A gas turbine engine includes a drive turbine, a fan, and a gearbox. The fan has a fan blade defining a leading edge fan radius RFan_LE and a trailing edge fan radius RFan_TE, and the fan defining a leading edge hub radius RHub_LE and a trailing edge hub radius RHub_TE. The gearbox mechanically couples the drive turbine to the fan. The gas turbine engine defines a Fan Leading Edge to Trailing Edge Compression Factor (FLTCF) greater than or equal to 1.05 and less than or equal to 1.8. The drive turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage divided by the annular exit area of a forward-most rotating stage. In some instances, the area ratio is within a range of 2.0-6.5. Additionally (or alternatively), the low-pressure turbine includes an area-EGT ratio within a range of 1.05-1.6.