An example includes a hydraulically controllable coupling to couple a rotating input and to an output to rotate, or to decouple the input and the output, with coupling and decoupling modes selected by switching a hydraulic device such as a vane pump between a pumping mode and a mode in which it does not pump. In an example, the system cooperates with a transmission to increase the number of possible gear ratios in some examples.

An example includes a hydraulically controllable coupling to couple a rotating input and to an output to rotate, or to decouple the input and the output, with coupling and decoupling modes selected by switching a hydraulic device such as a vane pump between a pumping mode and a mode in which it does not pump. In an example, the system cooperates with a transmission to increase the number of possible gear ratios in some examples.

An example includes a hydraulically controllable coupling to couple a rotating input and to an output to rotate, or to decouple the input and the output, with coupling and decoupling modes selected by switching a hydraulic device such as a vane pump between a pumping mode and a mode in which it does not pump. In an example, the system cooperates with a transmission to increase the number of possible gear ratios in some examples.

An example includes a hydraulically controllable coupling to couple a rotating input and to an output to rotate, or to decouple the input and the output, with coupling and decoupling modes selected by switching a hydraulic device such as a vane pump between a pumping mode and a mode in which it does not pump. In an example, the system cooperates with a transmission to increase the number of possible gear ratios in some examples.

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.