A gas turbine engine having, in operation, greater than or equal to 17,000 lbs (75.62 kN) of thrust and less than or equal to about 26,000 lbs (115.65 kN) of thrust, comprising: a fan rotor having a hub and a plurality of fan blades extending radially outwardly of said hub ; a compressor positioned downstream of the fan rotor, the compressor having a first compressor blade row defined along a rotational axis (A) of said fan rotor; and a gear reduction positioned axially between said first compressor blade row and said fan rotor, said gear reduction including a ring gear and a carrier , said carrier having an axial length (L 1 ) and said ring gear having an outer diameter (D 1 ), and said gear reduction is connected to drive said hub to rotate , wherein a volume is defined for said carrier and said ring gear , and said volume being designed to be greater than or equal to 899 inches 3 (14732 cm 3 ) and less than or equal to about 1349 inches 3 (22106.15 cm 3 ), the hub has a radius (r 1 ) defined at an inlet point of said hub , said fan blades have a radius (r 2 ), and a ratio of said hub radius (r 1 ) to said fan blade radius (r 2 ) is less than or equal to 0.36 and greater than or equal to 0.24, a gear ratio of said gear reduction is greater than or equal to 3.0, and an inlet into said compressor extends radially, inwardly along a surface from a radially outermost point to a point leading into said first compressor blade row , said gear reduction is positioned between said radially outermost point and said point leading into said first compressor blade row , and said point leading into said first compressor blade row is radially inward of said ring gear , characterised in that : a ratio of said axial length (L 1 ) to said outer diameter (D 1 ) is greater than or equal to 0.20 and less than or equal to 0.40. a fan rotor having a hub and a plurality of fan blades extending radially outwardly of said hub ; a compressor positioned downstream of the fan rotor, the compressor having a first compressor blade row defined along a rotational axis (A) of said fan rotor; and a gear reduction positioned axially between said first compressor blade row and said fan rotor, said gear reduction including a ring gear and a carrier , said carrier having an axial length (L 1 ) and said ring gear having an outer diameter (D 1 ), and said gear reduction is connected to drive said hub to rotate , wherein a volume is defined for said carrier and said ring gear , and said volume being designed to be greater than or equal to 899 inches 3 (14732 cm 3 ) and less than or equal to about 1349 inches 3 (22106.15 cm 3 ), the hub has a radius (r 1 ) defined at an inlet point of said hub , said fan blades have a radius (r 2 ), and a ratio of said hub radius (r 1 ) to said fan blade radius (r 2 ) is less than or equal to 0.36 and greater than or equal to 0.24, a gear ratio of said gear reduction is greater than or equal to 3.0, and an inlet into said compressor extends radially, inwardly along a surface from a radially outermost point to a point leading into said first compressor blade row , said gear reduction is positioned between said radially outermost point and said point leading into said first compressor blade row , and said point leading into said first compressor blade row is radially inward of said ring gear , characterised in that : a ratio of said axial length (L 1 ) to said outer diameter (D 1 ) is greater than or equal to 0.20 and less than or equal to 0.40. <EOS>