Turbomachines and epicyclic gear assemblies with axially offset sun and ring gears

Patent metadata

Field	Value
Publication number	US-12078075-B2
Application number	US-202218091753-A
Country	US
Kind code	B2
Filing date	Dec 30, 2022
Priority date	May 6, 2020
Publication date	Sep 3, 2024
Grant date	Sep 3, 2024

Abstract

A turbomachine engine includes a fan assembly and a core engine comprising a turbine and an input shaft rotatable with the turbine is provided. A single-stage epicyclic gear assembly receives the input shaft at a first speed and drives an output shaft coupled to the fan assembly at a second speed. A sun gear rotates about a longitudinal centerline of the gear assembly and has a sun gear-mesh region along the longitudinal centerline of the gear assembly where the sun gear is configured to contact a plurality of planet gears. A ring gear-mesh region is provided along the longitudinal centerline of the gear assembly where a ring gear is configured to contact the plurality of planet gears. The sun gear-mesh region is axially offset from the ring gear-mesh region along the longitudinal centerline.

First claim

We claim:

1. A turbomachine engine comprising:
a fan assembly comprising a plurality of fan blades;
a core engine comprising a turbine and an input shaft rotatable with the turbine; and
a single-stage epicyclic gear assembly that receives the input shaft at a first speed and drives an output shaft coupled to the fan assembly at a second speed, the second speed being slower than the first speed, the gear assembly comprising:
a sun gear, a plurality of planet gears, and a ring gear, the sun gear rotating about a longitudinal centerline of the gear assembly;
a sun gear-mesh region along the longitudinal centerline of the gear assembly where the sun gear is configured to contact the plurality of planet gears;
a ring gear-mesh region along the longitudinal centerline of the gear assembly where the ring gear is configured to contact the plurality of planet gears,

wherein the sun gear-mesh region is axially offset from the ring gear-mesh region along the longitudinal centerline such that at least 50% of a width of the sun gear-mesh region does not axially overlap with the ring gear-mesh region,
wherein the sun gear, the plurality of planet gears, and the ring gear comprise double helical gears, and the sun gear comprises a first sun gear set and a second sun gear set, each of the plurality of planet gears comprise a first planet gear set and a second planet gear set, and the ring gear comprises a first ring gear set and a second ring gear set,
wherein the first ring gear set and the second ring gear set are axially spaced apart from one another along the longitudinal centerline, and the first sun gear set and the second sun gear set are positioned between the first ring gear set and the second ring gear set,
wherein the sun gear-mesh region comprises a first sun gear-mesh region where the first sun gear set meshes with the first planet gear sets and a second sun gear-mesh region where the second sun gear set meshes with the second planet gear sets,
the ring gear-mesh region comprises a first ring gear-mesh region where the first ring gear set meshes with the first planet gear sets and a second ring gear-mesh region where the second ring gear set meshes with the second planet gear sets, and
wherein a width of the first planet gear set is less than a combined width of the first sun gear set and the first ring gear set.

2. The turbomachine engine of claim 1 , wherein the first sun gear-mesh region and the first ring gear-mesh region do not axially overlap along the longitudinal centerline.

3. The turbomachine engine of claim 1 , wherein there is an axial gap between the first sun gear-mesh region and the first ring gear-mesh region.

4. The turbomachine engine of claim 3 , wherein the axial gap has a gap width that is less than 15% of a width of the first planet gear sets.

5. The turbomachine engine of claim 1 , wherein there is an axial overlap between the first sun gear-mesh region and the first ring gear-mesh region, and an amount of the axial overlap is less than 15% of a width of the first planet gear sets.

6. The turbomachine engine of claim 1 , wherein a gear ratio of the gear assembly is within a range that extends from 6:1 to 14:1.

7. The turbomachine engine of claim 1 , wherein the gear assembly is a planetary gear configuration in which the ring gear is fixed relative to the engine and does not rotate.

8. The turbomachine engine of claim 1 , wherein the gear assembly is a star gear configuration in which the planet gears are fixed relative to the engine and do not rotate.

9. The turbomachine engine of claim 1 , wherein the fan assembly is a single stage of unducted fan blades.

10. The turbomachine engine of claim 1 , wherein a width of the first planet gear set is greater than a combined width of the first sun gear set and the first ring gear set.

11. The turbomachine engine of claim 1 , wherein the fan assembly has ten to sixteen blades, or ten to fourteen blades, or twelve blades.

12. The turbomachine engine of claim 1 , wherein a fan blade tip speed at a cruise flight condition is 650 to 900 fps.

13. The turbomachine engine of claim 1 , wherein the fan assembly has a fan pressure ratio (FPR) for the fan assembly that is 1.04 to 1.10, as measured across the fan blades at a cruise flight condition.

14. A turbomachine engine comprising:
a fan assembly comprising a plurality of fan blades;
a core engine comprising a turbine and an input shaft rotatable with the turbine; and
a gear assembly configured to drive an input shaft at a first speed and drive an output shaft at a second speed that is slower than the first speed, the gear assembly comprising:
a sun gear rotating about a longitudinal centerline of the gear assembly;
a plurality of planet gears;
a ring gear;
a sun gear-mesh region along the longitudinal centerline of the gear assembly where the sun gear is configured to contact the plurality of planet gears;
a ring gear-mesh region along the longitudinal centerline of the gear assembly where the ring gear is configured to contact the plurality of planet gears,

wherein the sun gear-mesh region is axially offset from the ring gear-mesh region along the longitudinal centerline such that at least 50% of a width of the sun gear-mesh region does not axially overlap with the ring gear-mesh region,
wherein the sun gear, the plurality of planet gears, and the ring gear mesh comprise double helical gears, and the sun gear comprises a first sun gear set and a second sun gear set, each of the plurality of planet gears comprise a first planet gear set and a second planet gear set, and the ring gear comprises a first ring gear set and a second ring gear set,
wherein the first sun gear set and the second sun gear set are axially spaced apart from one another along the longitudinal centerline, and the first sun gear set and the second sun gear set are positioned between the first ring gear set and the second ring gear set, and
wherein the fan assembly has a fan pressure ratio (FPR) for the fan assembly that is 1.04 to 1.10, as measured across the fan blades at a cruise flight condition.

15. The turbomachine engine of claim 14 , wherein the sun gear-mesh region comprises a first sun gear-mesh region where the first sun gear set meshes with the first planet gear sets and a second sun gear-mesh region where the second sun gear set meshes with the second planet gear sets, and the ring gear-mesh region comprises a first ring gear-mesh region where the first ring gear set meshes with the first planet gear sets and a second ring gear-mesh region where the second ring gear set meshes with the second planet gear sets.

16. The turbomachine engine of claim 15 , wherein there is an axial gap between the first sun gear-mesh region and the first ring gear-mesh region, and
wherein the axial gap has a gap width that is less than 5% of the width of the first planet gear sets.

17. The turbomachine engine of claim 15 , wherein the first sun gear-mesh region and the first ring gear-mesh region do not axially overlap along the longitudinal centerline.

18. The turbomachine engine of claim 15 , wherein there is an axial gap between the first sun gear-mesh region and the first ring gear-mesh region, and
wherein the axial gap has a gap width that is less than 15% of a width of the first planet gear sets.

19. The turbomachine engine of claim 14 , wherein a gear ratio of the gear assembly is within a range that extends from 6:1 to 14:1.

20. A turbomachine engine comprising:
a fan assembly comprising a plurality of fan blades;

Assignees

• Ge Avio Srl

Inventors

• Facchini Marco
• Andrei Gianluca
• Altamura Paolo

Classifications

• F16H1/32

  in which the central axis of the gearing lies inside the periphery of an orbital gear · CPC title

• F16H57/08 Primary

  of gearings with members having orbital motion · CPC title

• F16H3/44

  using gears having orbital motion · CPC title

• F16H1/2809

  with means for equalising the distribution of load on the planet gears · CPC title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title