Disclosed is a mechanically operational arrangement for continuously variable transmission, comprising a central shaft (1), wherein a toothed groove section (8) is circumferentially arranged in a middle portion of an external surface of the central shaft (1); wherein a shaft sleeve (9) is fitted over the external surface of the central shaft (1); wherein a plurality of axial limiting grooves (10) are provided on an external surface of the shaft sleeve (9); wherein inserted into each axial limiting groove (10) is a connecting plate (6); wherein an arc-shaped toothed wheel section (7) is arranged on an inner end face of each connecting plate (6); wherein each of the arc-shaped toothed wheel sections (7) is meshed with the toothed groove section (8); wherein a pivot (11) is mounted in a side face of each connecting plate (6); and wherein each connecting plate (6) is respectively hinged to a groove wall of one axial limiting groove (10) via the respective pivot (11). The mechanically operational arrangement for continuously variable transmission solves the problems existing in the prior art of continuously variable transmission arrangement that has an easily damaged steel belt with structural complexity and inconvenient maintenance.

An electric power generating device (1) capable of suppressing an increase of a frontal surface area of an aircraft engine includes a transmission (22) connected with a rotary shaft (9) of the engine (E), an electric power generator (34) driven by an output of the transmission (22), an input shaft (27) having a shaft axis extending in a direction crossing the rotary shaft (9) and connected with the rotary shaft (9), and a transmitting mechanism (21) connected with the input shaft (27) to drive the transmission (22) about an axis extending in a direction perpendicular to the input shaft (27). The transmission (22) and the electric power generator (34) are disposed spaced a distance from each other in a direction circumferentially of the rotary shaft (9).

An electric power generating device (1) capable of suppressing an increase of a frontal surface area of an aircraft engine includes a transmission (22) connected with a rotary shaft (9) of the engine (E), an electric power generator (34) driven by an output of the transmission (22), an input shaft (27) having a shaft axis extending in a direction crossing the rotary shaft (9) and connected with the rotary shaft (9), and a transmitting mechanism (21) connected with the input shaft (27) to drive the transmission (22) about an axis extending in a direction perpendicular to the input shaft (27). The transmission (22) and the electric power generator (34) are disposed spaced a distance from each other in a direction circumferentially of the rotary shaft (9).

A transmission and components thereof are provided. In one aspect, the transmission component has one or more formations, the one or more formations being substantially elongate and running along an engagement face of the component, the formation(s) configured to be frictionally engagable with a substantially elongate recess of a second transmission component; and/or (ii) one or more recesses, the one or more recesses being substantially elongate and running along an engagement face of the component, the recess(es) configured to be frictionally engagable with a substantially elongate formation of a second transmission component. In a second aspect, the transmission has a first transmission component and a second transmission component having one or more substantially elongate recesses, wherein the formation(s) of the first transmission component are frictionally engageable with the recess(es) of the second transmission component, such that in use the first transmission component is capable of driving the second transmission component. In a third aspect, a method for improving the torque density of a transmission is provided by setting or adjusting an amount of frictional engagement between two components involved in the torque flow through the transmission.

A number of variations may include a product comprising: an orifice flow valve comprising: a disk, wherein the disk comprises at least one orifice which is constructed and arranged to direct a forward flow of a fluid through the at least one orifice and to impede a backflow of the fluid through the at least one orifice.