An aircraft hybrid propulsion system (5) comprises an internal combustion engine (10) comprising a main drive shaft (24), an electric machine (28) comprising an electric machine rotor (78), a propulsor (12) mounted to a propulsor shaft (62), and a clutch arrangement configured to selectively couple each of the gas turbine engine main drive shaft (24) and electric machine rotor (78) to the propulsor drive shaft (62). The electric machine rotor (78) is mounted coaxially with the main drive shaft (24) and the clutch arrangement comprises a first overrunning clutch (52) configured to couple the main drive shaft (24) to the propulsor drive shaft (62), and a second overrunning clutch (54) configured to couple the electric machine rotor (78) to the propulsor drive shaft (62).

A mounting system for mounting a supplemental alternator, as well as methods of assembling the same, is provided. The mounting system includes a top mounting bracket that is configured to align with a top flange aperture of the additional alternator. The mounting system also includes a bottom mounting bracket having a bracket aperture that aligns with an aperture of an existing alternator mount and also having a flange aperture that aligns with the foot flange aperture of the additional alternator. The mounting system further includes a shaft that couples to the additional alternator.

A mounting system for mounting a supplemental alternator, as well as methods of assembling the same, is provided. The mounting system includes a top mounting bracket that is configured to align with a top flange aperture of the additional alternator. The mounting system also includes a bottom mounting bracket having a bracket aperture that aligns with an aperture of an existing alternator mount and also having a flange aperture that aligns with the foot flange aperture of the additional alternator. The mounting system further includes a shaft that couples to the additional alternator.

An after-fan system for an engine may comprise an after-fan turbine an electrical generator operationally coupled to the after-fan turbine, and an electric motor electrically coupled to the electrical generator. The electrical generator may be configured to generate an electrical current in response to rotation of the after-fan turbine. The electric motor may be configured to generate torque.

An after-fan system for an engine may comprise an after-fan turbine an electrical generator operationally coupled to the after-fan turbine, and an electric motor electrically coupled to the electrical generator. The electrical generator may be configured to generate an electrical current in response to rotation of the after-fan turbine. The electric motor may be configured to generate torque.

A method for controlling an electrical exhaust gas turbocharger of an internal combustion engine includes a measure (a), in accordance with which a load requirement placed on the internal combustion engine is monitored, and a measure (b), in accordance with which a boost mode of the electrical exhaust gas turbocharger is activated if the load requirement monitored in measure (a) exceeds a predetermined threshold value.

A method for controlling an electrical exhaust gas turbocharger of an internal combustion engine includes a measure (a), in accordance with which a load requirement placed on the internal combustion engine is monitored, and a measure (b), in accordance with which a boost mode of the electrical exhaust gas turbocharger is activated if the load requirement monitored in measure (a) exceeds a predetermined threshold value.

A starter/generator system that includes a first and second electric machine. The first electric machine has a first rotor and a first stator where the first rotor is adapted to receive kinetic energy and the first stator includes a first set of windings. The second electric machine has a second rotor rotatable and a second stator. The second stator is fixed relative to the first stator and the second stator includes a second set of windings.

A starter/generator system that includes a first and second electric machine. The first electric machine has a first rotor and a first stator where the first rotor is adapted to receive kinetic energy and the first stator includes a first set of windings. The second electric machine has a second rotor rotatable and a second stator. The second stator is fixed relative to the first stator and the second stator includes a second set of windings.

The disclosure relates to a load cell for a linear actuator. The load cell configured to measure a force exerted thereon by a rotary motor, and includes a spring element, a hollow portion and at least one strain gauge. The spring element includes a first side and a second side. The first side and the second side are opposite to each other. The hollow portion passes through the spring element. The at least one strain gauge is secured on the spring element and located between the first side and the second side, wherein when the force is exerted on the spring element when the rotary motor is driven to move along the first direction, the second side is moved relative to the first side, the spring element is deformed, and the at least one strain gauge changes shape, so that the force is measured and standardized under a specific range.