GAS TURBINE ENGINE WITH HIGHER LOW SPOOL TORQUE-TO-THRUST RATIO

A gas turbine engine (20) includes a fan drive turbine driving a low pressure compressor (44), and driving a gear reduction to in turn drive a fan rotor (42) at a speed slower than the fan drive turbine. The turbine section (28) further includes a high pressure turbine (54) driving the high pressure compressor (52). The fan drive turbine and low pressure compressor (44) are connected by a shaft (40) and the fan drive turbine, the shaft (40) and the low pressure compressor (44) define a low pressure spool. The gas turbine engine (20) is rated to provide an amount of thrust at maximum takeoff, and a low spool thrust ratio defined as a ratio of a torque on the low pressure spool at maximum takeoff in ft-lbs and the maximum takeoff thrust being defined in lbf, with the low spool torque ratio being greater than or equal to 0.70 ft-lb/lbf (0.21 Nm/N), and less than or equal to 1.2 ft-lb/lbf (0.37 Nm/N).