A gas turbine engine component includes a first member, a second member rotatable relative to the first member about an axis, and a seal assembly that includes a seal supported by the first member and a seal runner that rotates with the second member relative to the seal. The seal runner includes at least one internal passage to direct cooling fluid flow through the seal runner. A restriction is associated with the at least one internal passage to restrict flow through the at least one internal passage in response to an engine condition.

A free-wheel comprising a driving part and a driven part that are able to rotate about an axis of rotation, the free-wheel comprising a cage carrying at least one rolling element arranged in a connection space, the free-wheel having at least one lubrication device conveying a lubricating fluid into the connection space. The free-wheel comprises at least one variable-opening barrier arranged radially between the driving part and the driven part and longitudinally against the connection space, the opening being indexed on a relative position of the cage and of the driving part.

A free-wheel comprising a driving part and a driven part that are able to rotate about an axis of rotation, the free-wheel comprising at least one rotational connecting member arranged in a connection space, a driven connection section of the driven part surrounding a driving connection section of the driving part, the connection space being located radially, with respect to the axis of rotation, between the driving connection section and the driven connection section. The free-wheel comprises at least one barrier, the geometry of which varies depending on the speed of rotation of the driving part, arranged radially between the driving part and the driven part and longitudinally against the connection space, the barrier being constrained to rotate with the driving connection section.

A shaft (W) for a motor vehicle transmission (G) may have axial bore holes positioned within the shaft and configured to guide fluid within the shaft. The shaft may have first, second, and third axial sections (W1, W2, W3), the second axial section being axially between the first and third axial sections. Fluid enters the axial bore holes in the second axial section and exits the axial bore holes in the first and third axial sections. One of the axial bore holes (B2; B1, B1a) is arranged, at least partially, in the first axial section and is radially spaced from an axis of rotation (WA) of the shaft. Another of the axial bore holes (B1RS; B_SE5, B3a) is arranged, at least partially, in the third axial section. The one of the axial bore holes (B2; B1, B1a) is coaxial with the other of the axial bore holes (B1RS; B_SE5, B3a).

An oil distribution system including a shaft assembly, bearing assembly and mounting assembly is disclosed. The shaft assembly includes a shaft with an inner shaft. A pocket is defined between the shaft and the inner shaft. A ringed lattice containing oil is secured within the pocket, melting of the ringed lattice releases the oil. The shaft includes shaft slots to usher oil from the pocket towards the bearing assembly. The bearing assembly includes an inner and outer race. The inner and outer race each include axial slots and radial slots. The axial slots of the inner race align with the shaft slots to allow oil to flood the inner race. The mounting assembly includes a bearing support having bearing support slots to receive a stringed lattice. Oil from the bearing support flows into the outer race when the axial slots of the outer race align with the bearing support slots.

An oil distribution system including a shaft assembly, bearing assembly and mounting assembly is disclosed. The shaft assembly includes a shaft with an inner shaft. A pocket is defined between the shaft and the inner shaft. A ringed lattice containing oil is secured within the pocket, melting of the ringed lattice releases the oil. The shaft includes shaft slots to usher oil from the pocket towards the bearing assembly. The bearing assembly includes an inner and outer race. The inner and outer race each include axial slots and radial slots. The axial slots of the inner race align with the shaft slots to allow oil to flood the inner race. The mounting assembly includes a bearing support having bearing support slots to receive a stringed lattice. Oil from the bearing support flows into the outer race when the axial slots of the outer race align with the bearing support slots.

A turbine engine comprises a rotor shaft and a roller bearing supporting the shaft in rotation along an axis. The bearing comprises an inner ring, an outer ring, and rolling elements engaged between the inner and outer rings. The inner ring has a first axial end annular portion that is more exposed to heat during operation than a second axial end annular portion thereof. The turbine engine further comprises an oil injection device configured to supply the rolling elements with oil for lubrication of the latter. In order to homogenise the temperature of the inner ring, the latter comprises through-holes formed in the first axial end annular portion and distributed around the axis in order to allow for a circulation of oil coming from the oil injection device through the first axial end annular portion, thereby providing additional cooling to the first end annular portion.

A gas turbine engine component includes a first member, a second member rotatable relative to the first member about an axis, and a seal assembly that includes a seal supported by the first member and a seal runner that rotates with the second member relative to the seal. The seal runner includes at least one internal passage to direct cooling fluid flow through the seal runner. A restriction is associated with the at least one internal passage to restrict flow through the at least one internal passage in response to an engine condition.

An inner ring for a bearing assembly comprises an inner circumferential surface disposed between a first axial end and a second axial end. A circumferential slot is disposed in the inner circumferential surface adjacent the second axial end. At least one radial passage is disposed within the inner ring and is in fluid communication with the circumferential slot. At least one axial slot extends axially along the inner circumferential surface from a respective opening in the first axial end to the circumferential slot. At least one of the radial passage is circumferentially offset from each at least one axial slot.

Device for distributing oil from a rolling bearing (8) for an aircraft turbine engine, comprising: —a rolling bearing (8), —a body (5) for distributing oil, which body is configured to be mounted on a turbine engine shaft (4), said body comprising: i) a first outer cylindrical surface (5a) for mounting the inner ring (12) of the bearing, ii) a ring-shaped scoop (11) for recovering oil, iii) a ring-shaped track (26) of a dynamic seal (22), iv) a circuit (7) for lubricating the bearing and cooling the track, said circuit being formed in the body, characterised in that the ring-shaped scoop is the first scoop (11a) which supplies a first portion (7x) of the circuit with a view to cooling the track, and in that the body comprises a second ring-shaped scoop (11b) for recovering oil, which scoop supplies a second portion (7y) of the circuit with a view to lubricating the bearing.