Turbofan gas turbine engine with gearbox

Patent metadata

Field	Value
Publication number	US-11313438-B2
Application number	US-201916515733-A
Country	US
Kind code	B2
Filing date	Jul 18, 2019
Priority date	Jul 18, 2019
Publication date	Apr 26, 2022
Grant date	Apr 26, 2022

Abstract

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 rate. The output shaft is coupled to the fan to drive the fan at the reduced rate and provide trust for the gas turbine engine.

First claim

What is claimed is:

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, and the first-stage gear and the second-stage gears each having diameters that are smaller than a diameter of the sun gear,
wherein the gearbox includes seven or more compound gears, and
wherein the first-stage gear has a face width of up to 40 mm and the second-stage gear has a face width of up to 55 mm.

2. The gas turbine engine of claim 1 , wherein the sun gear and the ring gear have a gear ratio within a range of about 3 to about 5 and the gearbox includes up to seven compound gears.

3. The gas turbine engine of claim 2 , wherein a ratio of the diameter of the sun gear to the diameter of the ring gear is within a range of about 0.2 to about 0.6.

4. The gas turbine engine of claim 3 , wherein the ratio of the diameter of the sun gear to the diameter of the ring gear is within a range of about 0.4 to about 0.6.

5. The gas turbine engine of claim 4 , wherein the ratio of the diameter of the sun gear to the diameter of the ring gear is within a range of about 0.46 to about 0.53.

6. The gas turbine engine of claim 5 , wherein the ratio of the diameter of the sun gear to the diameter of the ring gear is greater than 0.5.

7. The gas turbine engine of claim 3 , wherein the ratio of the diameter of the sun gear to the diameter of the ring gear is within a range of about 0.23 to about 0.57.

8. The gas turbine engine of claim 4 , wherein the ratio of the diameter of the sun gear to the diameter of the ring gear is within a range of about 0.25 to about 0.54.

9. The gas turbine engine of claim 2 , wherein the sun gear and the ring gear have a gear ratio within a range of about 3 to about 4.5.

10. The gas turbine engine of claim 5 , wherein the ratio of the diameter of the sun gear to the diameter of the ring gear is within a range of about 0.23 to about 0.53.

11. The gas turbine engine of claim 10 , wherein the ratio of the diameter of the sun gear to the diameter of the ring gear is within a range of about 0.4 to about 0.6.

12. The gas turbine engine of claim 11 , wherein the ratio of the diameter of the sun gear to the diameter of the ring gear is within a range of about 0.46 to about 0.53.

13. The gas turbine engine of claim 12 , wherein the ratio of the diameter of the sun gear to the diameter of the ring gear is greater than 0.5.

14. The gas turbine engine of claim 2 , wherein the sun gear and the ring gear have a gear ratio within a range of about 3.5 to about 4.

15. The gas turbine engine of claim 14 , wherein the ratio of the diameter of the sun gear to the diameter of the ring gear is within a range of about 0.44 to about 0.55.

16. The gas turbine engine of claim 15 , wherein the ratio of the diameter of the sun gear to the diameter of the ring gear is greater than 0.5.

17. The gas turbine engine of claim 1 , wherein a ratio of the diameter of the first-stage gear to the diameter of the ring gear is within a range of about 0.3 to about 0.4.

18. The gas turbine engine of claim 17 , wherein the ratio of the diameter of the first-stage gear to the diameter of the ring gear is within a range of about 0.32 to about 0.36.

19. The gas turbine engine of claim 1 , wherein a ratio of the diameter of the first-stage gear to the diameter of the ring gear is within a range of about 0.1 to about 0.2.

20. The gas turbine engine of claim 19 , wherein the ratio of the diameter of the first-stage gear to the diameter of the ring gear is within a range of about 0.14 to about 0.19.

Assignees

• Rolls Royce Plc

Inventors

• Spruce Mark

Classifications

• F16H55/17

  Toothed wheels (worm wheels F16H55/22; chain wheels F16H55/30) · CPC title

• F16H1/28 Primary

  with gears having orbital motion · CPC title

• F02K3/06

  with front fan · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F02C3/06

  the compressor comprising only axial stages (F02C3/10 takes precedence) · CPC title