Architecture of a multi-engine helicopter propulsion system and corresponding helicopter
The invention relates to an architecture of a propulsion system of a multi-engine helicopter, comprising turboshaft engines ( 1, 2 ) that are connected to a power transmission gearbox ( 3 ), and comprising a low DC voltage onboard network ( 7 ) for supplying helicopter equipment during flight, characterized in that it comprises: a hybrid turboshaft engine ( 1 ) that is capable of operating in at least one standby mode during a stable flight of the helicopter; an electrotechnical pack ( 20 ) for quickly restarting said hybrid turboshaft engine in order to bring said engine out of said standby mode and to reach a mode in which it provides mechanical power, said restart pack ( 20 ) being connected to said onboard network ( 7 ); and at least two sources ( 4, 16, 18 ) of electrical power for said onboard network ( 7 ).
1. An architecture of a propulsion system of a multi-engine helicopter, comprising turboshaft engines that are connected to a power transmission gearbox, and comprising a low DC voltage onboard network for supplying power to helicopter equipment during flight,
wherein it comprises:
one turboshaft engine among said turboshaft engines, referred to as a hybrid turboshaft engine, which is capable of operating in at least one standby mode during a stable flight of the helicopter, the other turboshaft engines operating alone during this stable flight,
an electrotechnical pack for quickly restarting said hybrid turboshaft engine in order bring said engine out of said standby mode and to reach a mode referred to as the nominal mode, in which it provides mechanical power to said power transmission gearbox, said restart pack being connected to said onboard network,
at least two sources of electrical power for said onboard network.
2. The architecture according to claim 1 , wherein said electrotechnical pack for quick restart is a high-voltage pack, and in that a low voltage-high voltage converter is arranged between said onboard network and said rapid restart pack.
3. The architecture according to claim 1 , wherein said sources of electrical power for said onboard network are selected from the group comprising:
at least one current generator that is arranged between said power transmission gearbox and said onboard network and is associated with an AC-DC converter,
an auxiliary power unit that is connected to said onboard network and associated with an AC-DC converter,
a starter-generator that is arranged between a non-hybrid turboshaft engine and said onboard network.
4. The architecture according to claim 3 , wherein each current generator and said auxiliary power unit are capable of providing an AC voltage of 115 volts, and in that said associated converter is capable of converting said 115-volt AC voltage into a DC voltage of 28 volts.
5. The architecture according to claim 1 , wherein said electrotechnical pack comprises an electrical energy storage device which is capable of accumulating electrical energy from said onboard network during said nominal mode of said hybrid turboshaft engine, and which, following a command to leave standby, is capable of providing the hybrid turboshaft engine with the accumulated electrical energy that is necessary to ensure restart thereof.
6. The architecture according to claim 1 , wherein said restart pack is capable of providing, when said hybrid turboshaft engine is in standby mode, electrical energy for keeping said hybrid turboshaft engine in a predetermined standby mode.
7. The architecture according to claim 1 , wherein said quick restart pack comprises an electrical machine that is capable of restarting said turboshaft engine when leaving standby in normal conditions, and a device for leaving standby in an emergency that is capable of restarting said turboshaft engine when leaving standby in emergency conditions.
8. The architecture according to claim 7 , wherein said device for leaving standby in an emergency is selected from the group comprising an electrotechnical device, a pyrotechnic device, a pneumatic device and a hydraulic device.
9. The helicopter comprising a propulsion system, wherein said propulsion system has an architecture according to claim 1 .