Gas turbine engine with geared architecture

Abstract

A geared architecture with a flex mount for a fan drive gear system.

1 . A geared architecture for a gas turbine engine comprising:
 a fan shaft;   a frame which supports said fan shaft;   a gear system which drives said fan shaft;   a torque frame which at least partially supports said gear system; and   an input coupling to said gear system.   
     
     
         2 . The geared architecture as recited in  claim 1 , wherein said frame and said torque frame are mounted to a fixed structure. 
     
     
         3 . The geared architecture as recited in  claim 1 , wherein said frame and said torque frame are mounted to a front center body of a gas turbine engine. 
     
     
         4 . The geared architecture as recited in  claim 1 , wherein said torque frame is mounted to a planet carrier of said gear system. 
     
     
         5 . The geared architecture as recited in  claim 4 , wherein said input coupling is mounted to a sun gear of said gear system. 
     
     
         6 . The geared architecture as recited in  claim 5 , wherein said fan shaft is mounted to a ring gear of said gear system. 
     
     
         7 . The geared architecture as recited in  claim 6 , wherein said gear system is a star system. 
     
     
         8 . The geared architecture as recited in  claim 1 , wherein said torque frame is mounted to a ring gear of said gear system. 
     
     
         9 . The geared architecture as recited in  claim 8 , wherein said input coupling is mounted to a sun gear of said gear system. 
     
     
         10 . The geared architecture as recited in  claim 9 , wherein said fan shaft is mounted to a star carrier of said gear system. 
     
     
         11 . The geared architecture as recited in  claim 10 , wherein said gear system is a planet system. 
     
     
         12 . The geared architecture as recited in  claim 1 , wherein a bypass flow defines a bypass ratio greater than about ten (10). 
     
     
         13 . The geared architecture as recited in  claim 1 , wherein said system includes a gear train that defines a gear reduction ratio of greater than or equal to about 2.3. 
     
     
         14 . The geared architecture as recited in  claim 1 , wherein said system includes gear train that defines a gear reduction ratio of greater than or equal to about 2.5. 
     
     
         15 . The geared architecture as recited in  claim 1 , further comprising a low pressure turbine, wherein said low pressure turbine defines a pressure ratio that is greater than about five (5).