An aircraft turbomachine with a reduction gear has a first shaft and a second shaft having one same axis of rotation, the second shaft being rotationally driven by the first shaft via the reduction gear, the first shaft having elastically deformable means having bellows section(s) and being connected to the reduction gear by a connecting system likewise having elastically deformable means involving a hairpin or bellows section(s).

A casing for a bearing of a gas turbine engine includes a shaft extending along an axial direction. The casing includes an attachment feature at a radially outermost portion of the casing. The attachment feature is configured to be coupled to a static frame of the gas turbine engine. The casing further includes a plurality of support arms extend from the attachment feature to a radially innermost portion of the casing. At least one support arm of the plurality of support arms defines an internal cavity. Further, the radially innermost portion of the casing is configured to be coupled to an outer race of the bearing. The casing additionally includes a reinforcing member housed at least partially within the internal cavity of at least one support arm. Moreover, the reinforcing member includes a shape memory alloy material.

Compressor device provided with at least one compressor element and a drive for the compressor element, wherein all bearings of at least one shaft in the compressor device configured to carry static axial load, are provided with a bearing damper which comprises a coupling element and at least one damping element made of damping elastomer material. The bearing damper is installed with the aid of the coupling element between a bearing of the compressor device and the housing of the compressor device. The coupling element allows little or no movement of the bearing relative to the housing the radial direction compared to the axial direction. The damping element is configured to dampen the axial movement of the bearing relative to the housing.

A bearing support designed to be secured to a stationary turbojet element for supporting a journal, including a cone which widens from a central portion for supporting the journal to a portion for securing to the stationary element, a cylindrical body extending the portion for securing to the stationary element while surrounding the cone, an upstream skirt carried by the cone for defining an upstream enclosure for the central portion, and at least one downstream revolution element carried by the cone for defining a downstream enclosure for the central portion. The bearing support can be made as a single part produced by additive manufacturing.

A system for the axial retention of a holding ring for a bearing for guiding in rotation a rotary shaft of a turbomachine is disclosed. The system includes an annular bearing support and a bearing holding ring that is borne by the annular bearing support. The bearing holder ring includes an upstream ring configured to be brought into contact with the bearing support and a downstream ring that is elastically deformable. The bearing support has a first axial retention element, and the bearing holding ring has a second axial retention element. The first and second axial retention elements are configured to cooperate with one another to axially retain the bearing holding ring in the event of damage to the downstream ring.

A device for damping a rolling bearing includes a support and a radially flexible cage. The cage includes a ring provided in order to be mounted on the periphery of a rolling bearing. The radial flexibility of this cage results from the structure thereof which is perforated by oblique posts connecting the ring to an attachment annulus of this cage. The support includes a plurality of teeth each extending radially through a respective inter-post opening of the cage. The ring and the support form, radially between one another, a fluid damping cavity suitable for forming a compressed fluid film. The device allows a controlled radial movement of the ring, the latter being radially limited by the support, while having a limited footprint.

A turbine engine assembly includes: a fan assembly; a turbine coupled to the fan assembly through a gearbox; a stationary component; and an assembly extending between the gearbox and the stationary component to couple the gearbox to the stationary component, wherein the assembly includes at least one vibration-reducing mechanism configured to isolate a vibratory response of the gearbox from the stationary component.

A roller element device, in particular for a gas turbine engine, comprises an outer ring with an inner raceway, an inner ring with an outer raceway, and roller elements which are arranged between the raceways so as to roll thereon, wherein the outer ring and the inner ring are each connected via a connecting portion to a respective fixing portion for fixing to one of two components which are rotatable relative to each other about a rotation axis, and the connecting portions are formed such that the two raceways can be jointly tilted at least in portions relative to the rotation axis.

A mechanical reduction gear of a turbomachine, in particular of an aircraft. The reduction gear includes a sun gear, a ring gear surrounded by a ring gear carrier, and planet gears meshed with the sun gear and the ring gear. The ring gear carrier includes an axial abutment on which the ring gear is configured to bear, and helical external splines which are engaged in complementary internal splines of the ring gear carrier and which are configured to cooperate by sliding with the internal splines so as to force the ring gear to be held against the abutment in operation.

An annular parts assembly for mounting onto a shaft of an aircraft engine is provided. The assembly comprises a first annular body having a surface defining a plurality of pulling features extending from a remainder of the surface, the pulling features circumferentially spaced apart on the surface. The assembly comprises a second annular body defining a balancing ring, the balancing ring concentric with the first annular body, the balancing ring having a plurality of protrusions and circumferential spaces between adjacent ones of the plurality of protrusions, the circumferential spaces accommodating the pulling features such that the pulling features of the first annular body and the protrusions intercalate.