A turning device (30) includes an electric motor (41), a moving gear (53) configured to move between a first position (P1) at which rotation of an output shaft (43) of the electric motor (41) is able to be transmitted to a rotor (11) and a second position (P2) at which rotation of the output shaft (43) is unable to be transmitted to the rotor (11), a movement mechanism (60) configured to move the moving gear (53) between the first position (P1) and the second position (P2), a torque detection unit (44) configured to detect a torque of the output shaft (43) of the electric motor (41), and a control device (61) configured to control the movement mechanism (60) to move the moving gear (53) from the first position (P1) to the second position (P2) based on the torque detected by the torque detection unit (44).

A turning apparatus (30) includes an electric motor (41), a moving gear (53) that is movable between a first position at which rotation of an output shaft (43) of the electric motor (41) is able to be transmitted to a rotor (11), and a second position and a third position, which are different from each other and at which rotation of the output shaft (43) is unable to be transmitted to the rotor (11), a movement mechanism (60) configured to move the moving gear (53) between the first position, the second position and the third position, and a control device (61) configured to control the movement mechanism (60) based on a. retreat signal such that the moving gear (53) is moved from the first position to the second position and control the movement mechanism (60) based on an adhesion prevention signal such that the moving gear (53) reciprocates between the second position and the third position.

A turning apparatus (30) includes an electric motor (41), a moving gear (53) that is movable between a first position at which rotation of an output shaft (43) of the electric motor (41) is able to be transmitted to a rotor (11), and a second position and a third position, which are different from each other and at which rotation of the output shaft (43) is unable to be transmitted to the rotor (11), a movement mechanism (60) configured to move the moving gear (53) between the first position, the second position and the third position, and a control device (61) configured to control the movement mechanism (60) based on a. retreat signal such that the moving gear (53) is moved from the first position to the second position and control the movement mechanism (60) based on an adhesion prevention signal such that the moving gear (53) reciprocates between the second position and the third position.

An apparatus for driving a load is provided. The apparatus comprises a multiple-shaft gas turbine comprising a high pressure compressor and a high pressure turbine drivingly connected to one another by a first gas turbine shaft and a low pressure compressor and a power turbine drivingly connected to one another by a second gas turbine shaft extending coaxial with the first gas turbine shaft, the high pressure compressor and the high pressure turbine. The apparatus also comprises a load coupling drivingly connecting the power turbine to the load and a dual-speed turning gear with an output shaft drivingly engageable to and disengageable from the load, the dual-speed turning gear comprising a low speed turning motor and a high speed turning motor, wherein the low speed turning motor and the high speed turning motor are configured to selectively drive the load.

An apparatus for driving a load is provided. The apparatus comprises a multiple-shaft gas turbine comprising a high pressure compressor and a high pressure turbine drivingly connected to one another by a first gas turbine shaft and a low pressure compressor and a power turbine drivingly connected to one another by a second gas turbine shaft extending coaxial with the first gas turbine shaft, the high pressure compressor and the high pressure turbine. The apparatus also comprises a load coupling drivingly connecting the power turbine to the load and a dual-speed turning gear with an output shaft drivingly engageable to and disengageable from the load, the dual-speed turning gear comprising a low speed turning motor and a high speed turning motor, wherein the low speed turning motor and the high speed turning motor are configured to selectively drive the load.

The barring gear assembly is designed to drive in rotation a shaft of a turbo-alternator group having an axis of rotation A. The barring gear assembly includes a main wheel fixed on said shaft and defining lateral sides located on either side of the axis of rotation A, a barring gear module having a support piece on which is mounted a clutch system for coupling and uncoupling a secondary shaft to and from the main wheel, the secondary shaft being driven by an auxiliary motor, and the barring gear module being positioned on one of said lateral sides (C1) of the axis of rotation A.

The barring gear assembly is designed to drive in rotation a shaft of a turbo-alternator group having an axis of rotation A. The barring gear assembly includes a main wheel fixed on said shaft and defining lateral sides located on either side of the axis of rotation A, a barring gear module having a support piece on which is mounted a clutch system for coupling and uncoupling a secondary shaft to and from the main wheel, the secondary shaft being driven by an auxiliary motor, and the barring gear module being positioned on one of said lateral sides (C1) of the axis of rotation A.

An engine system for an aircraft includes a first gas turbine engine, a first core turning system, a second gas turbine engine, and a second core turning system. The engine system also includes a controller operable to shutdown the first gas turbine engine responsive to determining that the aircraft has landed and operate in the second gas turbine engine in a taxi mode while using the first core turning system to cool the first gas turbine engine. The controller is further operable to shutdown the second gas turbine engine and disable the first core turning system based on a power-down condition, restart the first gas turbine engine and use the second core turning system to cool the second gas turbine engine based on a restart condition, and complete cooling of the second gas turbine prior to restarting the second gas turbine engine.

An engine system for an aircraft includes a first gas turbine engine, a first core turning system, a second gas turbine engine, and a second core turning system. The engine system also includes a controller operable to shutdown the first gas turbine engine responsive to determining that the aircraft has landed and operate in the second gas turbine engine in a taxi mode while using the first core turning system to cool the first gas turbine engine. The controller is further operable to shutdown the second gas turbine engine and disable the first core turning system based on a power-down condition, restart the first gas turbine engine and use the second core turning system to cool the second gas turbine engine based on a restart condition, and complete cooling of the second gas turbine prior to restarting the second gas turbine engine.

A turbofan engine includes a first spool including a first turbine, and a first tower shaft engaged to the first spool. A second spool includes a second turbine, and a second tower shaft is engaged to the second spool. A superposition gearbox includes a sun gear, a plurality of intermediate gears engaged to the sun gear, and is supported in a carrier and a ring gear circumscribing the intermediate gears. The first tower shaft or the second tower shaft drives one of the intermediate gears. A drive motor is engaged to drive the sun gear, an inner electric motor, a stator disposed radially outside of the inner electric motor, and an outer electric motor disposed radially outside the stator. A first load on the first spool and a second load on the second spool is adjusted by operation of at least one of the inner electric motor and the outer electric motor.