have merit for a multi-spool/shaft machine protecting the aft low speed fan-drive turbine should a turbine drive shaft fail. However for a multi spool machine the separation of the high turbine drive shaft will still have enough air left in the burner behind the compressor to drive that turbine way above red-line operating speeds.
In the later sequence videos of fan blade failure testing RR-GE & P&W engines are shown. In some of these sequences you can see behind the fan the generation of an engine surge as a ball of incandescence flame spiraling forward through the fan blades.
And last but not least, all pilots should pay attention to the surge recognition video link posted above. That whole study and recognition program was the direct result of lots of data studies showing that most pilots did not understand the instruments, sounds or vibrations associated with a high power surge event in the current generation engines.