Turbofan gas turbine engine with gearbox
View Patent ↗A gas turbine engine includes an engine core, a fan and a gearbox interconnecting the engine core and the fan. The engine core is configured to drive rotation of at least one shaft. The power gearbox is configured to transfer torque from the at least one shaft to an output shaft at a reduced rotational speed. The output shaft is coupled to the fan to drive the fan at the reduced speed and provide trust for the gas turbine engine.
1. A gas turbine engine comprising an engine core including, a compressor, a combustor, and a turbine arranged along a reference axis, the turbine configured to drive rotation of a power shaft about the reference axis during operation of the gas turbine engine,
a fan driven in rotation about the reference axis by an output shaft, and
a gearbox interconnecting the output shaft and the power shaft to transfer rotational energy from the turbine to the fan during operation of the gas turbine engine, the gearbox including (i) a sun gear coupled with the power shaft for rotation about the reference axis with the power shaft, (ii) a plurality of compound gears coupled with the sun gear and spaced circumferentially around the reference axis from one another, each compound gear driven in rotation by the sun gear about a compound-gear axis that is fixed in position relative to the reference axis, and (iii) a ring gear coupled with each of the compound gears and the output shaft to transfer the rotational energy from the plurality of compound gears to the output shaft to drive rotation of the fan,
wherein each compound gear includes a first-stage gear coupled with the sun gear, a second-stage gear spaced axially from the first-stage gear and coupled with the ring gear, and a compound-gear shaft interconnecting the first-stage gear and the second-stage gear to cause the first-stage gear and the second-stage gear to rotate together, the first-stage gear and the second-stage gears having diameters that are smaller than a diameter of the sun gear, and
wherein the gearbox includes seven or more compound gears and the ratio of the diameter of the sun gear to the diameter of the ring gear is within a range of 0.2 to 0.6.
2. The gas turbine engine of claim 1 , wherein the first-stage gear has a face width of up to about 40 mm.
3. The gas turbine engine of claim 2 , wherein the first-stage gear has a face width within a range of about 10 mm to about 40 mm.
4. The gas turbine engine of claim 3 , wherein the plurality of compound gears includes an odd number of compound gears.
5. The gas turbine engine of claim 2 , wherein the first-stage gear has a face width-to-diameter ratio of up to about 0.12.
6. The gas turbine engine of claim 5 , wherein the first-stage gear has a face width-to-diameter ratio within a range of about 0.02 to about 0.12.
7. The gas turbine engine of claim 2 , wherein the first-stage gear has a face width-to-fan power ratio of up to about 0.8 mm/MW.
8. The gas turbine engine of claim 2 , wherein the first-stage gear has a face width-to-gearbox input torque ratio of up to about 0.5 mm/kNm.
9. The gas turbine engine of claim 2 , wherein the first-stage gear has a face width-to-pinion gear diameter ratio of up to about 0.2.
10. The gas turbine engine of claim 2 , wherein the first stage gear has a face width-to-fan diameter ratio of up to about 0.014.
11. The gas turbine engine of claim 10 , wherein the first-stage gear has a face width-to-fan diameter ratio within a range of about 0.002 to about 0.014.
12. The gas turbine engine of claim 1 , wherein the second-stage gear has a face width of up to about 55 mm.
13. The gas turbine engine of claim 12 , wherein the second-stage gear has a face width within a range of about 15 mm to about 55 mm.
14. The gas turbine engine of claim 12 , wherein the second-stage gear has a face width-to-diameter ratio of up to about 0.08.
15. The gas turbine engine of claim 14 , wherein the second-stage gear has a face width-to-diameter ratio of within a range of about 0.015 to about 0.08.
16. The gas turbine engine of claim 12 , wherein the second-stage gear has a face width-to-fan power ratio of up to about 1.1 mm/MW.
17. The gas turbine engine of claim 12 , wherein the second-stage gear has a face width-to-gearbox input torque ratio of up to about 1 mm/kNm.
18. The gas turbine engine of claim 12 , wherein the second-stage gear has a face width-to-pinion gear diameter ratio of up to about 0.6.
19. The gas turbine engine of claim 12 , wherein the second-stage gear has a face width-to-fan diameter ratio of up to about 0.02.
20. The gas turbine engine of claim 19 , wherein the second-stage gear has a face width-to-fan diameter ratio within a range of about 0.003 to about 0.019.