Driveshaft for the gearbox of auxiliary machines of a turbojet engine

Patent metadata

Field	Value
Publication number	US-9796264-B2
Application number	US-201214000314-A
Country	US
Kind code	B2
Filing date	Feb 17, 2012
Priority date	Feb 21, 2011
Publication date	Oct 24, 2017
Grant date	Oct 24, 2017

Abstract

A turbojet engine including an intermediate casing including radial arms and a driveshaft for a gearbox for auxiliary machines of the turbojet engine, the driveshaft mounted in a radial arm, the radial arm including an intermediate bearing supporting the driveshaft, the intermediate bearing including plural rolling bearings supporting the driveshaft, the driveshaft including a first shaft element connected at one end to a mechanism providing mechanical transmission to an engine shaft of the turbojet engine, and a second shaft element connected at one end to a mechanism providing mechanical transmission to the box. The first shaft element and the second shaft element are linked by a connection including plural splines. A single plane transversely passes through the plural splines and the plural rolling bearings.

First claim

What is claimed is:

1. A multi-flow turbojet engine, comprising:
an intermediate casing including radial arms and a driveshaft for a gearbox for auxiliary machines of the turbojet engine,
the driveshaft being mounted in one of the radial arms of the intermediate casing,
the one of the radial arms of the intermediate casing comprising an intermediate bearing for supporting the driveshaft,
the intermediate bearing comprising a plurality of rolling bearings for supporting the driveshaft,
the driveshaft comprising a first shaft element including a first end which is connected to a means for providing mechanical transmission to an engine shaft of the turbojet engine and including a second hollow cylindrical end opposite to the first end, and a second shaft element including a first end which is connected to a means for providing mechanical transmission to the gearbox and including a second end opposite to the first end, the second hollow cylindrical end of the first shaft element and the second end of the second shaft element being linked by a connection in which the second end of the second shaft element is fitted in the second hollow cylindrical end of the first shaft element, said connection including a plurality of complementary splines arranged on the second hollow cylindrical end of the first shaft element and on the second end of the second shaft element, the complementary splines being surrounded by the plurality of rolling bearings,
wherein a single plane, transverse to the plurality of complementary splines and to all the rolling bearings of the plurality of rolling bearings, passes through the plurality of complementary splines and all the rolling bearings of the plurality of rolling bearings.

2. The multi-flow turbojet engine according to claim 1 , wherein the first shaft element and the second shaft element of the driveshaft are articulated about a center of swiveling, and wherein the single plane passes through the center of swiveling and all the rolling bearings of the plurality of rolling bearings.

3. The multi-flow turbojet engine according to claim 2 , wherein the single plane transversely passes through the center of swiveling and a center of each rolling bearing of the plurality of rolling bearings.

4. The multi-flow turbojet engine according to claim 1 , wherein the single plane transversely passes through a center of one of the complementary splines and a center of the plurality of rolling bearings.

5. The multi-flow turbojet engine according to claim 1 , wherein each of the splines of the plurality of complementary splines is rounded.

6. The multi-flow turbojet engine according to claim 1 , wherein the first shaft element of the driveshaft is accommodated in a first sleeve and the second shaft element of the driveshaft is accommodated in a second sleeve.

7. The multi-flow turbojet engine according to claim 1 , wherein the intermediate bearing is accommodated in a space of the one of the radial arms separating a primary flow of the turbojet engine passing through compression stages, a combustion chamber, and turbine stages of the turbojet engine and a secondary flow bypassing the compression stages, combustion chamber, and turbine stages of the turbojet engine.

8. The multi-flow turbojet engine according to claim 1 , further comprising a lubrication-oil injection device configured to inject lubrication oil in a region of the plurality of complementary splines and the plurality of rolling bearings.

9. The multi-flow turbojet engine according to claim 1 , further comprising an outer race for the intermediate bearing that is centered in the intermediate casing.

10. The multi-flow turbojet engine according to claim 1 , wherein the second end of the first shaft element is directly connected to the second end of the second shaft element.

11. The multi-flow turbojet engine according to claim 1 , wherein the first shaft element is a single piece.

12. The multi-flow turbojet engine according to claim 1 , wherein the second end of the first shaft element includes an internal radial shoulder against which the second end of the second shaft element abuts in a longitudinal direction of the second shaft element.

Assignees

• Brault Michel Gilbert Roland
• Servant Regis Eugene Henri
• Snecma

Inventors

• Brault Michel Gilbert Roland
• Servant Regis Eugene Henri

Classifications

• F02C7/32 Primary

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

• B60K25/06 Primary

  from the transmission power take-off · CPC title

• F02K3/06

  with front fan · CPC title

• F05D2220/50

  for auxiliary power units (APU's) · CPC title

• F02C7/36

  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 title