FR3086690A1 - AIRCRAFT CONFIGURED AS A CURRENT GENERATOR, EQUIPMENT AND KIT FOR SUCH AN AIRCRAFT AND METHOD FOR EQUIPMENT OF AN AIRCRAFT - Google Patents

Abstract

The invention relates to an aircraft (1) comprising at least one turbomachine (10, 20) which is free of the receiver vane, and a current generator (30) having at least one axis (31) mechanically coupled with a drive shaft. rotor (110) of the turbomachine (10). The current generator (30) being configured to generate current from a rotational movement of its axis (31). The invention further relates to equipment (5) for an aircraft (1), an equipment kit and methods of equipping and restoring the aircraft (1).

Description

AIRCRAFT CONFIGURED AS A CURRENT GENERATOR, EQUIPMENT AND KIT FOR A

SUCH AIRCRAFT AND METHOD FOR EQUIPMENT OF AN AIRCRAFT

DESCRIPTION

TECHNICAL AREA

The invention relates to the field of aeronautics and more specifically aircraft.

The invention therefore more particularly relates to an aircraft, aircraft equipment, an aircraft equipment kit, an aircraft transformation method, an aircraft refitting method and a method for starting an aircraft turbomachine.

PRIOR STATE OF THE ART

During natural disasters, such as cyclones and earthquakes, the production and transmission of electricity are generally disrupted. However, in such a situation, the need for electricity, in particular to enable first aid to be provided, to organize aid and to supply the primary needs of the survivors, such as drinking water, are significant.

Thus, to overcome production shortcomings and / or the impossibility of supplying electricity, it is known to bring in electric current generators. However, such generators, in order to provide sufficient production, are heavy and are therefore relatively difficult to bring to regions which are generally, due to the consequences of the disaster, made difficult to access.

In order to solve such a problem, there would be interest in a solution making it possible to generate electricity with means already at least partly available on the spot and which thus limits the logistic needs for such production.

STATEMENT OF THE INVENTION

The invention aims to remedy these drawbacks and thus aims to provide electricity production directly on the scene of a natural disaster by limiting the means to be brought on site.

To this end, the invention relates to an aircraft comprising at least one turbomachine:

the turbomachine is free of the receiver vane, and the aircraft further comprises a current generator having at least one axis mechanically coupled with a rotor shaft of the turbomachine, the current generator being configured to generate current from 'a rotational movement of its axis.

Such an aircraft transformed into a current generator by coupling its turbomachine with the current generator is a high capacity current generator. Indeed, if a conventional generator set hardly exceeds 1500 kW, a single turbomachine can provide a power peak of typically 25,000 kW, in a take-off configuration, and a power of nearly 10,000 kW continuously. Thus, such an aircraft parked in an airport during the disaster can, by the simple modification according to the invention, replace more than six generators this by having to bring on site only the current generator. This capacity can, of course, be doubled in the case where at least two of the aircraft's turbomachines are equipped with a current generator according to the principle of the invention.

It will be noted that it is moreover possible, within the framework of the invention, for such a generator to be stored in the airport in anticipation of such a natural disaster, thereby eliminating the need to bring it to the market. place of disaster.

An aircraft according to the invention also makes it possible to benefit from the fuel stocks of the aircraft, generally around 2 tonnes, and of the airport. This also eliminates the need to transport fuel to the disaster site for power generation.

Of course, according to an advantage of the invention, the aircraft can, after the production and transport of electricity have been normalized, by a simple decoupling of the turbomachine from the current generator and by a simple installation of the receiver blades, regain its ability to fly.

Finally, the invention also authorizes the possibility of providing an aircraft

The turbomachine can be a turbojet engine which is free of fan blades.

Such a turbojet engine makes it possible to provide a particularly large generation of electricity and therefore, therefore, particularly benefits from the possibilities offered by the invention.

The invention further relates to equipment for an aircraft comprising at least one turbomachine, the equipment comprising:

a current generator having at least one axis configured to be mechanically coupled with a fan disc of the turbomachine, the receiver vanes of said turbomachine having been previously removed, said current generator being configured to generate current from a movement of rotation of its axis.

Such equipment makes it possible to equip a turbomachine with an aircraft in order to obtain an aircraft according to the invention and benefit from the advantages which are linked to it.

The equipment may further comprise a cooling system capable of generating an air flow at the level of at least one heat exchanger of a lubrication circuit of the bearing of the turbomachine, the cooling system preferably comprising at least the one of:

a fan configured to be mounted on a brick exchanger, a fan configured to equip at least part of a surface air / oil heat exchanger, an assembly comprising at least one fan associated with an air distributor intended to equip at least part of an air / oil surface heat exchanger, the air distributor being configured to distribute the air flow generated by the fan in the direction of the air / oil surface heat exchanger, a flow generation system d air in a secondary flow stream of the turbomachine in the direction of a sampling scoop arranged in said secondary flow stream of the turbomachine, said sampling scoop serving in particular at least one heat exchanger.

Such a cooling system makes it possible to compensate for the absence of secondary flow generated, in normal operation of the turbomachine, by the fan rotor, and therefore to avoid the risks of overheating that such an absence could cause. It is thus possible to operate the turbomachine at full speed for relatively long periods, that is to say greater than 30 minutes, without damaging the latter.

The equipment may further comprise a control unit adapted to connect to on-board electronics of the turbomachine, the control unit being adapted to provide instructions for controlling the turbomachine to the on-board electronics when the aircraft is equipped with the equipment, the control unit preferably being further adapted to allow a power measurement supplied by the rotor shaft of the turbomachine and to control the operating point of the turbomachine based on the result of the power measurement.

Such a control unit makes it possible to provide an optimized operation of the turbomachine when the latter and the aircraft which comprises it are equipped with equipment according to the invention.

The equipment may further comprise a filter system intended to equip the air inlet of the turbomachine and configured to prevent ingestion of foreign bodies in the turbomachine.

In this way, it is possible to reduce the risk of ingestion of foreign bodies which could be detrimental to the proper functioning of the turbomachine.

The invention also relates to an aircraft equipment kit (comprising: equipment according to the invention, at least one tool for dismantling the blades of a turbomachine receiver.

Such a kit and particularly advantageous for the implementation of equipment according to the invention. It is thus possible to store such a kit at an airport. In this way, in the event of a natural disaster, the airport technicians have access to all the elements necessary to implement the invention on one or more aircraft parked at the airport.

The invention further relates to a method of transforming an aircraft into an electric generator, the aircraft comprising at least one turbomachine, the method comprising the following steps:

supply of a current generator having at least one axis configured to be coupled with a rotor shaft of the turbomachine, the current generator being configured to generate current from a rotational movement of its axis, removal of the vanes from turbomachine receiver, coupling the axis of the current generator with the turbomachine receiver disc so as to mechanically couple the axis with a rotor shaft of said turbomachine.

Such a method allows the supply of an aircraft according to the invention and to benefit from the advantages which are linked to it.

The process comprising the following steps:

decoupling of the axis of the current generator with the rotor shaft of the turbomachine, installation of the turbine engine receiver vanes around the receiver disc.

In this way, from such a method it is possible to return an aircraft according to the invention in a flight state.

Method for starting a turbomachine of an aircraft according to the invention, the method comprising the following steps:

- aircraft ignition,

- ignition of an auxiliary generator on board the aircraft,

- ignition of the turbomachine,

- fuel supply to the turbomachine,

- start-up control of the turbomachine in order to start the generation of current by the current generator whose axis is driven by the rotor shaft of the turbomachine,

- switch-off of the on-board auxiliary generator.

Such a method makes it possible to obtain a generation of current with an aircraft according to the invention.

BRIEF DESCRIPTION OF THE DRAWINGS

The invention will be better understood with the aid of the description which follows, given solely by way of nonlimiting example and made with reference to the appended drawings in which:

FIG. 1 illustrates a schematic view of an aircraft according to the invention supplying an electrical network, a turbomachine equipped according to the invention being illustrated in inset,

FIG. 2 schematically illustrates in section an example of a turbomachine capable of equipping an aircraft according to the invention,

FIG. 3 schematically illustrates in section a turbomachine of the aircraft after removal of its fan disc and before its coupling to the current generator,

FIG. 4 schematically illustrates in section of the turbomachine of the aircraft after coupling to the current generator,

FIGS. 5A and 5B illustrate a cooling system according to a first and a second possibility of the invention,

- Figure 6 illustrates an equipment kit according to the invention.

The different parts shown in the figures are not shown on a uniform scale, to make the figures more readable.

The different possibilities (variants and embodiments) must be understood as not being mutually exclusive and can be combined with one another.

DETAILED PRESENTATION OF PARTICULAR EMBODIMENTS

FIG. 1 illustrates an aircraft 1 according to the invention supplying an electrical network 2 with electricity, this in order to provide, for example, a makeshift hospital or even a refugee camp.

According to the principle of the invention, the aircraft 1 comprises:

a first and a second turbomachine 10, 20 of which the first turbomachine 10 is made free of the receiver vane, an on-board computer 21, the on-board computer 21 being configured to control the elements of the aircraft, such as a on-board auxiliary generator 25 of the aircraft and the first and second turbomachines 10, 20 through a respective control unit 150 of the latter, a current generator 30 having an axis 31 mechanically coupled with a rotor shaft 110 of the first turbomachine 10, the current generator 30 being configured to generate current from a rotational movement of its axis 31, a cooling system 50 arranged in the first turbomachine 10 configured to supply an air flow in a secondary flow stream a control unit 40 connected to the current generator 30 and configured to supply a required voltage, for example an AC voltage of 220V, for example drawing of the current generated by the current generator 30 to supply the electrical network 2, the control unit also being configured to connect to a control unit 150 of the turbomachine 10.

Of course, if in this exemplary embodiment, only the first turbomachine 10 is equipped with the current generator 30 according to the principle of the invention, it is also conceivable, without departing from the scope of the invention, that all of the turbomachines 10, 20 of the aircraft 1 are equipped with a respective current generator 30.

FIG. 2 is a sectional view illustrating a type of turbomachine such as equipping an aircraft according to the invention, FIG. 2 referring to the first turbomachine 10. According to this example, the first turbomachine 10 is a turbofan engine for aircraft, generally comprising a fan disc 112, equipped with fan blades 113 forming an assembly of the fan rotor, intended for the suction of an air flow F1 dividing downstream of the fan into a flow primary F2 supplying a core of the turbojet engine and a secondary flow F3 bypassing this core and intended in principle to provide most of the thrust.

The heart of the turbojet engine comprises, in a well known manner, a low pressure compressor 114, a high pressure compressor 116, a combustion chamber 118 for example of the annular type, a high pressure turbine 120 and a low pressure turbine 122. The turbojet engine is faired by a nacelle 124 surrounding the flow space 126 of the secondary flow. The rotor shafts of the turbojet engine, including the low pressure rotor shaft 110 on which the fan disc is mounted, are rotatably mounted around a longitudinal axis 128 of the turbojet engine. Of course, the invention is not limited to this single type of turbomachine and is therefore applicable to any type of turbomachine.

According to the principle of the invention, as illustrated in FIG. 3, the first turbomachine 10 is free of receiver vanes which are, for a turbojet engine, the fan blades 113. More specifically, the first turbomachine 10 is free of fan blade, these having been previously dismantled. In this way, the removal of the fan blades makes it possible to free access to the fan disk for coupling to the current generator 30.

This coupling is illustrated in FIG. 4. As shown in this figure, the current generator 30 is preferably an alternator. Alternatively, in the case where a DC voltage is required, the current generator 30 can also be a dynamo. The current generator 30 has its axis 31 coupled to the rotor shaft 110 of the first turbomachine 10, this through the fan disc. The axis 31 of the current generator 30 is adapted to allow such coupling. Thus the axis 31 has an interface complementary to the fan disc of the first turbomachine 10 released from the fan blades 113, such as for example a bulb crown reproducing the geometry of the feet of fan blades 113.

According to one possibility of the invention, not illustrated, the axis 31 can have the interface in the form of a removable tip, the current generator 30 being able to be supplied with a plurality of tips each suitable for a type of turbomachine. . In this way, the current generator 30 does not have to be dedicated to a type of turbomachine and can be installed on any aircraft present at the airport when the natural disaster takes place.

In order to keep the current generator 30 centered with respect to the rotor shaft 110 of the first turbomachine 10, the aircraft 1 comprises, as shown in FIG. 4, a system for fixing 35 to the stator adapted to fix the current generator 30 to a stator element of the first turbomachine 10. Thus, the fixing system can be a connection based on a fixing using bolts to the stator element of the fan such as the fan casing. Such a connection is particularly suitable since the fan stator is capable, by the design of the turbomachine 10, of supporting the torque to which the current generator 30 is subjected in operation of the first turbomachine 10.

It will be noted that, depending on the possibility or the interface takes the form of a removable tip and that the generator is supplied with a plurality of tips each adapted to a type of turbomachine, it is also possible, this to facilitate adaptability of the current generator, whether this is supplied with a plurality of fixing systems 35 or of an adjustable fixing system. In this way, it is possible to adapt the fixing system to the configuration of the stator of the turbomachine 10.

The fastening system 35 preferably comprises a centering support, not illustrated, to facilitate the centering of the generator 30 with respect to the rotor shaft 110 and flexible junctions 36 connecting the stator of the first turbomachine 10 to the generator of current 30.

The aircraft 1 also comprises a filter system 32, such as a grid or another filter element, arranged at the level of the air inlet of the first turbomachine 10. With such a filter system, the limits are: or even eliminates, the risks of ingestion of foreign bodies in the first turbomachine 10. Such equipment is all the more advantageous if we consider that, in the configuration of the invention, the aircraft 1 is intended to operate at soil which drastically increases the risk of such ingestion.

As illustrated in FIG. 1, the control unit 40 includes a transformer unit 41 configured to provide an adaptation of the current generated by the current generator 30 in order to supply a voltage compatible with the electrical network 2, for example an alternating voltage of 220V. According to one possibility of the invention, the transformation unit is also able to determine, for example from a measurement of at least one parameter of the current generator 30, the value of the power supplied by the shaft from rotor 110 to current generator 30.

The control unit 40 also comprises a control unit 45 configured to determine an operating point of the turbomachine from parameters of the electrical network 2 and parameters of the first turbomachine 10 and to control the first turbomachine to configure it in accordance with said point Operating.

To do this, the control unit 45 is adapted to be connected to the on-board computer 21 of the aircraft and thus, through the on-board computer 21, of the on-board electronics 150 of the first turbomachine 10. In this way, the control unit 45 can provide the instructions to the on-board electronics of the first turbomachine 10 in order to operate it in a configuration making it possible to optimize the yields of the generation of electricity and to correspond to the needs. in electricity. It will be noted that among the parameters of the first turbomachine 10, the control unit 45 can in particular be adapted to recover, from the transformation unit 41, the value of the power supplied by the rotor shaft 110 to the current generator 30.

It will be noted that it is conceivable, according to the invention, that the control unit is suitable for, from the electric power to be supplied by the generator 30, calculating an engine speed this in order to maintain the turbomachine in a zone of optimized performance.

According to an advantageous possibility of the invention, the control unit 45 can be adapted to implement a method for starting the generator formed by the aircraft 1, said method comprising the following steps:

ignition of the aircraft 1, this first step generally being implemented directly by the technician in charge of connecting the control unit 45 to the on-board computer 25 of the aircraft 1,

- ignition of an on-board auxiliary generator 25 of the aircraft 1,

- ignition of the first turbomachine 10,

- fuel supply to the first turbomachine 10,

command to start the turbomachine 10 in order to start the generation of current by the current generator 30 therefore the axis 31 is driven by the rotor shaft 110 of the turbomachine 10,

- switch-off of the on-board auxiliary generator 25.

It will be noted that, according to a usual starting sequence of a turbomachine, the starting command comprises the following sub-steps:

opening of a compressed air valve of an air starter of the first turbomachine, ignition of the spark plugs and fuel injection, control of the first turbomachine 10 thus started according to a suitable operating point.

In the configuration of the aircraft 1 according to the invention, the first turbomachine 10 is put into operation while it is free from a receiver vane, or other aerodynamic receiver, to generate a secondary air flow F3. However, for certain type of turbomachine, such as that of the turbofan engines, part of the secondary flow F3 generated by the fan rotor is used to cool certain part of the turbomachine. Thus, if we take the case of a turbofan engine, a part of the secondary stream F3 makes it possible in particular to cool the oil of the compressors 114, 115 and the turbines 120, 122 and the low pressure turbine 122 and makes it possible to ventilate the core compartment of the turbomachine. Thus, the secondary air flow F3 is generally necessary so that the first turbomachine 10 can reach its full power and / or maintain its full power over an extended period (that is to say a duration greater than 30 minutes).

In order to compensate for the absence of secondary flow F3, it is possible within the framework of the invention to provide a cooling system 50 capable of generating an air flow at the level of at least one heat exchanger of a compressor assembly , combustion chamber and turbine of the turbomachine 10. In this way, by generating, from such a cooling system 50, an air flow at at least one heat exchanger, such as a heat exchanger air-oil, it is possible to provide cooling similar to that provided by the secondary flow F3 in a propulsion configuration of the first turbomachine 10. Thus equipped, the turbomachine is able to reach its full power without risk of damage and / or maintain its full power for an extended period (that is to say a period greater than 30 minutes).

As illustrated in FIGS. 5A and 5B, the cooling system 50 can comprise at least one of:

an axial fan 41 configured to be mounted on a brick exchanger 123, as shown in FIG. 5A, a fan 42A, 42B, 42C, 42D configured to equip at least part of a surface heat exchanger 124 air / oil, only part of the fins of the surface heat exchanger 124 being shown in FIG. 5B, according to a possibility not illustrated, an assembly comprising at least one fan, associated with an air distributor intended to equip at least part of a air / surface oil heat exchanger, the air distributor being configured to distribute the air flow generated by the fan towards the heat exchanger according to a possibility not illustrated, a system for generating air flow in a secondary flow stream of the turbomachine in the direction of a sampling scoop arranged in said turbomachine secondary flow stream, said sampling scoop serving n in particular at least one heat exchanger.

It will be noted that in accordance with the general knowledge of a person skilled in the art, brick exchangers are air / oil exchangers having a parallelepiped shape, from which they derive their name of brick exchanger, which are supplied with fresh air by specific scoops. The surface exchangers are however installed on a casing surface and intercept the secondary air flow F3 from the turbomachine 10.

In a conventional configuration of the invention, the cooling system 50 can comprise several of the elements from the list above, the system thus being able to comprise an axial fan 41 for each of the scoops and a plurality of fans 42A, 42B, 42C, 42D equipping the surface heat exchangers 124 of the first turbomachine 10.

It will be noted that the brick exchangers 123 and the surface air-oil heat exchangers 124 are exchangers conventionally used in a turbofan engine and that they are generally arranged to receive part of the secondary flow taken in particular from scoops for supply the core of the turbojet engine. Thus, the brick exchangers are in particular arranged at the level of such scoops.

According to an advantageous possibility of the invention, the cooling system 50 can be controlled by the control unit 40, this in particular by the control unit 45, in order to best adapt the cooling capacity to the cooling needs of the first turbomachine 10.

The current generator 30, the fixing system, the filtering system, the cooling system 50 and the control box 40 together form an equipment item 5 for aircraft. Such equipment can for example be stored in an airport present in a region liable to be subjected to a natural disaster. In this way, in the event of a natural disaster, a technician can use said equipment to modify an aircraft into an aircraft 1 according to the invention which is capable of generating electricity.

According to another possibility of the invention illustrated in FIG. 6, this equipment 5 can also be associated with at least one tool 6 for dismantling the turbomachine receiver vanes 10, this in order to form an equipment kit 4 for an aircraft 1. In this way, the technician having to carry out the equipment of the aircraft 1 in order to obtain an aircraft according to the invention, is in the presence of all the required elements.

To make such an assembly, the technician can implement an aircraft equipment method comprising the following steps:

supply of the current generator 30 having at least one axis 31 configured to be coupled with a rotor shaft 110 of the turbomachine (10), the current generator 30 being configured to generate current from a rotational movement of its axis 31, removal of the receiver vanes from the turbomachine 10, coupling of the axis 31 of the current generator 30 with the blower disc free of the receiver vanes, here fan blade of the turbomachine 10, installation of the other elements of the equipment 5, with the fixing system for fixing the current generator 30, the filter system arranged at the air inlet of the first turbomachine, the cooling system 50 mounted inside the turbomachine 10 and the control unit 40 connected to the current generator 30 and to the on-board computer 21 of the aircraft.

Of course, once the production and transport capacities of electricity have been restored in the region that presented the natural disaster, the generation of electricity offered by the aircraft is no longer necessary, the technician is able to carry out a reconditioning of an aircraft 1 by means of the adapted method comprising the following steps:

decoupling of the axis 31 of the current generator 30 with the rotor shaft 110 of the turbomachine 10, disassembly and removal of the elements 30, 32, 35, 40, 50, from the equipment for decluttering the aircraft 1 and the first turbomachine 10, reinstallation of the turbine engine receiver vanes 10 around the rotor shaft 110.

In this way, the aircraft 1 is able to resume its passenger and / or freight transport functions.

Of course, if the invention relates more particularly to commercial aircraft fitted with turbojets, the invention is not limited to this single type of aircraft and covers all types of aircraft, whether these are commercial, tourist or even aircraft. regardless of the type and number of turbomachines fitted to them.

S64971 ET-P

Claims (10)

1. Aircraft (1) comprising at least one turbomachine (10, 20), the aircraft (1) being characterized in that: the turbomachine (10) is free of the receiver vane, and the aircraft (1) further comprises a current generator (30) having at least one axis (31) mechanically coupled with a rotor shaft (110) of the turbomachine (10), the current generator (30) being configured to generate current from a rotational movement of its axis (31). 2. Aircraft (1) according to claim 1, in which the turbomachine (10, 20) is a turbojet engine which is free of fan blades. 3. Equipment (2) for an aircraft (1) comprising at least one turbomachine (10, 20), the equipment (2) comprising: a current generator (30) having at least one axis (31) configured to be mechanically coupled with a fan disc (110) of the turbomachine (10), the receiver vanes of said turbomachine (10) having been previously removed, said current generator (30) being configured to generate current from a rotational movement of its axis (31). 4. Equipment (2) according to claim 3, wherein the equipment further comprises a cooling system (50) capable of generating an air flow at at least one heat exchanger (123,124) of a circuit for lubricating the bearing of the turbomachine (10), the cooling system (50) preferably comprising at least one of: a fan (51) configured to be mounted on a brick exchanger (123), a fan (52A, 52B, 52C, 52D) configured to equip at least part of an air / oil surface heat exchanger (124), a assembly comprising at least one fan associated with an air distributor intended to equip at least part of an air / oil surface heat exchanger (124), the air distributor being configured to distribute the air flow generated by the fan in the direction of the air / oil surface heat exchanger (124), a system for generating air flow in a secondary flow stream of the turbomachine in the direction of a sampling scoop arranged in said secondary flow stream turbomachine, said sample scoop serving in particular at least one heat exchanger. 5. Equipment (5) according to claim 3 or 4 further comprising a control unit (45) adapted to connect to on-board electronics (150) of the turbomachine (10), the control unit (45) being suitable for providing instructions for controlling the turbomachine to the on-board electronics (150) when the aircraft (1) is equipped with the equipment (5)., the control unit (45) being preferably also adapted to allow measurement power supplied by the rotor shaft of the turbomachine (10) and for controlling the operating point of the turbomachine (10) based on the result of the power measurement. 6. Equipment (5) according to any one of claims 3 to 5 further comprising a filter system (32) intended to equip the air intake of the turbomachine (10) and configured to prevent ingestion of foreign bodies in the turbomachine. 7. Aircraft equipment kit (4) (1) comprising: equipment (5) according to any one of claims 3 to 7, at least one tool (6) for removing the turbomachine receiver vanes (10). 8. Method for transforming an aircraft (1) into an electric generator, the aircraft (1) comprising at least one turbomachine (10, 20), the method comprising the following steps: supply of a current generator (30) having at least one axis (31) configured to be coupled with a rotor shaft (110) of the turbomachine (10), the current generator (30) being configured to generate current to from a rotational movement of its axis (31), withdrawal of the receiver blades from the turbomachine (10), coupling of the axis (31) of the current generator (30) with the receiver disc (110) of the turbomachine (10) so as to mechanically couple the axis (31) with a rotor shaft (110) of said turbomachine (10). 9. Method for rehabilitating an aircraft (1) according to claim 1, the method comprising the following steps: decoupling of the axis (31) of the current generator (30) with the rotor shaft (110) of the turbomachine (10), installation of the turbine engine receiver vanes (10) around the receiver disc (110 ). 10. Method for starting a turbomachine (10) of an aircraft (1) according to claim 1, the method comprising the following steps: - aircraft ignition (1), - ignition of an on-board auxiliary generator (25) of the aircraft (1), - ignition of the turbomachine (10), - fuel supply to the turbomachine (10), - command to start the turbomachine (10) in order to start the generation of current by the current generator (30) whose axis (31) is driven by the rotor shaft (110) of the turbomachine (10), - switch-off of the on-board auxiliary generator (25).