An aircraft engine, has: a shaft rotatable about a central axis and engaged at an end thereof to a rotatable load via splines; a reference tube extending around the shaft and having a first end secured to the shaft and a second end free relative to the shaft for measuring a deformation of the shaft, the reference tube defining at least one tube aperture; an oil nozzle defining an exit flow axis intersecting the at least one tube aperture, the shaft defining at least one shaft aperture through the shaft, an oil flow path extending from the oil nozzle to the splines; and a drain outlet located radially outwardly of an inlet of the at least one shaft aperture for outputting excess oil out of an annular gap defined between the shaft and the reference tube.

An apparatus is provided for a turbine engine. This turbine engine apparatus includes a journal bearing extending axially along and circumferentially about an axis. The journal bearing extends radially between a bearing inner side and a bearing outer side. The journal bearing includes a bore, a passage, a groove and a slot. The bore extends axially within the journal bearing and along the bearing inner side. The passage extends radially within the journal bearing and is fluidly coupled with the bore and the groove. The groove extends longitudinally within the journal bearing at the bearing outer side between a groove first end and a groove second end. At least a portion of the slot extends circumferentially about the axis within the journal bearing at the bearing outer side from the groove first end to the groove second end.

An apparatus is provided for a turbine engine. This turbine engine apparatus includes a journal bearing extending axially along and circumferentially about an axis. The journal bearing extends radially between a bearing inner side and a bearing outer side. The journal bearing includes a bore, a passage, a groove and a slot. The bore extends axially within the journal bearing and along the bearing inner side. The passage extends radially within the journal bearing and is fluidly coupled with the bore and the groove. The groove extends longitudinally within the journal bearing at the bearing outer side between a groove first end and a groove second end. At least a portion of the slot extends circumferentially about the axis within the journal bearing at the bearing outer side from the groove first end to the groove second end.

Lubrication device for a turbomachine reduction gear, the device comprising an annular lubricating oil collecting cup delimited by a first wall and a second wall, said cup being divided by internal walls extending between the first wall and the second wall so as to define a plurality of angular sectors forming oil collection basins, the basins being circumferentially adjacent around the axis and comprising lubricating oil outlets, characterized in that one or more of said internal walls have openings allowing oil to pass between the circumferentially adjacent basins, characterized in that said openings (58) are formed in one or more of said internal walls so as to define one or more rows of openings in said one or more internal walls.

Lubrication device for a turbomachine reduction gear, the device comprising an annular lubricating oil collecting cup delimited by a first wall and a second wall, said cup being divided by internal walls extending between the first wall and the second wall so as to define a plurality of angular sectors forming oil collection basins, the basins being circumferentially adjacent around the axis and comprising lubricating oil outlets, characterized in that one or more of said internal walls have openings allowing oil to pass between the circumferentially adjacent basins, characterized in that said openings (58) are formed in one or more of said internal walls so as to define one or more rows of openings in said one or more internal walls.

An auxiliary power unit for an aircraft, having a compressor, an intercooler including first conduit(s) having an inlet in fluid communication with the compressor outlet and second conduit(s) configured for circulation of a coolant therethrough, an engine core having an inlet in fluid communication with an outlet of the first conduit(s), and a bleed conduit in fluid communication with the outlet of the first conduit(s) through a bleed air valve. The auxiliary power unit may include a generator in driving engagement with the shaft of the engine core to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.

An auxiliary power unit for an aircraft, having a compressor, an intercooler including first conduit(s) having an inlet in fluid communication with the compressor outlet and second conduit(s) configured for circulation of a coolant therethrough, an engine core having an inlet in fluid communication with an outlet of the first conduit(s), and a bleed conduit in fluid communication with the outlet of the first conduit(s) through a bleed air valve. The auxiliary power unit may include a generator in driving engagement with the shaft of the engine core to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.

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.

An oil distribution system uses an oil storage container to contain an air/oil separation unit, a heat exchanger, and an oil reservoir. The functions of oil storage, air/oil separation, and cooling are integrated in the container. Hot aerated oil enters the container at an air/oil separation unit. The air/oil separator deposits hot de-aerated oil into the oil reservoir. The oil reservoir transfers hot de-aerated oil to conduits in a heat exchanger. The heat exchanger uses fuel to cool the oil and warm the fuel. Cooled de-aerated oil is provided to a mechanical device for lubrication and warmed fuel is provided to power an engine. The container may alternatively receive hot aerated oil into the conduits in the heat exchanger. Cooled aerated oil is delivered to the air/oil separation unit to deposit cooled de-aerated oil into the reservoir. Cooled de-aerated oil is pumped to a mechanical device to provide lubrication.

An oil distribution system uses an oil storage container to contain an air/oil separation unit, a heat exchanger, and an oil reservoir. The functions of oil storage, air/oil separation, and cooling are integrated in the container. Hot aerated oil enters the container at an air/oil separation unit. The air/oil separator deposits hot de-aerated oil into the oil reservoir. The oil reservoir transfers hot de-aerated oil to conduits in a heat exchanger. The heat exchanger uses fuel to cool the oil and warm the fuel. Cooled de-aerated oil is provided to a mechanical device for lubrication and warmed fuel is provided to power an engine. The container may alternatively receive hot aerated oil into the conduits in the heat exchanger. Cooled aerated oil is delivered to the air/oil separation unit to deposit cooled de-aerated oil into the reservoir. Cooled de-aerated oil is pumped to a mechanical device to provide lubrication.