Hybrid propulsion system for an aircraft
A hybrid propulsion system including a turbine engine including a high-pressure spool and a low-pressure spool, the low-pressure spool including reduction gear, the reduction gear forming part of a transmission gearbox which is positioned axially at a front end of the propulsion system; —first and second electric machines mechanically and respectively connected to the high-pressure and low-pressure spools, the electric machines being configured to operate in modes referred to as motor and generator, the first and second electric machines being fixed to the transmission gearbox; —a control system which is configured to allow the transfer of power between the high-pressure and low-pressure spools via the first and second electric machines.
1 . An aircraft comprising:
a hybrid propulsion system comprsing:
a turboshaft engine comprising a high-pressure spool and a low-pressure spool movable in rotation, the high-pressure spool comprising a compressor and an expansion turbine mechanically connected to each other by a high-pressure shaft, the low-pressure spool comprising a power turbine which drives a power take-off in rotation via a reduction gear, the reduction gear forming part of a first transmission gearbox which is arranged axially at a front end of the propulsion system;
first and second electric machines mechanically connected to the high-pressure and low-pressure spools respectively, the electric machines being configured to operate in so-called motor and generator modes, the first and second electric machines being attached to the first transmission gearbox;
a control system which is configured to allow power to be transferred between the high-pressure and low-pressure spools via the first and second electric machines;
a main transmission gearbox which is driven by the power take-off of the turboshaft engine.
2 . The aircraft according to claim 1 , wherein the first and second electric machines are attached to a front face of the first transmission gearbox.
3 . The aircraft according to claim 1 , wherein the first electric machine is connected to the high-pressure spool via a first transmission mechanism arranged in the first transmission gearbox, the first transmission mechanism preferably being a gear mechanism.
4 . The aircraft according to claim 1 , wherein the second electric machine is connected to the low-pressure spool via a second transmission mechanism arranged in the first transmission gearbox, the second transmission mechanism preferably being a gear mechanism.
5 . The aircraft according to claim 1 , wherein the power turbine and the reduction gear are mechanically connected to each other by a low-pressure shaft, the low-pressure and high-pressure shafts being coaxial, the low-pressure shaft passing internally through the high-pressure shaft.
6 . The aircraft according to claim 1 , wherein the main transmission gearbox is mechanically connected to the power take-off of the turboshaft engine by means of an upper transmission shaft.
7 . The aircraft according to claim 1 , wherein the first and second electric machines are high-voltage electric machines which are connected to a high-voltage electrical network of the control system.
8 . The aircraft according to claim 1 , wherein the first electric machine is configured to start the turboshaft engine.
9 . The aircraft according to claim 1 , wherein the propulsion system is configured to operate according to one of the following operating modes:
a first hybrid operating mode wherein the first electric machine operates in generator mode and the second electric machine operates in motor mode, the electrical energy produced by the first electric machine being used to supply electrical energy to the second electric machine, so as to transfer power from the high-pressure spool towards the low-pressure spool;
a second hybrid operating mode wherein the first electric machine operates in motor mode and the second electric machine operates in generator mode, the electrical energy produced by the second electric machine being used to supply electrical energy to the first electric machine, so as to transfer power from the low-pressure spool towards the high-pressure spool.
10 . The aircraft according to claim 1 , wherein the aircraft comprises a rear transmission gearbox which is mechanically connected to the main transmission gearbox by means of a lower transmission shaft, the lower transmission shaft being located below an upper transmission shaft.
11 . The aircraft according to claim 1 , wherein the first and second electric machines are attached to a front face of the first transmission gearbox, the first and second electric machines being located directly next to each other.
12 . The aircraft according to claim 1 , wherein the first and second electric machines are attached to a front face of the first transmission gearbox, the first and second electric machines being located above the power take-off.
13 . The aircraft according to claim 1 , wherein the first and second electric machines are attached to a front face of the first transmission gearbox, the first and second electric machines being located above the power take-off, the first electric machine being located above the second electric machine.
14 . The aircraft according to claim 1 , wherein the first and second electric machines are attached to a front face of the first transmission gearbox, the propulsion system comprising accessories that are transversely opposed to the first and second electric machines.
15 . The aircraft according to claim 1 , wherein the control system comprises a turboshaft engine computer, a low-voltage electrical network and a high-voltage electrical network.
16 . The aircraft according to claim 1 , wherein the control system comprises at least one electrical energy storage device which is configured to store the electrical energy produced by the first electric machine and the second electric machine.
17 . The aircraft according to claim 1 , wherein the control system comprises at least one power converter configured to convert alternating current to direct current or vice versa.
18 . The aircraft according to claim 1 , wherein the propulsion system comprises a cooling and lubrication circuit configured to cool and lubricate the first transmission gearbox, the first and second electric machines being cooled and lubricated via the cooling and lubrication circuit.
19 . A helicopter comprising:
a hybrid propulsion system comprising:
a turboshaft engine comprising a high-pressure spool and a low-pressure spool movable in rotation, the high-pressure spool comprising a compressor and an expansion turbine mechanically connected to each other by a high-pressure shaft, the low-pressure spool comprising a power turbine which drives a power take-off in rotation via a reduction gear, the reduction gear forming part of a first transmission gearbox which is arranged axially at a front end of the propulsion system;
first and second electric machines mechanically connected to the high-pressure and low-pressure spools respectively, the electric machines being configured to operate in so-called motor and generator modes, the first and second electric machines being attached to the first transmission gearbox;
a control system which is configured to allow power to be transferred between the high-pressure and low-pressure spools via the first and second electric machines;
a main transmission gearbox which is mechanically connected to the power take-off of the turboshaft engine by means of an upper transmission shaft;
a rear transmission gearbox which is mechanically connected to the main transmission gearbox by means of a lower transmission shaft, the lower transmission shaft being located below the upper transmission shaft.