US 12,261,512 B2
Actuation system for an aircraft engine lubrication pump and associated aircraft
Nicolas Bertrand Georges De Blois, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/995,332
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Mar. 26, 2021, PCT No. PCT/FR2021/050531
§ 371(c)(1), (2) Date Oct. 3, 2022,
PCT Pub. No. WO2021/198597, PCT Pub. Date Oct. 7, 2021.
Claims priority of application No. 2003368 (FR), filed on Apr. 3, 2020.
Prior Publication US 2023/0142269 A1, May 11, 2023
Int. Cl. F02C 7/06 (2006.01); H02K 7/18 (2006.01); H02K 7/20 (2006.01); H02K 11/21 (2016.01)
CPC H02K 7/1823 (2013.01) [F02C 7/06 (2013.01); H02K 7/20 (2013.01); H02K 11/21 (2016.01); F05D 2220/323 (2013.01); F05D 2220/76 (2013.01)] 8 Claims
OG exemplary drawing
 
1. An actuation system for a lubrication pump of an aircraft engine, including a generator rotating electric machine, a drive rotating electric machine, a control device and a matrix of switches,
the generator rotating electric machine comprising a first rotor, intended to be mechanically coupled to a shaft of the aircraft engine forming a drive shaft, and a first stator comprising at least one output stator winding,
the drive rotating electric machine comprising a second rotor, intended to be mechanically coupled to the lubrication pump for its actuation, and a second stator comprising at least one input stator windings,
the matrix of switches being electrically connected, on the one hand, to the at least one output stator winding and, on the other hand, to the at least one input stator winding so as to electrically connect or disconnect the at least one output stator winding and the at least one input stator winding to/from each other,
the control device being configured to, according to a state of a control signal, control the matrix of switches so as to electrically connect the at least one output stator winding and the at least one input stator winding to each other or not,
the control device further being configured to control a configuration of the matrix of switches, according to a direction of rotation of the first rotor of the generator rotating electric machine, the control device being configured to place the matrix of switches in a first configuration of switches when the first rotor of the generator rotating electric machine has a first direction of rotation and is further configured to place the matrix of switches in a second configuration of switches different from said first configuration of switches when the first rotor of the generator rotating electric machine has a second direction of rotation opposite to the first direction of rotation, the first configuration of switches and the second configuration of switches being provided so that when the first rotor of the generator rotating electric machine is driven in rotation in the first direction, the second rotor has a given direction of rotation, and when the first rotor of the generator rotating electric machine is driven in rotation in the second direction, the second rotor retains the said given direction of rotation.