Geared turbofan with four star/planetary gear reduction

1. A turbofan engine assembly comprising:

a nacelle; and

a turbofan engine comprising:

a fan including a fan rotor having fan blades, said nacelle enclosing said fan rotor and said blades;

a turbine rotor driving said fan rotor;

an epicyclic gear reduction positioned between said fan rotor and said turbine rotor, said epicyclic gear reduction including a ring gear, a sun gear, and four intermediate gears that engage said sun gear and said ring gear, a gear ratio of said gear reduction is greater than 3.06;

wherein said fan drive turbine drives said sun gear to, in turn, drive said fan rotor;

a bypass ratio is defined as a volume of air delivered by said fan into a bypass duct inward of said nacelle compared to a volume of air delivered into a compressor, said bypass ratio is greater than or equal to 12.0;

said sun gear defines a sun gear center axis and a top dead center point is defined at a vertically uppermost location of said ring gear, with a center point of a top two of said four intermediate gears being at a spacing angle from a line drawn between said top dead center point and said sun gear center axis, and said spacing angle is at least 30 degrees; and

wherein said intermediate gears are star gears.

2. The turbofan engine assembly as set forth in claim 1 , wherein said spacing angle is 45 degrees.

3. The turbofan engine assembly as set forth in claim 1 , wherein said gear ratio is greater than or equal to 4.0.

4. The turbofan engine assembly as set forth in claim 3 , wherein said gear ratio is greater than or equal to 4.2.

5. The turbofan engine assembly as set forth in claim 4 , wherein said gear ratio is less than or equal to 4.4.

6. The turbofan engine assembly as set forth in claim 5 , wherein at least one blade row in said turbine rotor has blades formed of a directionally solidified material.

7. The turbofan engine assembly as set forth in claim 1 , wherein at least one blade row in said turbine rotor has blades formed of a directionally solidified material.

8. The turbofan engine assembly as set forth in claim 7 , wherein said turbine rotor has greater than or equal to three stages.

9. The turbofan engine assembly as set forth in claim 1 , wherein at least one blade row in said turbine rotor has blades formed of a directionally solidified material.

10. The turbofan engine assembly as set forth in claim 1 , wherein said turbine rotor includes an inlet, an outlet and a pressure ratio of greater than 5, the pressure ratio being pressure measured prior to said inlet as related to pressure at said outlet prior to an exhaust nozzle.

11. The turbofan engine assembly as set forth in claim 10 , wherein said turbofan has a low fan pressure ratio of less than 1.45 measured across said fan blades alone, and a low corrected fan tip speed of the fan rotor is less than 1150 ft/second (350.5 meters/second).

12. The turbofan engine assembly as set forth in claim 7 , wherein said turbine rotor includes an inlet, an outlet and a pressure ratio of greater than 5, the pressure ratio being pressure measured prior to said inlet as related to pressure at said outlet prior to an exhaust nozzle.

13. The turbofan engine assembly as set forth in claim 12 , wherein said turbofan has a low fan pressure ratio of less than 1.45 measured across said fan blades alone, and a low corrected fan tip speed of the fan rotor is less than 1150 ft/second (350.5 meters/second).

14. The turbofan engine assembly as set forth in claim 3 , wherein said turbine rotor includes an inlet, an outlet and a pressure ratio of greater than 5, the pressure ratio being pressure measured prior to said inlet as related to pressure at said outlet prior to an exhaust nozzle.

15. The turbofan engine assembly as set forth in claim 14 , wherein said turbofan has a low fan pressure ratio of less than 1.45 measured across said fan blades alone, and a low corrected fan tip speed of the fan rotor is less than 1150 ft/second (350.5 meters/second).

16. A turbofan engine assembly comprising:

a nacelle; and

a turbofan engine comprising:

a fan including a fan rotor having fan blades, said nacelle enclosing said fan rotor and said blades;

a turbine rotor driving said fan rotor; and

an epicyclic gear reduction positioned between said fan rotor and said turbine rotor, said epicyclic gear reduction including a ring gear, a sun gear, and no more than four star gears that engage said sun gear and said ring gear;

wherein said fan drive turbine drives said sun gear to, in turn, drive said fan rotor;

a bypass ratio is defined as a volume of air delivered by said fan into a bypass duct inward of said nacelle compared to a volume of air delivered into a compressor, said bypass ratio is greater than or equal to 12.0;

wherein said turbine rotor includes an inlet, an outlet and a pressure ratio of greater than 5, the pressure ratio being pressure measured prior to said inlet as related to pressure at said outlet prior to an exhaust nozzle, and wherein said fan has a low fan pressure ratio of less than 1.45 measured across said fan blades alone, and a low corrected fan tip speed of the fan rotor is less than 1150 ft/second (350.5 meters/second); and

wherein said sun gear defines a sun gear center axis and a top dead center point is defined at a vertically uppermost location of said ring gear, with a center point of a top two of said four star gears being at a spacing angle from a line drawn between said top dead center point and said sun gear center axis, and said spacing angle is at least 15 degrees.

17. The turbofan engine assembly as set forth in claim 16 , wherein said spacing angle is at least 30 degrees.

18. The turbofan engine assembly as set forth in claim 16 , wherein said gear reduction having a gear ratio between the speed of a drive input to the sun gear, and an output speed of the fan rotor and said gear ratio being greater than or equal to 2.6.

19. The turbofan engine assembly as set forth in claim 18 , wherein said gear ratio is greater than or equal to 3.06.

20. The turbofan engine assembly as set forth in claim 19 , wherein said gear ratio is greater than or equal to 4.0.

21. The turbofan engine assembly as set forth in claim 20 , wherein said gear ratio is less than or equal to 4.4.

22. The turbofan engine assembly as set forth in claim 21 , wherein said fan drive turbine having three or four stages of blades.

23. The turbofan engine assembly as set forth in claim 22 , wherein at least one blade row in said turbine rotor has blades formed of a directionally solidified material.

24. The turbofan engine assembly as set forth in claim 18 , wherein said fan drive turbine having three or four stages of blades.

25. The turbofan engine assembly as set forth in claim 16 , wherein said fan drive turbine having three or four stages of blades.

26. The turbofan engine assembly as set forth in claim 25 , wherein at least one blade row in said turbine rotor has blades formed of a directionally solidified material.

27. The turbofan engine assembly as set forth in claim 16 , wherein at least one blade row in said turbine rotor has blades formed of a directionally solidified material.

28. The turbofan engine assembly as set forth in claim 27 , wherein said bypass ratio is greater than or equal to 14.0.

29. The turbofan engine assembly as set forth in claim 16 , wherein said bypass ratio is greater than or equal to 14.0.