Geared turbofan with four star/planetary gear reduction
A gas turbine engine has a fan rotor, a turbine rotor driving the fan rotor, and an epicyclic gear reduction positioned between the fan rotor and the turbine rotor. The epicyclic gear reduction includes a ring gear, a sun gear, and no more than four intermediate gears that engage the sun gear and the ring gear. The fan drive turbine is configured to drive the sun gear to, in turn, drive the ring gears to, in turn, drive the fan rotor.
1. A gas turbine engine comprising:
a fan rotor mounted within a nacelle and for delivering air into a bypass duct with said nacelle and into a low pressure compressor;
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 no more than four star gears that engage said sun gear and said ring gear,
wherein said turbine rotor is for driving said sun gear to, in turn, drive said star gears to, in turn, drive said fan rotor;
said turbine rotor for driving said low pressure compressor at a common speed, and driving said sun gear to drive said fan rotor at a reduced speed; 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, wherein said spacing angle is at least 30 degrees.
2. The gas turbine engine as set forth in claim 1 , wherein said spacing angle is 45 degrees.
3. The gas turbine engine as set forth in claim 1 , wherein said bypass ratio is defined as a volume of air delivered by said fan into a bypass duct compared to a volume of air delivered into said compressor, wherein said bypass ratio is greater than or equal to 12.0.
4. The gas turbine engine as set forth in claim 3 , 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.
5. The gas turbine engine as set forth in claim 4 , wherein said gear ratio is greater than or equal to 4.0.
6. The gas turbine engine as set forth in claim 5 , wherein said gear ratio is greater than or equal to 4.2.
7. The gas turbine engine as set forth in claim 6 , wherein said gear ratio is less than or equal to 4.4.
8. The gas turbine engine as set forth in claim 5 , wherein said fan drive turbine having three or four stages of blades.
9. The gas turbine engine as set forth in claim 5 , wherein an auxiliary oil supply system provides oil to journal bearings associated with said four star gears during a windmilling condition of said fan rotor.
10. The gas turbine engine as set forth in claim 5 , wherein at least one blade row in said turbine rotor has blades formed of a directionally solidified material.
11. The gas turbine engine as set forth in claim 1 , 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.
12. The gas turbine engine as set forth in claim 11 , wherein said gear ratio is greater than or equal to 4.0.
13. The gas turbine engine as set forth in claim 12 , wherein said gear ratio is greater than or equal to 4.2.
14. The gas turbine engine as set forth in claim 1 , wherein said fan drive turbine having three or four stages of blades.
15. The gas turbine engine as set forth in claim 1 , wherein an auxiliary oil supply system provides oil to journal bearings associated with said four star gears during a windmilling condition of said fan rotor.
16. The gas turbine engine as set forth in claim 1 , wherein at least one blade row in said turbine rotor has blades formed of a directionally solidified material.