Accessory drive case for a turboprop

Patent metadata

Field	Value
Publication number	US-10145260-B2
Application number	US-201414896263-A
Country	US
Kind code	B2
Filing date	Jun 4, 2014
Priority date	Jun 6, 2013
Publication date	Dec 4, 2018
Grant date	Dec 4, 2018

Abstract

A turbomachine including an accessory drive case, connected to the engine shaft via a radial shaft, wherein the accessory drive case also includes: a primary shaft which is driven by the radial shaft via a bevel gearbox, and assemblies for mechanically driving accessories, driven by the primary shaft and configured such that the related accessories lie at the upper portion and on at least one of the side edges of the engine case.

First claim

The invention claimed is:

1. A turbomachine, comprising:
an engine casing,
an engine shaft, housed in the engine casing, said engine shaft defining an axis of rotation,
an accessory gearbox, positioned outside the engine casing, the accessory gearbox being connected to the engine shaft through a radial transmission shaft driven by the engine shaft forming an angle with the axis of rotation of the engine shaft,
a plurality of transmission shafts intended to mechanically drive the accessories, a primary shaft, extending substantially transversely to the axis of rotation of the engine shaft and driven by the radial transmission shaft through a primary angle gear, said primary angle gear comprising a primary gearing member mounted on the primary shaft, and
a plurality of mechanical drive assemblies of the transmission shafts, said drive assemblies being driven directly by the primary shaft and being configured so that the associated accessories extend in an upper portion and over at least one lateral edge of the engine casing,
wherein the accessory gearbox comprises a first accessory positioned at a first free end of the primary shaft, wherein the first accessory is arranged so as to extend toward the engine and to be positioned along a first lateral edge of the engine casing.

2. The turbomachine according to claim 1 , wherein at least one of the drive assemblies comprises a secondary gearing member fixedly attached to the primary shaft and an output gearing member fixedly attached to one transmission shaft of the plurality of transmission shafts of the accessory driven by the drive assembly.

3. The turbomachine according to claim 2 , wherein the secondary gearing member comprises a bevel wheel and the output gearing member comprises a bevel gear so that an axis of the primary shaft and an axis of the one transmission shaft of the plurality of transmission shafts are concurrent.

4. The turbomachine according to claim 2 , wherein at least one the gearing members of the primary angle gear and at least one of the drive assemblies have non-concurrent axes.

5. The turbomachine according to claim 4 , wherein the primary angle gear comprises a wheel and a worm.

6. The turbomachine according to claim 4 , wherein at least one of the drive assemblies comprises an angle gear comprising two gearing members comprising a worm and a wheel.

7. The turbomachine according to claim 4 , wherein the accessory gearbox comprises a box casing and the gearing members of the at least one drive assembly are attached to the box casing by at least two connecting members extending on either side of each gearing member.

8. The turbomachine according to claim 1 , wherein the primary angle gear comprises an input gearing member fixedly attached to the radial transmission shaft.

9. The turbomachine according to claim 8 , wherein the gearing members of the primary angle gear have concurrent axes, the input gearing member comprising an input bevel gear and the primary gearing member comprising a bevel crown gear.

10. The turbomachine according to claim 1 , wherein at least one of the drive assemblies comprises gearing with parallel axes comprising a secondary wheel driven by the primary shaft and an output wheel fixedly attached to one transmission shaft of the plurality of transmission shafts so that the axis of the secondary wheel and the axis of the output wheel are parallel.

11. The turbomachine according to claim 10 , wherein at least two of the drive assemblies are driven in series by one and the same gearing member attached to the primary shaft said gearing member comprising a secondary wheel attached to the primary shaft.

12. The turbomachine according to claim 10 , wherein at least one of the drive assemblies comprises an output wheel driven via an intermediate wheel by a secondary wheel attached to the primary shaft.

13. An aircraft, comprising:
a nacelle, and
a turbomachine according to claim 1 housed in the nacelle,
wherein the nacelle has a generally elongated shape in a vertical direction and the turbomachine is positioned in a generally lower area of the nacelle while the accessory gearbox extends within a generally upper area of said nacelle.

14. The aircraft comprising a turbomachine according to claim 13 , wherein the accessory gearbox comprises a plurality of accessories distributed in the upper area of the nacelle and on the at least one lateral edge of the engine casing.

15. The turbomachine according to claim 1 , comprising a turboprop.

16. A turbomachine, comprising:
an engine casing,
an engine shaft, housed in the engine casing, said engine shaft defining an axis of rotation,
an accessory gearbox, positioned outside the engine casing, the accessory gearbox being connected to the engine shaft through a radial transmission shaft driven by the engine shaft forming an angle with the axis of rotation of the engine shaft,
a plurality of transmission shafts intended to mechanically drive the accessories, a primary shaft, extending substantially transversely to the axis of rotation of the engine shaft and driven by the radial transmission shaft through a primary angle gear, said primary angle gear comprising a primary gearing member mounted on the primary shaft, and
a plurality of mechanical drive assemblies of the transmission shafts, said drive assemblies being driven directly by the primary shaft and being configured so that the associated accessories extend in the upper portion and over at least one lateral edge of the engine casing,
wherein at least one of the drive assemblies comprises a secondary gearing member fixedly attached to the primary shaft and an output gearing member fixedly attached to one transmission shaft of the plurality of transmission shafts of the accessory driven by the drive assembly,
wherein at least one of the gearing members of the primary angle gear and at least one of the drive assemblies have non-concurrent axes, and
wherein at least one of the drive assemblies comprises an angle gear comprising two gearing members comprising a worm and a wheel, and
wherein the accessory gearbox comprises a first accessory positioned at a first free end of the primary shaft, wherein the first accessory is arranged so as to extend toward the engine and to be positioned along a first lateral edge of the engine casing.

17. A turbomachine, comprising:
an engine casing,
an engine shaft, housed in the engine casing, said engine shaft defining an axis of rotation,
an accessory gearbox, positioned outside the engine casing, the accessory gearbox being connected to the engine shaft through a radial transmission shaft driven by the engine shaft forming an angle with the axis of rotation of the engine shaft,
a plurality of transmission shafts intended to mechanically drive the accessories, a primary shaft, extending substantially transversely to the axis of rotation of the engine shaft and driven by the radial transmission shaft through a primary angle gear, said primary angle gear comprising a primary gearing member mounted on the primary shaft, and
a plurality of mechanical drive assemblies of the transmission shafts, said drive assemblies being driven directly by the primary shaft and being configured so that the associated accessories extend in the upper portion and over at least one of the lateral edges of the engine casing,
wherein at least one of the drive assemblies comprises a secondary gearing member fixedly attached to the primary shaft and an output gearing member fixedly attached to one transmission shaft of the plurality of transmission shafts of the accessory d

Assignees

• Safran Aircraft Engines

Inventors

• Armange Frantz

Classifications

• F16H1/222

  with non-parallel axes · CPC title

• F01D15/12 Primary

  Combinations with mechanical gearing (driven by multiple engines F01D13/00) · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F16H1/225

  with two or more worm and worm-wheel gearings · CPC title

• F02C7/32 Primary

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