An electrically-actuated variable camshaft timing (VCT) phaser assembly, comprises a sun gear configured to receive input from an electric motor and one or more planet gears having radially-outwardly-extending gear teeth that engage the sun gear; a first ring gear, having radially-inwardly extending gear teeth that engage the radially-outwardly-extending gear teeth of the sun gear, configured to receive rotational output provided by a crankshaft; a second ring gear, having radially-inwardly extending gear teeth that engage the radially-outwardly-extending gear teeth of the sun gear, configured to couple to a camshaft; one or more planet gear pins that carry the planet gear(s) and engage a planetary gear set to prevent the relative rotation of the planet gear pin(s) relative to the planetary gear set; and one or more springs that bias the planet gear pin(s) and the planetary gear(s) toward the first ring gear and the second ring gear.

An electrically-actuated variable camshaft timing (VCT) device, comprising: an input configured to receive rotational force from an electric motor; an output configured to couple with a camshaft of an internal combustion engine; a planet gear having radially outwardly extending gear teeth configured to engage ring gears and a radially-inwardly-facing surface; a planet pin, supporting the planet gear, having an outer surface and an axis of rotation about which the planet gear rotates; and a spring applying force in a substantially axial direction along the axis of rotation that moves the planet gear in a radial direction.

Apparatuses, systems, and methods apply, with a fan, a braking force to a vehicle that includes an axle. The fan is rotated at a first rotational speed based on a rotation of the axle that rotates at a second rotational speed. The first rotational speed is different from the second rotational speed. The fan applies the braking force when the fan rotates at the first rotational speed.

A turbofan gas turbine engine includes, among other things, a fan section including a fan hub and an outer housing, the fan hub including a hub diameter supporting a plurality of fan blades, a turbine section including a fan drive turbine, and a geared architecture that interconnects the fan drive turbine and the fan hub, the geared architecture including a gear volume.

A turbofan gas turbine engine includes, among other things, a fan section including a fan hub and an outer housing, the fan hub including a hub diameter supporting a plurality of fan blades, a turbine section including a fan drive turbine, and a geared architecture that interconnects the fan drive turbine and the fan hub, the geared architecture including a gear volume.

The present disclosure is directed to a turbine engine (10) defining an axial direction and a radial direction. The turbine engine includes a fan or propeller assembly (14) comprising a gearbox; an engine core (20) comprising one or more rotors, wherein at least one of the rotors defines an axially extended annular hub; and a flexible coupling shaft (100) defining a first end and a second end along the axial direction, wherein the first end is connected to the engine core and the second end is connected to the gearbox, and further wherein the flexible coupling shaft extends from the one or more rotors to the gearbox in the axial direction and inward of the hub in the radial direction.

The present disclosure is directed to a turbine engine (10) defining an axial direction and a radial direction. The turbine engine includes a fan or propeller assembly (14) comprising a gearbox; an engine core (20) comprising one or more rotors, wherein at least one of the rotors defines an axially extended annular hub; and a flexible coupling shaft (100) defining a first end and a second end along the axial direction, wherein the first end is connected to the engine core and the second end is connected to the gearbox, and further wherein the flexible coupling shaft extends from the one or more rotors to the gearbox in the axial direction and inward of the hub in the radial direction.

An improved roller shade system provides increased support, additional adjustments and/or increased safety. The slip plate allows the brake to slip forward and minimize damage to the clutch spring when a user pulls too hard on the hembar. The center drive mechanism extends through a bracket to allow the drive shaft to distribute power in both directions and drive two shade tube simultaneously. The tube adapter absorbs force from the spinning shade tube to minimize damage to the other components and the bead chain. The sprocket has a back wall supporting the sprocket, allowing the sprocket 130 to rest on the back flange of the sun gear to minimize pressure on the gears. An adjustment arm is adjusted to help level the shade band. The shade bands may be removed without disturbing the other shade bands in the system. A height of a hembar may be adjusted by rotating a rod within the hembar.

An actuator capable of achieving high output with a smaller number of parts is proposed. An actuator including a stator that has teeth arranged on an outer peripheral surface, a rotor that rotates around a central axis of the stator while teeth arranged on an outer peripheral surface mesh with the teeth arranged on the outer peripheral surface of the stator, and a second gear that rotates while meshing with a first gear coupled to the rotor coaxially with a central axis of the rotor and is coupled to an output shaft, in which the stator has an electromagnet, the rotor has a magnet, and a magnetic pole of the electromagnet corresponding to a position of the rotor moves along a circumferential direction of the stator.

A mechanical gearbox for an aircraft turbomachine includes a sun gear having an axis (X) of rotation, a ring gear around the sun gear, and planet gears meshed with the sun gear and the ring gear. Each planet gear has a first toothing meshed with the sun gear and a second loathing meshed with the ring gear. The first toothing includes a series of upstream teeth and a series of downstream teeth located on either side of a plane (H) perpendicular to the axis (X) of rotation of the sun gear. The second toothing includes a series of upstream teeth and a series of downstream teeth located on either side of the plane (H) and separated from one another by the first toothing, these teeth being parallel to one another and to the axis (Y) of rotation of the planet gear.