US 11,990,805 B1
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
Ellis F H Chong, Derby (GB); Andreas Reeh, Nuremberg (DE); Johannes Gabriel Bauer, Neuried (DE); and Anton Rudenko, Ottobrunn (DE)
Assigned to Rolls-Royce Deutschland Ltd & Co KG, Blankenfelde-Mahlow (DE)
Filed by Rolls-Royce Deutschland Ltd & Co KG, Blankenfelde-Mahlow (DE)
Filed on May 24, 2023, as Appl. No. 18/201,638.
Claims priority of application No. 2300388 (GB), filed on Jan. 11, 2023.
Int. Cl. H02K 1/14 (2006.01); B64C 29/00 (2006.01); B64D 27/24 (2006.01); B64D 33/08 (2006.01); H02K 3/24 (2006.01); H02K 21/24 (2006.01)
CPC H02K 21/24 (2013.01) [B64C 29/0025 (2013.01); B64D 27/24 (2013.01); B64D 33/08 (2013.01); H02K 1/145 (2013.01); H02K 3/24 (2013.01); H02K 2201/12 (2013.01); H02K 2213/03 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A transverse flux electric motor comprising:
a stator comprising coils configured to carry current; and
a rotor arranged to interact with the stator, the rotor configured to produce a torque for driving rotation of the rotor,
wherein the transverse flux electric motor has an active parts mass, mact, equal to a cumulated mass of components of the transverse flux electric motor that contribute to the production of the torque,
wherein the transverse flux electric motor is configured to produce a peak rated torque, τpeak,
wherein the transverse flux electric motor has an active parts torque density, ρact, defined as the peak rated torque, τpeak, divided by the active parts mass, mact,
wherein 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 95 Nmkg−1, Δ being equal to:

OG Complex Work Unit Math