Torque transmission device with reduced friction

Patent metadata

Field	Value
Publication number	US-11378014-B2
Application number	US-201917055428-A
Country	US
Kind code	B2
Filing date	May 15, 2019
Priority date	May 15, 2018
Publication date	Jul 5, 2022
Grant date	Jul 5, 2022

Abstract

A turbomachine includes a low-pressure shaft that drives a fan shaft in rotation by a coupling assembly including a first shaft on which are formed plural first axial grooves, a second shaft on which are formed plural second axial grooves, and a coupling device including rolling elements and an annular cage positioned between the first shaft and the second shaft. The rolling elements are positioned between one of the first axial grooves and one of the second axial grooves to couple in rotation the first and the second shaft. Each first and second groove has a first and a second substantially planar surface inclined with respect to one another and extending along the axis.

First claim

The invention claimed is:

1. A turbomachine including a casing, a low-pressure shaft mounted in rotation in the casing, a fan shaft mounted in rotation relative to the casing and a coupling assembly, the low-pressure shaft being configured to drive the fan shaft in rotation by means of the coupling assembly, the coupling assembly including:
a first shaft which extends along an axis and integral with one among the low-pressure shaft and the fan shaft, the first shaft comprising at least a first portion having an outer face in which are formed a plurality of first axial grooves,
a second shaft coaxial with the first shaft and integral with one among the low-pressure shaft and the fan shaft, the second shaft comprising at least one second portion which surrounds the first portion and has an inner face in which are formed a plurality of second axial grooves,
a coupling device including a plurality of rolling elements and a cage that is annular, said cage being positioned between the first shaft and the second shaft, a plurality of recesses being formed in the cage, each of the rolling elements being positioned in a respective recess and between one of the first axial grooves and one of the second axial grooves so as to couple in rotation the first and the second shaft, dimensions of one of the rolling elements and the positioning of one of the second axial grooves relative to one of the first axial grooves being configured to supply a radial and tangential clearance to one of the rolling elements, and in which each first and second groove has a first and a second substantially planar surface extending along the axis,
wherein, within each of the first and second groove, the first and the second surfaces are inclined relative to one another.

2. The turbomachine according to claim 1 , wherein each rolling element is mounted free in its respective recess.

3. The turbomachine according to claim 1 , wherein the recesses of the cage are axially aligned so as to form a series of axial rows, the axial rows being distributed angularly in regular fashion around the axis so that each row extends along a first axial groove and a second axial groove.

4. The turbomachine according to claim 1 , wherein the rolling elements comprise balls.

5. The turbomachine according to claim 1 , wherein the coupling device is movable in translation along the axis.

6. The turbomachine according to claim 1 , wherein the coupling assembly further comprises a first return element extending between the cage and one among the first shaft and the second shaft, the first return element being configured to define an axial position of the cage relative to one among the first portion and the second portion.

7. The turbomachine according to claim 6 , wherein one among the first portion and the second portion has a first axial abutment, the cage having a second axial abutment, the first return element being supported on each of the first axial abutment and the second axial abutment.

8. The turbomachine according to claim 1 , comprising a second return element extending between the cage and a portion among the first portion and the second portion which has a first axial abutment, the second return element being configured to define an axial position of the cage relative to said portion among the first portion and the second portion which has the first axial abutment.

9. The turbomachine according to claim 8 , wherein the portion among the first portion and the second portion which has the first axial abutment also has a third abutment, and the cage also has a fourth abutment, the second return element being supported on the third abutment and the fourth abutment.

10. The turbomachine according to claim 6 , further comprising a second return element extending between the cage and a portion among the first portion and the second portion which has a first axial abutment, the second return element being configured to define the axial position of the cage relative to said portion among the first portion and the second portion which has the first axial abutment, wherein the first return element and the second return element extend on either side of the cage.

11. The turbomachine according to claim 1 , wherein the low-pressure shaft includes a turbine portion attached to a low-pressure turbine and a rear abutment portion attached axially to the casing of the turbomachine and guided in rotation relative to the casing, the turbine portion and the rear abutment portion being coupled by means of a splined coupling.

Assignees

• Safran Aircraft Engines

Inventors

• Blanchard Stéphane Pierre Guillaume
• Condat Helene Myriam
• Trappier Nicolas Xavier
• Perrot Laurent Paul François

Classifications

• F05D2250/294

  grooved · CPC title

• F16D3/065 Primary

  by means of rolling elements · CPC title

• F16C33/425

  from a single part, e.g. ribbon cages with one corrugated annular part · CPC title

• F05D2250/241

  spherical · CPC title

• F05D2260/38

  by a spring, i.e. spring loaded or biased towards a certain position · CPC title