The invention relates to a continuously variable transmission and a transmission system comprising said continuously variable transmission, wherein the continuously variable transmission comprises a first gear pump and a second gear pump, wherein each gear pump comprises a first gear and a second gear meshing with the first gear over an overlap distance in an overlap direction parallel to the first gear axis, wherein each gear pump further comprises an adjustment member for adjusting the pump volume, wherein the adjustment member of the first gear pump and the adjustment member of the second gear pump are interconnected by a connecting member for adjusting the pump volume of the first gear pump and the pump volume of the second gear pump in an inverse correlation to each other.

The invention relates to a continuously variable transmission and a transmission system comprising said continuously variable transmission, wherein the continuously variable transmission comprises a first gear pump and a second gear pump, wherein each gear pump comprises a first gear and a second gear meshing with the first gear over an overlap distance in an overlap direction parallel to the first gear axis, wherein each gear pump further comprises an adjustment member for adjusting the pump volume, wherein the adjustment member of the first gear pump and the adjustment member of the second gear pump are interconnected by a connecting member for adjusting the pump volume of the first gear pump and the pump volume of the second gear pump in an inverse correlation to each other.

A stator of a torque converter is divided into a first stator on an upstream side and a second stator on a downstream side, and the first and second stators are supported on a fixed part via first and second one-way clutches, respectively. Since, with regard to a blade of the first stator, when viewed in the axis direction, the blade tip part is inclined relative to the blade base part in the disengagement direction of the first one-way clutch, it is possible to ensure the blade area without increasing the dimension in the radial direction and the dimension in the axis direction of the blade of the first stator, and it is possible, by smoothly guiding oil along the blade of the first stator to thus suppress the occurrence of a vortex, to reduce energy loss in a low speed ratio region where the vortex easily occurs.

A transmission includes a torque converter stator with controllable blade angle. The blade angle is adjusted by adjusting the rotational position of a control ring with respect to a stator hub. The stator blades are supported by the stator hob, a locking ring, and an outer ring. The stator blades have teeth that mesh with teeth on the control ring to determine blade angle. A controller adjust the blades by commanding fluid pressures in hydraulic circuits routed to the stator hub. Various circumstances in which the controller would adjust the blade angle are discussed.

A transmission includes a torque converter stator with controllable blade angle. The blade angle is adjusted by adjusting the rotational position of a control ring with respect to a stator hub. The stator blades are supported by the stator hob, a locking ring, and an outer ring. The stator blades have teeth that mesh with teeth on the control ring to determine blade angle. A controller adjust the blades by commanding fluid pressures in hydraulic circuits routed to the stator hub. Various circumstances in which the controller would adjust the blade angle are discussed.

An aircraft engine includes at least one electrical apparatus, which can be driven by a driveshaft in order to generate electrical energy. A hydrodynamic torque converter, with guide blades, which can be adjusted via a mechanism, is arranged between the driveshaft and the electrical apparatus. The guide blades are adjusted as a function of a rotational speed of the driveshaft, wherein the rotational speed of a shaft of the electrical apparatus operated as a generator can be adjusted, essentially within a predefined rotational speed range, via the adjustment of the guide blades.

An aircraft engine includes at least one electrical apparatus, which can be driven by a driveshaft in order to generate electrical energy. A hydrodynamic torque converter, with guide blades, which can be adjusted via a mechanism, is arranged between the driveshaft and the electrical apparatus. The guide blades are adjusted as a function of a rotational speed of the driveshaft, wherein the rotational speed of a shaft of the electrical apparatus operated as a generator can be adjusted, essentially within a predefined rotational speed range, via the adjustment of the guide blades.