ratio associated with the lpt 46 is pressure measured prior to the inlet of the lpt 46 as related to the pressure at the outlet of the lpt 46 prior to an exhaust nozzle of the gas turbine engine 20 in one non limiting embodiment the bypass ratio of the gas turbine engine 20 is greater than about ten 10 1 the fan diameter is significantly larger than that of the lpc 44 and the lpt 46 has a pressure ratio that is greater than about five 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 disclosure is applicable to other gas turbine engines including direct drive turbofans in one non limiting embodiment a significant amount of thrust is provided by the bypass flow 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 this flight condition with the gas turbine engine 20 at its best fuel consumption is also known as bucket cruise thrust specific fuel consumption tsfc tsfc is an industry standard parameter of fuel consumption per unit of thrust fan pressure ratio is the pressure ratio across a blade of the fan section 22 without a fan exit guide vane system the low fan pressure ratio according to one non limiting embodiment of the example gas turbine engine 20 is less than 1 45 low corrected fan tip speed is the actual fan tip speed divided by an industry standard temperature correction of u201c t u201d 518 7 0 5 in which u201c t u201d represents the ambient.