Advanced Geared Gas Turbine Engine

1 . A gas turbine engine comprising:

a fan rotor driven by a fan drive turbine, said fan drive turbine also rotating with one of a ring gear, an intermediate gear carrier, and a sun gear;

a first compressor driven by another of said ring gear, said intermediate gear carrier, and said sun gear; and

a second turbine rotating with the third of said ring gear, said intermediate gear carrier, and said sun gear.

2 . The gas turbine engine as set forth in claim 1 , wherein a third turbine operates at a higher pressure than said second turbine or said fan drive turbine, and drives a second compressor, said second compressor operating at higher speeds than said first compressor.

3 . The gas turbine engine as set forth in claim 2 , wherein said fan drive turbine rotates said ring gear.

4 . The gas turbine engine as set forth in claim 3 , wherein said intermediate gear carrier rotates with said second turbine.

5 . The gas turbine engine as set forth in claim 4 , wherein said sun gear is an output gear driving said first compressor section.

6 . The gas turbine engine as set forth in claim 5 , wherein said intermediate gear carrier rotating with a plurality of intermediate gears, said intermediate gears engaged with said ring gear and said sun gear.

7 . The gas turbine engine as set forth in claim 6 , wherein relative speed between said ring gear, said intermediate gear carrier, and said sun gear are controlled during different operational conditions.

8 . The gas turbine engine as set forth in claim 7 , wherein a control may operate to control at least one of a variable inlet guide vane leading to said first compressor, or an amount of fuel delivered to a combustor in said gas turbine engine.

9 . The gas turbine engine as set forth in claim 8 , wherein structure is provided for preventing rotation of said first compressor in an undesired direction.

10 . The gas turbine engine as set forth in claim 1 , wherein a third turbine operates at a higher pressure than said second turbine or said fan drive turbine, and drives a second compressor, said second compressor operating at higher speeds than said first compressor.

11 . The gas turbine engine as set forth in claim 10 , wherein said fan drive turbine rotates said ring gear.

12 . The gas turbine engine as set forth in claim 11 , wherein said intermediate gear carrier rotates with said second turbine.

13 . The gas turbine engine as set forth in claim 12 , wherein said sun gear is an output gear driving said first compressor section.

14 . The gas turbine engine as set forth in claim 13 , wherein said intermediate gear carrier rotating with a plurality of intermediate gears, said intermediate gears engaged with said ring gear and said sun gear.

15 . The gas turbine engine as set forth in claim 1 , wherein relative speed between said ring gear, said intermediate gear carrier, and said sun gear are controlled during different operational conditions.

16 . The gas turbine engine as set forth in claim 15 , wherein a control may operate to control at least one of a variable inlet guide vane leading to said first compressor, or an amount of fuel delivered to a combustor in said gas turbine engine.

17 . The gas turbine engine as set forth in claim 16 , wherein structure is provided for preventing rotation of said first compressor in an undesired direction.

18 . The gas turbine engine as set forth in claim 1 , wherein said fan drive turbine rotates said ring gear.

19 . The gas turbine engine as set forth in claim 18 , wherein said intermediate gear carrier rotates with said second turbine.

20 . The gas turbine engine as set forth in claim 19 , wherein said sun gear is an output gear driving said first compressor section.