Aircraft turbomachine assembly having an improved decoupling system in the event of a fan blade loss

Patent metadata

Field	Value
Publication number	US-10690004-B2
Application number	US-201815984948-A
Country	US
Kind code	B2
Filing date	May 21, 2018
Priority date	May 22, 2017
Publication date	Jun 23, 2020
Grant date	Jun 23, 2020

Abstract

An assembly for a turbomachine includes a fan rotor drive shaft, a rolling element and a support of an exterior rolling-element bearing ring including an exterior annular element as well as an interior annular element coupled through a decoupling interface in the shape of a truncated sphere and configured to be retained by friction under normal operating conditions of the turbomachine, and to move with respect to one another in the event of a fan blade loss. The rolling-element bearing is designed so that each rolling element has four points of contact with the rings, and so that the interface between the ring and the support has a hollowed space for deformation routed around a central portion of the exterior ring.

First claim

The invention claimed is:

1. An aircraft turbomachine assembly comprising:
a fan rotor drive shaft;
a rolling-element bearing comprising an exterior ring, an interior ring, and rolling elements arranged between the exterior and interior rings;
means for connecting the interior rolling-element bearing ring to the drive shaft;
a support for the exterior rolling-element bearing ring, said support being designed to be attached to a stator element of the turbomachine, and comprising an interior radial support surface in contact with an exterior radial surface of the exterior ring, the interior and exterior radial surfaces defining a junction interface between the exterior ring and the support,
wherein said support includes an exterior annular element as well as an interior annular element coupled to the exterior annular element via a decoupling interface in the shape of a truncated sphere, the exterior and interior annular elements being configured to be retained with respect to one another by friction at their decoupling interface under normal operating conditions of the turbomachine, and to move with respect to one another in the event of a fan blade loss, under the influence of a decoupling moment originating in the drive shaft and transmitted by the rolling-element bearing which is designed so that each rolling element has two points of contact with the exterior ring and two points of contact with the interior ring, and so that said junction interface has, under normal operating conditions of the turbomachine, a hollowed space for deformation routed around a central portion of the exterior ring.

2. The assembly according to claim 1 , wherein said means for connecting the interior rolling-element bearing ring to the drive shaft are made in a single part with the interior ring of the rolling-element bearing.

3. The assembly according to claim 1 , wherein the exterior rolling-element bearing ring is split axially into two adjoining rings.

4. The assembly according to claim 1 , wherein the exterior radial surface of the exterior ring comprises at a center of the exterior radial surface a notch having a half-section in the shape of a V radially open toward the exterior, delimiting a portion of said hollowed space.

5. The assembly according to claim 3 , wherein the exterior radial surface of the exterior ring comprises at a center of the exterior radial surface a notch having a half-section in the shape of a V radially open toward the exterior, delimiting a portion of said hollowed space, the exterior radial surface of each of the two rings has a chamfer, and the two chamfers face one another so as to jointly form said notch.

6. The assembly according to claim 1 , wherein said support is equipped with means of detecting the position of the interior annular element with respect to the exterior annular element.

7. The assembly according to claim 1 , wherein the rolling elements are balls.

8. An aircraft turbomachine comprising at least one assembly according to claim 1 .

9. The turbomachine according to claim 8 , further comprising three rolling-element bearings for guiding the fan rotor drive shaft, wherein said rolling-element bearing of the assembly constitutes an intermediate rolling-element bearing situated between the two others.

10. The turbomachine according to claim 8 , wherein the fan rotor drive shaft is a low-pressure shaft.

Assignees

• Safran Aircraft Engines

Inventors

• Leeder Laurent
• Bessy Arnaud

Classifications

• F16C19/166

  Four-point-contact ball bearings · CPC title

• F01D21/08

  Restoring position · CPC title

• F16C35/077

  between housing and outer race ring · CPC title

• F16C23/084

  sliding on a complementary spherical surface · CPC title

• F16C33/60

  divided {or split, e.g. comprising two juxtaposed rings} · CPC title