Patent ID: 9341079
Filing Date: 2016-05-17
CPC Classification: F01D,F05D,F16C,Y02T,Y10T

Claim Text:
1. A structure for an aircraft turbojet comprising: a rolling bearing including an outer ring; a bearing bracket surrounding the outer ring; a retaining ring interposed between the outer bearing ring and the bearing bracket; means for connecting the outer ring to the bearing bracket, wherein the means for connecting includes: means for allowing axial retention of the outer bearing ring, if the flexible connection means fracture, wherein the means enabling axial retention of the outer ring includes: first stop means securely attached to the retaining ring, and capable of axially retaining the retaining ring relative to the bearing bracket in event that the flexible connection means fracture; and second stop means securely attached to the retaining ring, and capable of axially retaining the outer ring relative to the retaining ring, in the event that the flexible connection means fracture, wherein the second stop means includes multiple slugs spaced circumferentially relative to one another, wherein each slug is held in a slug insertion opening made in the retaining ring, wherein the slugs include a radially internal end which is located in a groove made on the outer bearing ring fitted with multiple radial clearance through-holes, emerging in a base of the groove, wherein each of the slugs is positioned radially opposite a full portion of the base of the groove.