Gas turbine engine with geared architecture

A geared architecture for a gas turbine engine comprising:

• a fan shaft and a fan supported on said fan shaft and defining a bypass flow ratio greater than about six;
• a frame which supports said fan shaft;
• a gear system which drives said fan shaft, said gear system having a gear reduction ratio of greater than or equal to about 2.3;
• a torque frame which at least partially supports said gear system;
• an input coupling to said gear system;
• and
• a low pressure turbine coupled to rotatably drive said input coupling, said low pressure turbine defining a pressure ratio that is greater than about five (5).