3 2 3 1 the low pressure turbine 46 has a pressure ratio that is greater than about five 5 1 the low pressure turbine 46 pressure ratio is pressure measured prior to inlet of low pressure turbine 46 as related to the pressure at the outlet of the low pressure turbine 46 prior to an exhaust nozzle in one disclosed embodiment the gas turbine engine 20 bypass ratio is greater than about ten 10 1 and the fan diameter is significantly larger than that of the low pressure compressor 44 the low pressure turbine 46 has a pressure ratio that is greater than about five 5 1 the geared architecture 48 may be an epicycle gear train such as a planetary gear system or other gear system with a gear reduction ratio of greater than about 2 5 2 5 1 it should be understood however that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present invention is applicable to other gas turbine engines including direct drive turbofans a significant amount of thrust is provided by the bypass flow b due to the high bypass ratio the fan section 22 of the gas turbine engine 20 is designed for a particular flight condition u2014 typically cruise at about 0 8 mach and about 35 000 feet the flight condition of 0 8 mach and.