A hybrid drive module is disclosed. An exemplary embodiment of the present invention provides a hybrid drive module that selectively transmits torque transmitted from an engine and a motor to a transmission including a housing disposed between the engine and the transmission, a drive shaft rotatably mounted inside the housing in a radial direction with its one end portion toward the engine based on an axial direction protruding from the housing and to which torque of the engine is inputted, a rotor hub provided within the housing and mounted with a rotor of the motor on its radially outer side, and in which a hub plate part integrally extending toward the drive shaft and rotatably connected to the other end portion of the drive shaft toward the transmission based on the axial direction is formed on its radially inner side, a rotor hub ridge, an inner circumferential surface of which is rotatably supported by the housing based on the radial direction and an external circumferential surface of which is fixed to the rotor hub based on the axial direction at the side of the engine, an engine clutch disposed at the engine side in the axial direction with the hub plate part interposed therebetween, and configured to directly connect the drive shaft and the rotor hub to selectively transmit the torque of the engine to the rotor hub, and a torque converter disposed at the side of the transmission in the axial direction with the hub plate part interposed therebetween to be connected to the rotor hub, and configured to multiply the torque of the engine, torque of the motor, or the torque of the engine and the motor when a vehicle is initially driven, or to transmit it to the transmission in a ratio of 1:1, wherein at least one fluid groove for supplying an operating fluid to the rotor to cool the rotor between the rotor hub and the engine clutch is formed on a surface of the hub plate part toward the engine clutch based on the axial direction.

A motor-driven power steering system for a vehicle is configured such that movement of the worm shaft and a clearance caused by backlash between the worm wheel and the worm shaft may be prevented using the bearing-integrated damper bush which is coupled to the end portion of the worm shaft and is made of steel, and during of rotation of the worm shaft, the lubricant is supplied between the worm shaft and the bearing-integrated damper bush to facilitate lubrication and cooling.

An oil restrictor for emergency lubrication of a component for an aircraft turbine engine includes a metal cylindrical body having a longitudinal axis and configured to be housed in and shrink-fitted into a cylindrical bore of a part of the turbine engine. The restrictor further includes an integrated oil circuit enabling oil to pass through the restrictor along the axial extent thereof. The body is a one-piece body, and the circuit has at least two oil channels recessed on an outer cylindrical surface of the body and extending around and/or along the axis.

Gearboxes for aircraft gas turbine engines, in particular to arrangements for journal bearings such gearboxes, and to related methods of operating such gearboxes and gas turbine engines. Example embodiments include 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.

Provided herein is an axle assembly, including: a carrier housing defining an interior cavity; a pinion shaft rotatably supported in the carrier housing by at least one bearing; a lubricant channel disposed in the carrier housing, the lubricant channel having a first end in fluid communication with the at least one bearing and a second end in fluid communication with the interior cavity; and a lubricant controller at least partially disposed in the lubricant channel, wherein the lubricant controller includes a lubricant capture portion.

Gearboxes for aircraft gas turbine engines, in particular to arrangements for journal bearings such gearboxes, and to related methods of operating such gearboxes and gas turbine engines. Example embodiments include 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.

A shroud is provided and includes first and second curved sections, at least one of which defines a main interior channel and at least one of first and second lube jet sections integrated with the first and second curved sections. The first lube jet section includes a summit at which proximal portions of the first and second curved sections meet and defines a first jetting interior channel fluidly communicative with the main interior channel and terminating at the summit The second lube jet section includes an elongate member extending from one of the first and second curved sections and defines a second jetting interior channel fluidly communicative with the main interior channel and terminating at a distal end of the elongate member.

Gearboxes for aircraft gas turbine engines, in particular to arrangements for journal bearings such gearboxes, and to related methods of operating such gearboxes and gas turbine engines. Example embodiments include 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 to arrangements for journal bearings such gearboxes, and to related methods of operating such gearboxes and gas turbine engines. Example embodiments include 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.

A gear system includes at least one gear stage, a pump system and oil channels for circulating a first lubricant oil flow via first elements of the gear stage and a second lubricant oil flow via second elements of the gear stage, and an oil conditioning system for controlling temperatures of the first and second lubricant oil flows so that the temperatures of the first and second lubricant oil flows are different from each other and flow rates of the first and second lubricant oil flows are different from each other. Thus, it is possible to utilize for example the fact that bearings do not need as much oil flow as gear wheels but, on the other hand, lowering oil temperature of the bearings provides more advantages than lowering oil temperature of the gear wheels.