ROLLING BEARING FOR AIRCRAFT TURBOJET ENGINE FITTED WITH AXIAL RETENTION OF ITS EXTERNAL RING Russian patent published in 2015 - IPC F01D25/16 F02C7/06 

FIELD: motors and pumps.

SUBSTANCE: structure for an aircraft turbojet engine contains a rolling bearing, a bearing support, an insert between a bearing external ring and a support, and also connectors of the external ring with the support and means ensuring the axial retention of the external ring. The connectors of the external ring with the support contain a fixing flange installed on the support and a flexible connecting means fixed on the external ring and on the fixing flange. The axial retention means of the external ring contain the first and the second thrust elements. The first thrust elements are connected to the insert and implemented with a possibility of its axial retention in regard to the support in case of the destruction of the flexible connectors. The second thrust elements are connected to the insert and implemented with a possibility of its axial retention in regard to the support in case of the destruction of the flexible connectors. The second thrust elements are implemented as pins arranged in the circumferential direction with a spacing between each other and each entering into a nested hole made in the insert. The pins contain radially an internal end located in the ring groove, made on the external ring of the bearing and containing a set of through passage radial holes reaching the bottom of the ring groove. Each pin is arranged radially opposite to the continuous part of the ring groove bottom. When mounting the named structure the external ring is inserted into the insert so that to align in the radial direction all through the passage holes made in the ring with the nested holes for the pins made in the insert. The pins are inserted into the nested holes through the through passage holes so that radially internal ends of all the pins have been accommodated in the ring groove of the external ring. The external ring is arranged so that all the pins have been oriented in the radial direction opposite to the continuous part of the bottom of the named ring groove, and the fixing flange is installed on the bearing support. Another invention of the group relates to an aircraft jet turbine engine containing the named structure.

EFFECT: group of inventions allows reducing dimensions and weight of the bearing support of the turbojet engine.

7 cl, 10 dwg