An assembly includes: a fan drive reducing gear of an aircraft turbine engine, and a lubrication system including: a housing enclosing the reducing gear; a device for spraying lubricant onto the reducing gear; a lubricant supply pipe intended to convey the lubricant towards the spraying device; a lubricant recovery pipe communicating with a bottom of the housing; a controlled valve equipping the recovery pipe; and a lubricant overflow discharge pipe connected to an overflow outlet of the bottom of the housing situated above a horizontal level of a bottom point of a gearing of the reducing gear, and to the recovery pipe, downstream from the valve.

A gear assembly for an aeronautical engine that includes a first gear disposed at a centerline axis of the gear assembly; a second gear coupled to the first gear in adjacent radial arrangement to form a first mesh between the first gear and the second gear; a third gear coupled to the second gear in adjacent radial arrangement to form a second mesh between the second gear and the third gear; a collector rotatably coupled with the third gear; and a lubricant input portion disposed between a portion of the first gear and the second gear such that a first supply opening of the lubricant input portion is directed at the first mesh between the first gear and the second gear. The first supply opening provides a flow of lubricant to the first mesh with a portion of the flow of lubricant is collected by the collector.

A lubrication system for a transmission assembly includes a primary reservoir, at least one primary jet, a primary circulating system fluidly coupling the primary reservoir and the at least one primary jet, a secondary reservoir, at least one secondary jet, and a secondary circulating system fluidly coupling the primary reservoir and the at least one secondary jet and fluidly coupling the primary reservoir and the secondary reservoir.

Embodiments are directed to solid lubricant assemblies for providing over temperature protection for bearings and gears in rotorcraft systems. A solid lubricant enters a fluid state above a certain temperature and is positioned so that fluid lubricant is applied to the bearings or gears.

A fan drive gear system for a turbofan engine according to an exemplary embodiment of this disclosure, among other possible things includes a sun gear that is rotatable about an axis, a plurality of intermediate gears driven by the sun gear, and a baffle that is disposed between at least two of the plurality of intermediate gears for defining a lubricant flow path from an interface between the sun gear and at least one of the plurality of intermediate gears. The baffle includes a channel with at least one ramp portion directing lubricant.

A method of retrofitting a gear box assembly with an emergency lubrication system includes removing plugs from visual inspection ports of a gearbox housing, removing a breather from a breather port of the gearbox housing, and installing jet plugs into the respective visual inspection ports and breather port, wherein each jet plug includes a respective jet tube.

A lubrication system for a mechanical system, the lubrication system comprising a main tank, a reserve tank and a main lubrication circuit. The main lubrication circuit comprises, in particular, a pump drawing in the lubricating liquid from the main tank via a main suction point and a main suction pipe connecting the main suction point to the pump. The reserve tank is supplied with lubricating liquid either directly from the main tank or via the main lubrication circuit. The reserve tank is connected to the main suction pipe via an outlet pipe and the reserve tank is located above the main suction point so that the lubricating liquid flows through the outlet pipe to the main suction pipe by gravity.

An example of an emergency lubrication system for an aircraft includes a lubricant tank configured to supply a lubricant to a gearbox of the aircraft, a tube coupled between the lubricant tank and the gearbox and comprising a check ball disposed within the tube, a first lubricant line coupled to the tube and a first inlet of the gearbox, and a second lubricant line coupled to the tube and a second inlet of the gearbox.

A mechanical system comprising a sump and at least one component to be lubricated or cooled arranged in the sump, the mechanical system comprising a lubricating fluid system provided with a lubricating fluid and a tank arranged in the sump. The tank is a leaking tank and is situated above said at least one component to be lubricated or cooled, the lubricating fluid flowing out of the tank by force of gravity, so as to reach said at least one component to be lubricated or cooled. The lubricating fluid system has at least one lift flow generator connected by at least one filling line to the tank and to at least one suction point present in a bottom of the sump. The lift flow generator fills the tank with the lubricating fluid present in said bottom at least during a starting phase.

A method (500) and apparatus (50, 60) for lubrication of a gearbox (30) of an aircraft engine comprise provision (502) of oil to the gearbox (30) through a primary oil system (50) driven by a core (11) of the engine (10) in normal conditions; detection (504) of windmilling conditions and/or failure of the primary oil system (50); and in response to the detected condition or failure, activation (506) of an electric pump (61) of an auxiliary oil system (60), to provide oil to the gearbox (30).