Geared gas turbine engine

• US 10,487,917 B2
• Filed: 09/21/2016
• Issued: 11/26/2019
• Est. Priority Date: 10/15/2015
• Status: Active Grant

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Chmylkowski, Pawel B
• Primary Examiner(s): Brockman, Eldon T
• Application Number:
  US15/271,809
• Publication Number:
  US 20170108084A1
• Time in Patent Office: 1,161 Days
• CPC Class Codes: F01D 15/12 Combinations with mechanical gearing driven by multiple engines F01D13/00
• CPC Class Codes: F02C 7/36 Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H
• CPC Class Codes: F04D 29/053 Shafts
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2260/40311 of the epicyclical, planetary or differential type
• CPC Class Codes: F16H 1/28 with gears having orbital motion
• CPC Class Codes: F16H 1/2818 by allowing limited movement of the ring gear relative to the casing or shaft
• CPC Class Codes: F16H 1/34 involving gears essentially having intermeshing elements other than involute or cycloidal teeth in worm gearing F16H1/30
• CPC Class Codes: F16H 57/08 of gearings with members having orbital motion
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine comprises a gearbox comprising a sun gear, an annulus gear, a plurality of planet gears and a carrier. Each planet gear is rotatably mounted in the carrier by a bearing. The sun gear meshes with the planet gears and the planet gears mesh with the annulus gear. The sun gear, the planet gears and the annulus gear comprise helical gear teeth. The annulus gear is secured to a surrounding structure by a radially extending member. A face of the flange nearest the middle of the annulus gear is axially spaced from the middle of the annulus gear by a first distance. The reference diameter of the annulus gear is radially spaced from a point at which the radially extending member is secured to the surrounding structure by a second distance. The ratio of first distance to second distance is between and including 0.5 and 1.2 such that misalignment between the annulus gear and the planet gears is reduced to minimise vibrations, noise, stress and wear of the gearbox.

Claims

1. A gas turbine engine comprising a gearbox, the gearbox comprising:

a sun gear, an annulus gear, a plurality of planet gears, and a carrier,

each planet gear being rotatably mounted in the carrier by at least one bearing,

the sun gear meshing with the planet gears and the planet gears meshing with the annulus gear,

each of the sun gear, the planet gears, and the annulus gear comprising helical gear teeth, the helical gear teeth having a pressure angle and a helix angle,

the annulus gear being secured to a surrounding structure by a radially extending member, a face of the radially extending member nearest a middle of the annulus gear being axially spaced from the middle of the annulus gear by a first distance, a reference diameter of the annulus gear being radially spaced from a point at which the radially extending member is secured to the surrounding structure by a second distance, wherein

the first distance=(the second distance×

sin(the helix angle of the helical gear teeth))/tan (the pressure angle of the helical gear teeth).

2. The gas turbine engine as claimed in claim 1, wherein a ratio of the first distance to the second distance is between and including 0.5 and 1.2.

3. The gas turbine engine as claimed in claim 2, wherein the ratio of the first distance to the second distance is between and including 0.55 and 1.17.

4. The gas turbine engine as claimed in claim 2, wherein the ratio of the first distance to the second distance is between and including 0.60 and 1.10.

5. The gas turbine engine as claimed in claim 1, wherein each planet gear is rotatably mounted on the carrier by a bearing, the bearing is selected from a group consisting of a journal bearing and at least one rolling element bearing.

6. The gas turbine engine as claimed in claim 1, wherein the carrier is connected to an output shaft and the surrounding structure is a static structure.

7. The gas turbine engine as claimed in claim 1, wherein the carrier is connected to a static structure and the surrounding structure is an output shaft.

8. The gas turbine engine as claimed in claim 1, wherein the carrier is connected to an output shaft and the surrounding structure is connected to the output shaft.

9. The gas turbine engine as claimed in claim 1, wherein the radially extending member is a flange.

10. The gas turbine engine as claimed in claim 9, wherein the flange is secured to the surrounding structure by a bolted connection.

11. The gas turbine engine as claimed in claim 10, wherein the flange comprises a plurality of apertures for bolts of the bolted connection, axes of the apertures being arranged at a radial distance from an inner surface of the annulus gear.

12. The gas turbine engines as claimed in claim 11, wherein a point at which the flange is secured to the surrounding structure is the radial distance from the inner surface of the annulus gear to the axes of the apertures in the flange.

13. The gas turbine engine as claimed in claim 1, further comprising a propulsor, an intermediate-pressure compressor, a high-pressure compressor, a high-pressure turbine, and a low-pressure turbine, wherein the high-pressure turbine is arranged to directly drive the high-pressure compressor, the low-pressure turbine is arranged to directly drive the intermediate-pressure compressor, and the low-pressure turbine is arranged to drive the propulsor via the gearbox.

14. The gas turbine engine as claimed in claim 13, wherein the sun gear is driven by the low-pressure turbine, the annulus gear is secured to a static structure, and the carrier is arranged to drive the propulsor.

15. The gas turbine engine as claimed in claim 13, wherein the sun gear is driven by the low-pressure turbine, the carrier is secured to a static structure, and the annulus gear is arranged to drive the propulsor.

16. The gas turbine engine as claimed in claim 1, further comprising a propulsor, an intermediate-pressure compressor, a high-pressure compressor, a high-pressure turbine, and a low-pressure turbine, wherein the high-pressure turbine is arranged to directly drive the high-pressure compressor, the low-pressure turbine is arranged to directly drive the propulsor, and the low-pressure turbine is arranged to drive the intermediate-pressure compressor via the gearbox.

17. The gas turbine engine as claimed in claim 1, further comprising a propulsor, an intermediate-pressure compressor, a high-pressure compressor, a high-pressure turbine, an intermediate-pressure turbine, and a low-pressure turbine, wherein the high-pressure turbine is arranged to directly drive the high-pressure compressor, the intermediate-pressure turbine is arranged to directly drive the intermediate-pressure compressor, and the low-pressure turbine is arranged to drive the propulsor via the gearbox.

18. The gas turbine engine as claimed in claim 1, further comprising a propulsor, a high-pressure compressor, a high-pressure turbine, and a low-pressure turbine, wherein the high-pressure turbine is arranged to directly drive the high-pressure compressor and the low-pressure turbine is arranged to drive the propulsor via the gearbox.

19. The gas turbine engine as claimed in claim 1, wherein each of the sun gear, the planet gears, and the annulus gear comprises two sets of helical gear teeth.

20. A gearbox comprising:

a sun gear, an annulus gear, a plurality of planet gears, and a carrier,

each planet gear being rotatably mounted in the carrier by at least one bearing,

the sun gear meshing with the planet gears and the planet gears meshing with the annulus gear,

each of the sun gear, the planet gears, and the annulus gear comprising helical gear teeth,

the annulus gear being secured to a surrounding structure by a radially extending member, a face of the radially extending member nearest a middle of the annulus gear being axially spaced from the middle of the annulus gear by a first distance, a reference diameter of the annulus gear being radially spaced from a point at which the radially extending member is secured to the surrounding structure by a second distance, wherein

the first distance=(the second distance×

sin(helix angle of the helical gear teeth))/tan (pressure angle of the helical gear teeth), and

a ratio of the first distance to the second distance is between and including 0.5 and 1.2.