公开(公告)号：US12110128B2

公开(公告)日：2024-10-08

申请号：US18559224

申请日：2022-04-25

申请人： SAFRAN HELICOPTER ENGINES

发明人： Benjamin Nicolas Fulleringer ,  Antoine Pascal Moutaux ,  Romain Jean Gilbert Thiriet

IPC分类号： B64D35/022 ,  B64C27/12 ,  B64D35/08 ,  F01D15/10 ,  F02C7/32

CPC分类号： B64D35/022 ,  B64D35/08 ,  F01D15/10 ,  F02C7/32 ,  B64C27/12 ,  F05D2220/50 ,  F05D2220/76

摘要： A device for a hybrid aircraft including a turboshaft engine having a gas generator, a free turbine, and a main rotor. The device includes a first reversible electric machine coupled to a shaft of the free turbine by way of a first free wheel, and to the main rotor. The device further includes a second reversible electric machine coupled to a shaft of the gas generator by way of a second free wheel, and coupled to the main rotor by way of a third free wheel. The second free wheel activates when the second electric machine rotates in a first direction of rotation, and the third free wheel activates when the second electric machine rotates in a second direction of rotation opposite to the first direction of rotation.

公开(公告)号：US12060807B2

公开(公告)日：2024-08-13

申请号：US17287487

申请日：2019-10-10

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Gilles Alain Marie Charier ,  Caroline Marie Frantz ,  Loïc Paul Yves Guillotel ,  Vincent François Georges Millier

IPC分类号： F01D5/02 ,  B64D27/33 ,  B64D35/022 ,  B64D35/023 ,  B64D35/024 ,  B64D35/026 ,  F01D15/10 ,  F02C7/268 ,  F02C7/32 ,  F02C7/36

CPC分类号： F01D5/02 ,  B64D27/33 ,  B64D35/022 ,  B64D35/023 ,  B64D35/024 ,  B64D35/026 ,  F01D15/10 ,  F02C7/268 ,  F02C7/32 ,  F02C7/36 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2230/60 ,  F05D2240/20 ,  F05D2240/60

摘要： An aircraft turbine engine includes a gas generator and a fan arranged upstream from the gas generator and configured to generate a main gas flow, one portion of which flows in a flow path of the gas generator to form a primary flow, and another portion of which flows in a flow path around the gas generator to form a secondary flow. The gas generator has a low-pressure body with a rotor driving the fan and a low-pressure compressor situated upstream from an intermediate housing. The turbine engine also includes an electric machine, mounted coaxially downstream from the fan and upstream from the intermediate housing. An intermediate shaft is driven by the rotor of the low-pressure body and drives rotors of the electric machine and of the low-pressure compressor.

公开(公告)号：US20240239509A1

公开(公告)日：2024-07-18

申请号：US18559224

申请日：2022-04-25

申请人： SAFRAN HELICOPTER ENGINES

发明人： Benjamin Nicolas FULLERINGER ,  Antoine Pascal MOUTAUX ,  Romain Jean Gilbert THIRIET

IPC分类号： B64D35/022 ,  B64C27/12 ,  B64D35/08 ,  F01D15/10 ,  F02C7/32

CPC分类号： B64D35/022 ,  B64D35/08 ,  F01D15/10 ,  F02C7/32 ,  B64C27/12 ,  F05D2220/50 ,  F05D2220/76

摘要： A transmission device for a hybrid aircraft comprising a turboshaft engine including a gas generator, a free turbine, and a main rotor, the device comprising a first reversible electric machine 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 coupled to a shaft of the gas generator by way of a second deactivatable coupling means, and coupled to the main rotor by way of a third deactivatable coupling means, the second deactivatable coupling means being able to be activated when the second electric machine rotates in a first direction of rotation, and the third deactivatable coupling means being able to be activated when the second electric machine rotates in a second direction of rotation opposite to the first direction of rotation.