US 12,030,662 B2
Propulsion system for a helicopter
Romain Jean Gilbert Thiriet, Moissy-Cramayel (FR); Olivier Bedrine, Moissy-Cramayel (FR); and Antoine Pascal Moutaux, Moissy-Cramayel (FR)
Assigned to SAFRAN HELICOPTER ENGINES, Bordes (FR)
Appl. No. 17/769,939
Filed by SAFRAN HELICOPTER ENGINES, Bordes (FR)
PCT Filed Oct. 15, 2020, PCT No. PCT/FR2020/051843
§ 371(c)(1), (2) Date Apr. 18, 2022,
PCT Pub. No. WO2021/074537, PCT Pub. Date Apr. 22, 2021.
Claims priority of application No. 1911599 (FR), filed on Oct. 17, 2019.
Prior Publication US 2022/0388673 A1, Dec. 8, 2022
Int. Cl. B64D 35/08 (2006.01); B64C 27/12 (2006.01); B64D 27/24 (2006.01); B64D 27/02 (2006.01)
CPC B64D 35/08 (2013.01) [B64C 27/12 (2013.01); B64D 27/24 (2013.01); B64D 27/026 (2024.01)] 16 Claims
OG exemplary drawing
 
1. A propulsion system (1) for a helicopter, comprising:
a turboshaft engine (2) with a linked turbine and a rotor (2a);
an electric machine (3) capable of operating as an electric motor with a rotor (3a), the turboshaft engine (2) and the electric machine (3) being capable of driving in rotation at least one main rotor (5) intended to be coupled to a rotating wing (6); and
means of coupling and decoupling (14) in rotation between the rotor (3a) of the electric machine (3) and the rotor (2a) of the turboshaft engine (2),
the means of coupling and decoupling (14) being capable of allowing the rotor (2a) of the turboshaft engine (2) to be driven in rotation with the aid of the electric machine (3), in a first state of the propulsion system (1), and capable of allowing the rotor (2a) of the turboshaft engine (2) and the rotor (3a) of the electric machine (3) to be decoupled in rotation, in a second state of the propulsion system (1).