A lubricant system for a gear assembly of an aircraft is presented. The lubricant system includes a main lubricant conduit and an emergency lubricant conduit joined with a valve, and further wherein the valve defines a closed position disposing lubricant through the emergency lubricant conduit when an engine is at rest, and wherein the valve defines an open position disposing lubricant through the main lubricant conduit when the engine is in operation.

A vehicle drive apparatus including a case member having a bottom wall portion and a side wall portion to form a reservoir space of oil which includes a first reservoir space radially inward of a shaft support member, a second reservoir space between the shaft support member and a ring gear, and a third reservoir space radially outward of the ring gear, a first passage provided in the shaft support member to communicate the first reservoir space and the second reservoir space, a second passage provided in the ring gear to communicate the second reservoir space and the third reservoir space, and an oil passage forming part configured to form an oil passage to communicate with the first reservoir space at a first end of the oil passage and communicate with an oil pump at a second end of the oil passage.

A drive device for a motor vehicle having a drive assembly that is operatively connected or can be operatively connected to an input shaft of a gearbox. A gear set of the gearbox can be supplied with lubricant by a primary lubricant pump. The primary lubricant pump is coupled to an output shaft of the gearbox.

A lubricant system includes a first gearbox defining a first internal cavity, a second gearbox defining a second internal cavity, a first lubricant cooler positioned external the first and second internal cavities, a second lubricant cooler positioned external the first and second internal cavities, and a plurality of fluid passages fluidly connecting the first lubricant cooler and second lubricant coolers to each of the first gearbox and the second gearbox. The first lubricant cooler and the second lubricant cooler are configured to hold lubricant. The fluid passages include a first main fluid passage fluidly connecting the first lubricant cooler to the first gearbox, a second main fluid passage fluidly connecting the second lubricant cooler to the second gearbox, a first auxiliary passage fluidly connecting the first lubricant cooler to the second gearbox, and a second auxiliary passage fluidly connecting the second lubricant cooler to the first gearbox.

A drive system for a rotorcraft includes first and second gearbox assemblies and a lubrication assembly. The lubrication assembly includes first and second lubrication systems and a valve connected between the first and second lubrication systems such that when the valve is in a first position, a test mode of operation of the lubrication assembly is enabled and when the valve is in a second position, a normal mode of operation of the lubrication assembly is enabled.

The lubrication assembly also includes a valve control unit operable to instruct the valve to selectively move between the first position and the second position.

A lubrication device for a helicopter including: an oil sump in which oil for lubrication is retained; a lubrication pump configured to suck the oil from the oil sump to discharge the oil; and a lubrication passage extending from the lubrication pump to a first lubrication target. The lubrication passage includes: a first supply port that supplies the oil to the first lubrication target; an oil reservoir provided upstream of the first supply port; and an opening provided upstream of the oil reservoir and above the oil reservoir. The first supply port is formed right above the first lubrication target.

A gas turbine engine includes a fan drive turbine, a fan rotor, and a gear reduction driven by the fan drive turbine and, in turn, to drive the fan rotor. A main oil supply system supplies oil to components within the gear reduction, and an auxiliary oil supply system. The auxiliary oil supply system includes a rotation sensor for sensing rotation of a component that will rotate with the fan rotor, a control, an auxiliary oil pump, and a main supply sensor for sensing operation of the main oil supply system. The control is programmed to supply oil from the auxiliary oil pump to the gear reduction when the rotation sensor senses the component is rotating. A determination is made that inadequate oil is being supplied from the main oil supply system based upon information from the main supply sensor.

A gas turbine engine for an aircraft including a unit supplied with oil from a first oil circuit and a second oil circuit. The first oil circuit and the second oil circuit each are fluidly coupled with at least one inlet and with at least one outlet of the unit and with at least one inlet and with at least one outlet of an oil tank. The first oil circuit and the second oil circuit are configured to receive oil from the oil tank and to direct the received oil to the unit. The oil tank is incorporating offset outlets to each of the oil circuits. The offset outlet of the second oil circuit is positioned higher in the oil tank than the offset outlet of the first oil circuit.

A lubrication system for a gas turbine engine, the system comprising: a gearbox, the gearbox comprising a sump; an oil tank; a primary gearbox lubrication system configured to pump oil from the oil tank to lubricate the gearbox with a gearbox primary feed; a secondary gearbox lubrication system, configured to lubricate the gearbox with oil from the sump when the oil level in the sump reaches a predetermined level; wherein the system is configured to increase the oil level in the sump to at least the predetermined level in response to a failure of the primary gearbox lubrication system.

According to one embodiment, a rotorcraft includes a body, a rotor blade, a drive system that can be operated to rotate the rotor blade, and an emergency valve control unit. The drive system contains a first gearbox assembly, a second gearbox assembly, a first lubrication system that can deliver lubricant to the first gearbox assembly, and a second lubrication system that can deliver lubricant to the second gearbox assembly. The drive system also contains an emergency valve that can be opened to deliver lubricant from the first lubrication system to the second gearbox assembly. The emergency valve control unit can instruct the emergency valve to open.