Geared turbofan with overspeed protection

A gas turbine engine comprises:

• a propulsor drive turbine driving a gear reduction, said gear reduction, in turn, driving a propulsor rotor, said fan rotor delivering air into a bypass duct as bypass air and into a compressor section as core flow;
• a forward bearing positioned between said gear reduction and said fan rotor and supporting said gear reduction, and a second bearing positioned aft of said gear reduction and supporting said gear reduction, and said second bearing being a thrust bearing;
• a propulsor turbine drive shaft driving said gear reduction;
• and
• a catcher provided to resist movement of said gear reduction and said propulsor rotor in an outer direction of said second bearing, said catcher being fixed to static structure, said static structure being radially outward of said forward bearing, and said catcher including a member having a radially inner location positioned forwardly of a radially outwardly extending flange which rotates with said propulsor drive shaft, said catcher being contacted by said flange should said gear reduction move in a forward direction, to resist said movement of said gear reduction, and said member being axially intermediate said forward bearing and said propulsor rotor.