Gearbox comprising an improved reduction gear

Patent metadata

Field	Value
Publication number	US-10415671-B2
Application number	US-201615560195-A
Country	US
Kind code	B2
Filing date	Mar 22, 2016
Priority date	Mar 24, 2015
Publication date	Sep 17, 2019
Grant date	Sep 17, 2019

Abstract

A gearbox for an aircraft turbine engine includes a drive shaft, a secondary drive shaft coupled to the drive shaft with a reduction mechanism, and output shafts, each of which is coupled to the drive shaft or to the secondary drive shaft with a set of ring and pinion gears, wherein the reduction mechanism includes an intermediate shaft, a first end coupled to the drive shaft with a first stage of gears and the second end coupled to the secondary drive shaft with a second stage of gears, and wherein the intermediate shaft is rotatably mounted in the gearbox about the main axis thereof which is oriented substantially perpendicular to the main axis of the drive shaft.

First claim

The invention claimed is:

1. A gearbox for an aircraft turbine engine, the gearbox comprising:
a drive shaft,
a secondary drive shaft coupled to the drive shaft with a reduction mechanism, and
output shafts, one of which being coupled to the drive shaft, an other of which being coupled to the secondary shaft with a set of ring and pinion gears,
wherein the reduction mechanism comprises an intermediate shaft, a first end coupled to the drive shaft with a first stage of gears and the second end coupled to the secondary drive shaft with a second stage of gears.

2. The gearbox according to claim 1 , wherein each of the first or second stage of gears comprises a pinion mounted on the drive shaft or the secondary drive shaft and a pinion mounted on the associated end of the intermediate shaft.

3. The gearbox according to claim 2 , wherein the main axis of the secondary drive shaft is substantially coaxial with the main axis of the drive shaft, and the intermediate shaft is situated between two facing ends of the drive shaft and of the secondary drive shaft.

4. The gearbox according to claim 1 , wherein the intermediate shaft is situated between two facing ends of the drive shaft and of the secondary drive shaft.

5. The gearbox according to claim 3 , wherein each facing end of the drive shaft and of the secondary drive shaft carries the pinion of the first or second stage of gears that is associated therewith.

6. The gearbox according to claim 2 , comprises means for guiding the intermediate shaft rotatably about its main axis, which are arranged at each end of the intermediate shaft.

7. The gearbox according to claim 6 , wherein the pinions of the stages of gears, which are carried by the ends of the intermediate shaft, are situated between said means for guiding the intermediate shaft in rotation about its main axis.

8. The gearbox according to claim 1 , wherein the main axis of the intermediate shaft is perpendicular to the main axis of the drive shaft.

9. An aircraft turbine engine, comprising a gearbox according to claim 1 .

10. A turbine engine according to claim 9 , further comprising means for connecting the drive shaft to the rotor of the turbine engine.

Assignees

• Safran Trans Systems

Inventors

• Bauduin Lionel
• Guillemont Maxence
• Viel Julien

Classifications

• F16H37/065

  with a plurality of driving or driven shafts (F16H37/0806 takes precedence) · CPC title

• F16H1/222 Primary

  with non-parallel axes · CPC title

• F02C7/32

  Arrangement, mounting, or driving, of auxiliaries · CPC title

• F05D2250/314

  the axes being inclined in relation to each other · CPC title

• F05D2250/313

  the axes being perpendicular to each other · CPC title