A combination starter-generator device is provided for a work vehicle having an engine. The starter-generator device includes an electric machine and a gear set configured to receive rotational input from the electric machine and the engine. The gear set includes a ring gear formed by a cylindrical base with a perimeter surface facing the engine and a circumferential row of castellations extending in a radial direction from the perimeter surface. The starter-generator device further includes a mounting arrangement comprising a drive plate configured to be secured to a crank shaft of the engine and a flex plate mounted to the drive plate. The flex plate includes a row of engagement apertures configured to receive the castellations of the ring gear to rotationally couple the ring gear to the engine via the mounting arrangement.

A power transmission device for a hybrid vehicle may include: a cover part mounted on a vehicle body; two motor parts embedded in the cover part; two rotor parts mounted in the respective motor parts and rotated; a transfer part selectively connected to the rotor part; a torsion damper part coupled to the transfer part; a clutch part configured to selectively connect any one of the rotor parts to the transfer part; and an output part connected to the clutch part and configured to discharge power to a transmission, wherein any one of the rotor parts is connected to the torsion damper part.

In at least some implementations, an automotive driveline unit includes a main housing having an interior and a first reservoir in the interior arranged to collect lubricant, the main housing also having a feed passage that is open to the first reservoir, a gear located within the interior and having a periphery arranged in the first reservoir so that rotation of the gear causes the gear to engage and displace some of the lubricant from the first reservoir, and a second housing carried by the main housing. A second reservoir is defined between the main housing and the second housing, the second reservoir is communicated with the first reservoir via the feed passage and includes multiple, spaced apart outlets through which lubricant exits the second reservoir at different locations to provide lubricant to different areas of the interior of the main housing.

The invention relates to a planetary gear box in a gas turbine engine, characterized by at least one protective device in the interior of a casing of the planetary gear box, wherein the protective device is designed and configured to divert at least one particle which is moving in the casing, in particular in an event of damage, and/or to extract kinetic energy from the moving at least one particle, in particular by deformation of the protective device, wherein the protective device is coupled to the casing of the planetary gear box, to a planet gear and/or to a planet carrier. The invention also relates to a gas turbine engine.

An engine for an aircraft comprises an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan comprising a plurality of fan blades; and a gearbox. The gearbox is an epicyclic gearbox and comprises a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted. The radial bending stiffness of the planet carrier is equal to or greater than 1.20×10.sup.9 N/m, and/or the tilt stiffness of the planet carrier is greater than or equal to 6.00×10.sup.8 Nm/rad. A method of operation of such an engine is also disclosed.

In an electric vehicle including a motor shaft connected to a drive motor, a counter shaft coupled with the motor shaft, a drive shaft coupled with the counter shaft, a drive wheel coupled with the drive shaft, a plurality of bearings configured to support the counter shaft, and a plurality of gears configured to rotate integrally with the counter shaft, a torque sensor is disposed in a region in which a slope of a bending moment occurring on the counter shaft is minimum at a time that the drive motor is driven.

Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines, including a gearbox for an aircraft gas turbine engine, the gearbox including: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.

Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines. A gearbox for an aircraft gas turbine engine includes: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.

An engine system includes a gearbox assembly that includes a housing having plural interconnected gears disposed between an engine side of the housing and an alternator side of the housing, a rotatable engine coupler connected with the engine side of the housing, the engine coupler configured to engage a rotatable shaft of an engine, and a rotatable alternator coupler connected with the alternator side of the housing, the alternator coupler configured to engage a rotor of a first alternator. The housing is configured to be positioned between the engine and the first alternator. The engine coupler is configured to engage the engine that is resiliently mounted in the powered system and the alternator coupler is configured to engage the first alternator that is rigidly mounted in the powered system to transfer rotation of the shaft of the engine to rotation of the rotor of the first alternator.

An apparatus includes a shared cooling device for cooling one or more systems or components, and a plurality of primary cooling pathways. Each of the primary cooling pathways includes a fan, and each fan is in fluid communication with the shared cooling device.