US 12,110,128 B2
Transmission device for hybrid aircraft
Benjamin Nicolas Fulleringer, Moissy-Cramayel (FR); Antoine Pascal Moutaux, Moissy-Cramayel (FR); and Romain Jean Gilbert Thiriet, Moissy-Cramayel (FR)
Assigned to SAFRAN HELICOPTER ENGINES, Bordes (FR)
Appl. No. 18/559,224
Filed by SAFRAN HELICOPTER ENGINES, Bordes (FR)
PCT Filed Apr. 25, 2022, PCT No. PCT/FR2022/050779
§ 371(c)(1), (2) Date Nov. 6, 2023,
PCT Pub. No. WO2022/234210, PCT Pub. Date Nov. 10, 2022.
Claims priority of application No. 2104791 (FR), filed on May 6, 2021.
Prior Publication US 2024/0239509 A1, Jul. 18, 2024
Int. Cl. B64D 35/022 (2024.01); B64C 27/12 (2006.01); B64D 35/08 (2006.01); F01D 15/10 (2006.01); F02C 7/32 (2006.01)
CPC B64D 35/022 (2024.01) [B64D 35/08 (2013.01); F01D 15/10 (2013.01); F02C 7/32 (2013.01); B64C 27/12 (2013.01); F05D 2220/50 (2013.01); F05D 2220/76 (2013.01)] 10 Claims
OG exemplary drawing
 
1. A transmission device for a hybrid aircraft, the aircraft comprising a turbomachine including at least one gas generator, a free turbine rotationally driven by a stream of gas generated by the gas generator, and a main rotor, the transmission device comprising a first reversible electric machine able to be coupled to a shaft of the free turbine by way of a first deactivatable coupling means, and to the main rotor, and a second reversible electric machine able to be coupled to a shaft of the gas generator by way of a second deactivatable coupling means, and to be coupled to the main rotor by way of a third deactivatable coupling means, the second deactivatable coupling means being configured to be activated when the second electric machine rotates in a first direction of rotation, and the third deactivatable coupling means being configured to be activated when the second electric machine rotates in a second direction of rotation opposite to the first direction of rotation.