Rolls-Royce Deutschland Ltd & Co. Kg

Deutsches Zentrum Fur Luft-Und Raumfahrt E.v.

Anton Rudenko

Ellis F H Chong

Andreas Reeh

Johannes Gabriel Bauer

Sebastian Geier

Stefan Biser

Markus Kintscher

A transverse flux electrical machine for coupling to a rotating shaft of a propulsor of an aircraft is provided. The transverse flux electrical machine includes a rotor having a plurality of circumferentially distributed permanent magnets that form a number, N, of rotor poles, wherein the rotor poles have a pole pitch angle, P, equal to 2π divided by the number of rotor poles, N. The transverse flux electrical machine further includes a stator having a plurality of current-carrying coils configured to interact with the rotor poles of the rotor to produce a torque. The transverse flux electrical machine further includes an air gap separating the rotor from the stator by an air gap distance, G, wherein a machine parameter,, defined as:=P×Gis less than 100 micro radian-meters.

Electrical machines for aircraft power and propulsion systems

A vertical take-off and landing (VTOL) aircraft includes at least one electrical propulsion unit (EPU). An EPU of the at least one EPU includes a propeller or a fan and a transverse flux electric motor. The electric motor includes a stator having coils configured to carry current and a rotor arranged to interact with the stator, such that a torque for driving rotation of the propeller or the fan is generated. The rotor is configured to supply a flow of air to the coils, such that heat is removed from the coils. The coils are directly exposed to the flow of air, such that heat is exchanged directly from the coils to the flow of air. Each coil includes an effective cooling surface area directly exposed to the flow of air. An effective cooling surface area is at least 20% of a total surface area of the respective coil.

Electrical machines for aircraft power and propulsion systems with air cooling of coils

A transverse flux electric motor includes a stator including coils configured to carry current and a rotor arranged to interact with the stator. The rotor is configured to produce a torque for driving rotation of the rotor. The transverse flux electric motor has an active parts mass, m, equal to a cumulated mass of components of the transverse flux electric motor that contribute to the production of the torque. The transverse flux electric motor has an active parts torque density, ρ, defined as a peak rated torque, τ, divided by the active parts mass, m. The transverse flux electric motor has a power factor equal to cos(∅), wherein ∅ is a steady-state phase difference between a stator coil current and a stator coil voltage, and wherein the transverse flux electric motor has a machine parameter Δ that is greater than or equal to 65 Nmkg, where Δ equals ρ/cos(∅).

Electrical machines for aircraft power and propulsion systems having a defined machine parameter based on a ratio between an active parts torque density and a power factor

A vertical take-off and landing (VTOL) aircraft is provided. The VTOL aircraft includes at least one electrical propulsion unit (EPU), wherein an EPU of the at least one EPU includes a propeller or a fan. The EPU further includes an electric motor including a stator having insulated coils for carrying current and a rotor arranged to interact with the stator, such that a torque for driving rotation of the propeller or the fan is produced.

An electrical power system for an aircraft includes a DC:AC power electronics converter and a transverse flux electrical machine. The transverse flux electrical machine includes a rotor that is coupleable to a rotating shaft of a propulsor of the aircraft, wherein the rotor includes a plurality of permanent magnets defining a number, N, of evenly distributed rotor poles. The transverse flux electrical machine further includes a stator arranged to interact with the rotor, such that a torque is produced. The stator includes a plurality of coils.

An electrical propulsion unit (EPU) for a vertical take-off and landing (VTOL) aircraft is provided. The EPU includes a propeller or a fan and an electric motor. The electric motor includes a stator comprising coils configured to carry current and a rotor arranged to interact with the stator. The rotor is configured to generate a torque for driving rotation of the propeller or the fan. The coils of the stator have a cumulated conductor volume VThe stator, the rotor, or the stator and the rotor include a flux guiding iron material configured to guide magnetic flux generated by the coils of the stator, wherein the flux guiding iron material has a cumulated iron volume V, and wherein the electric motor has a machine parameter &#x393; that is greater than or equal to 0.25, &#x393; being defined as: &#x393;=V/V.

The present invention provides a rotor, an axial flux electrical machine and a hybrid-electrical or electrical air craft. The rotor for the axial flux electrical machine comprises first sections of a first material and second sections of a second material. The first sections and second sections are arranged in alternating order and ring-shape. The arrangement is characterized by third sections which form interface areas between the first sections and second sections, whereas the third sections are comprising the first material and the second material in such a manner that the first section and the second section are connected force-fitted.

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Ottobrunn, Germany

Anton Rudenko