Turbomachine comprising a permanent magnet electric machine for powering a rotating load

Abstract

Turbomachine (50) for an aircraft (100), the turbomachine (50) extending along an axis of rotation (A) and comprising at least: - a rotating part (Pt) about the axis of rotation (A), - a stationary part (Pf) rotating about the axis of rotation (A) relative to the rotating part (Pt), the stationary part (Pf) comprising a fan housing (52), the turbomachine (50) being characterized in that it comprises at least one permanent magnet synchronous electric machine (M1, M2, M3), said machine (M1, M2, M3) comprising at least one permanent magnet (11) positioned on the stationary part (Pf) of the turbomachine (50) and at least one winding (12) positioned on the rotating part (Pt) of the turbomachine (50), the at least one permanent magnet (11) being arranged radially around the at least one winding (12), Figure 3

Description

Title of the invention: Turbomachine comprising a permanent magnet electric machine for powering a rotating load technical field

[0001] The invention relates to the field of aircraft turbomachinery and more particularly to a turbomachine comprising a permanent magnet synchronous electric machine.

[0002] In this description, the term "aircraft turbomachine" refers to a set of turbomachines or gas turbine devices that produce motive power, dedicated to the propulsion of an aircraft and equipped with or without a nacelle. Among these devices, a distinction is made in particular between turbojets, which provide the thrust necessary for propulsion by reaction to the high-speed ejection of gas, and turboshaft engines, in which motive power is provided by the rotation of a drive shaft. For example, turboshaft engines are used as helicopter engines. Turboprop engines (turboshafts driving a propeller) are turboshaft engines used as aircraft engines. Prior art

[0003] Climate change is a major concern for many legislative and regulatory bodies worldwide. Indeed, various restrictions on carbon emissions have been, are being, or will be adopted by various states. In particular, an ambitious standard applies to both new types of aircraft and those currently in operation, requiring the implementation of technological solutions to bring them into compliance with current regulations. Civil aviation has been actively working for several years now to contribute to the fight against climate change.

[0004] Technological research efforts have already led to very significant improvements in the environmental performance of aircraft. The Applicant takes into account the factors impacting all phases of design and development in order to obtain aeronautical components and products that are less energy-intensive, more environmentally friendly, and whose integration and use in civil aviation have moderate environmental impacts, with the aim of improving the energy efficiency of aircraft.

[0005] Consequently, the Applicant is constantly working to reduce its climate impact through the use of methods and the operation of virtuous development and manufacturing processes that minimize greenhouse gas emissions. to the minimum possible to reduce the environmental footprint of its activity.

[0006] This sustained research and development work focuses on new generations of aircraft engines, the weight reduction of aircraft, in particular through the materials used and lighter on-board equipment, the development of the use of electrical technologies to provide propulsion, and, as essential complements to technological progress, aviation biofuels.

[0007] There are devices disposed in a rotating part of a turbomachine, for example a turbine rotor, such as a device for controlling the pitch of the blades of a blower, devices for protecting small pitch of blower blades, devices for de-icing a cone or the blades of the blower, etc... Such devices can be powered by electrical energy.

[0008] To achieve this, it is known to have an electrical machine in a fixed part of a turbomachine and to transmit the electrical energy to the rotating part. This can, for example, be accomplished by means of a slip ring. However, such a slip ring can be fragile and require regular maintenance.

[0009] The fixed part refers to devices of the turbomachine configured to be stationary or fixed in rotation relative to an aircraft on which the turbomachine is installed. The fixed part includes, for example, the fan casing.

[0010] Rotating part refers to devices of the turbomachine configured to be mobile in rotation relative to the aircraft on which the turbomachine is installed.

[0011] The transmission of electrical energy to the rotating part can also be achieved by a rotating transformer associated with an inverter, resulting in an increase in the mass and volume of the turbomachine. Furthermore, an electromagnetic field generated by the rotating transformer can interfere with measuring devices of the turbomachine, such as a speed sensor or a fan pitch sensor.

[0012] There is therefore a need in this regard for a power supply in the rotating part which is reliable, of reduced mass and of reduced size. Description of the invention

[0013] One embodiment relates to a turbomachine for an aircraft, the turbomachine extending along an axis of rotation and comprising at least:

[0014] - a part rotating around the axis of rotation,

[0015] - a fixed part rotating about the axis of rotation relative to the part rotating, the fixed part comprising a blower housing,

[0016] the turbomachine being characterized in that it comprises at least one permanent magnet synchronous electric machine,

[0017] said machine comprising at least one permanent magnet positioned on the fixed part of the turbomachine and at least one winding positioned on the rotating part of the turbomachine, the at least one permanent magnet being arranged radially around the at least one winding,

[0018] the turbomachine comprising an electrical power network positioned in the rotating part, said at least one electrical power network being connected to the electrical machine and configured to carry an electric current,

[0019] the turbomachine comprising an electrical device positioned on the rotating part and configured to be powered by said electric current.

[0020] Generally, the axial direction corresponds to the direction of the axis of rotation of the turbomachine (or of a fan disk), and a radial direction is a direction perpendicular to the axis of rotation.

[0021] Furthermore, upstream and downstream are defined with respect to a normal flow direction of the gases (from upstream to downstream) through the turbomachine.

[0022] In some embodiments, the turbomachine comprises at least one turbine, at least one compressor and at least one blower which are positioned along the axial direction, i.e. linearly along the axis of rotation.

[0023] The turbomachine may also include a nacelle.

[0024] The turbine, compressor, and nacelle include elements or devices forming the fixed part of the turbomachine with respect to the aircraft, when the turbomachine is attached to the aircraft via the nacelle. In other words, the fixed part is integral with the nacelle.

[0025] The turbine, compressor, and blower comprise moving parts that rotate about the axis of rotation. These parts form the rotating section of the turbomachine. These parts exhibit relative motion with respect to the nacelle.

[0026] By means of expanding the gases in a combustion chamber, the turbomachine drives the rotational shaft on which the rotating part is fixed. The turbomachine also includes at least one electrical machine as described in this document. The electrical machine can be used in generator mode, in which it produces electrical energy, or in motor mode, in which it consumes energy to rotate the rotational shaft.

[0027] The motor mode of the electric machine can be used during a start-up of the turbomachine, or during a maintenance operation requiring a rotation of the rotating part of the turbomachine, or to inject mechanical torque on a shaft of the turbomachine to which the electric machine is coupled during any phase of flight of the aircraft.

[0028] More specifically, the machine is a rotating machine that can convert mechanical energy into alternating current electrical energy and vice versa.

[0029] The electrical machine is synchronous. In other words, the rotating part rotates synchronously with a rotating field of the stationary part. The machine may, for example, be of the type of a permanent magnet synchronous motor with an external rotor (PMSM) in which an external part, comprising at least one permanent magnet, is positioned on the stationary part and an internal part, comprising at least one winding, is positioned on the rotating part.

[0030] The machine according to the subject of this description comprises at least one permanent magnet generating a constant field. This at least one permanent magnet is positioned in the fixed part of the turbomachine. In other words, the permanent magnet is fixed relative to the nacelle and relative to the aircraft when the turbomachine is installed in the aircraft.

[0031] The permanent magnet is an inductor of the machine, that is to say that the permanent magnet has the function of inducing an electromagnetic field in the rotating part of the machine.

[0032] The rotating part of the machine consists of at least one winding, which corresponds to an armature. In other words, during rotation, at least one winding receives an induction from the inductor, the permanent magnet, and transforms it into electricity, and more precisely into a sinusoidal alternating current, in the rotating part of the turbomachine. The at least one winding can refer to an electrical coil.

[0033] The electric machine therefore directly supplies the rotating part of the turbomachine with alternating electric current on the power electrical network.

[0034] The electric current is therefore generated directly in the rotating part by the electric machine.

[0035] In the present description, the terms "at least one permanent magnet" refer to at least one pair of north-south permanent magnets.

[0036] The machine, by using at least one permanent magnet, delivers a variable voltage which varies with a rotational speed and whose effective value and frequency vary with the rotational speed of the rotating part.

[0037] The electric current generated in the rotating part powers an electrical device, also referred to as a "function," of the turbomachine, which is also located in the rotating part. In this way, it is not necessary to transmit the electric current from the stationary part to the rotating part. The efficiency, weight, and volume of the turbomachine are improved.

[0038] Any electrically consuming element of the turbomachine is called an electrical function or device. Electrically implemented turbomachine functions can also be referred to as "electrical loads." A function can perform a physical action on the turbomachine, such as heating, or a regulatory or control action.

[0039] For example, the rotating part includes functions such as a control of a step of the blower, a small step protection, or a defrosting of a cone or the blades of the blower.

[0040] For example, defrosting a cone or the blower blades requires an electrical power of about 30kW.

[0041] The object of this presentation may also have one or more of the following characteristics taken alone or in combination.

[0042] According to one embodiment, the turbomachine may include on the one hand a high-pressure body comprising a high-pressure compressor and a high-pressure turbine, and on the other hand a low-pressure body comprising a low-pressure compressor and a low-pressure turbine.

[0043] According to one embodiment, the turbomachine also includes an intermediate body comprising an intermediate pressure compressor and an intermediate pressure turbine.

[0044] According to one embodiment, the electric machine is positioned axially between the blower and the compressor.

[0045] According to one embodiment, the electric machine is positioned axially between the blower and a gearbox.

[0046] According to one embodiment, the electric machine is positioned between a gearbox and the compressor.

[0047] Thus, the machine has a higher operating speed and therefore a better efficiency.

[0048] According to one embodiment, at least one electrical power network is electrically connected to an electrical supply network which is positioned in the fixed part of the turbomachine.

[0049] The electrical supply network corresponds to a general electrical network of the turbomachine, and more generally of the aircraft, which supplies functions in the fixed part such as, for example, a power supply for the flight controls, wing anti-icing, a power supply for the cabin air conditioning system, lighting for a cabin of the aircraft, or a power supply for the cockpit.

[0050] Thus, when the power grid is connected to the supply grid, the power grid comprises two power sources: one from the turbomachine's electric motor and the other from the supply grid. There is therefore redundancy of the power sources. The electrical safety of the rotating part's functions is improved.

[0051] Furthermore, when an electric current is generated by the electric machine but When no function of the rotating part is in operation, the generated electrical current can be sent to the power grid. This ensures redundancy of the power supply to the grid.

[0052] According to one embodiment, the electrical power network is electrically connected to the electrical supply network by means of a rotating power transformer.

[0053] A rotating transformer allows the transmission of electrical energy by electromagnetic induction between first and second windings positioned respectively on the fixed part and on the rotating part of the turbomachine.

[0054] According to one embodiment, the electrical power network is configured to provide an electrical power greater than or equal to 10 kW and less than or equal to 50 kW.

[0055] According to one embodiment, the turbomachine includes an electrical control network positioned in the rotating part and connected to at least one power controller positioned in the rotating part.

[0056] The electrical control network allows the transmission of operating and regulation commands to the various functions of the rotating part.

[0057] The power supply controller generates and regulates the various functions of the rotating part such as electrical protection or the management of the start-up of a function.

[0058] According to one embodiment, the electrical control network is electrically connected to a general regulation network which is positioned in the fixed part.

[0059] The general control network can be connected to the full authority digital engine electronic controls, also known as FADEC (Full Authority Digital Engine Control). The general control network is a system that interfaces between a cockpit and the aircraft's turbomachine to ensure proper turbomachine operation. The FADEC receives all information concerning the operation of the aircraft, or more precisely, the turbomachine, and controls the various functions based on this information.

[0060] A link between the electrical control network and the general regulation network allows data to be transmitted between the two, but also allows information to be sent back, for example in the event of a failure on the turbomachine, and more particularly on a function of the rotating part of the turbomachine.

[0061] According to one embodiment, the electrical control network is electrically connected to the general regulation network by means of a rotating data transformer.

[0062] According to one embodiment, the turbomachine includes a mechanical element for separating and disconnecting the electrical machine from a shaft of the tur- bomachine.

[0063] Indeed, in the event of an electrical failure of the electrical machine or the electrical power network, it is necessary to have an element allowing the electrical machine to be mechanically disconnected.

[0064] According to one embodiment, the mechanical separation element can be positioned on the rotating part of the turbomachine.

[0065] According to one embodiment, the mechanical separation element can be a dog clutch box.

[0066] According to one embodiment, at least one electrical machine is positioned inside the blower housing.

[0067] Another aspect of the invention relates to an aircraft comprising a turbomachine according to any one of the embodiments of the present description. Brief description of the drawings

[0068] The purpose of this presentation will be better understood, thanks to the following description, which relates to several embodiments, given by way of non-limiting examples and explained with reference to the attached schematic drawings, in which:

[0069] [Fig.1] is a representation of an aircraft;

[0070] [Fig.2] is a schematic representation of a turbomachine architecture according to the purpose of this presentation;

[0071] [Fig.3] is a first embodiment of the object of this presentation;

[0072] [Fig.4] is a second embodiment of the object of this presentation; Description of the implementation methods

[0073] Figure 2 represents an aircraft 100, in this example an airplane, equipped with two turbomachines 50, in this example two propulsion units or two turbojets 50, namely one turbomachine 50 per wing 101. Only one turbomachine 50 and one wing 101 are shown in Figure 2. According to one variant, the aircraft 100 can be equipped with more than one turbomachine 50 per wing 101, each wing 101 being fitted with the same number of turbomachines 50.

[0074] Fig. 2 represents a schematic view, in cross-section along plane II of Fig. 1, of an architecture of the turbomachine 50 according to the object of the present presentation.

[0075] The turbomachine 50 includes a fan, also called a blower 52, which is positioned in a blower housing and a gas generator 54.

[0076] In this example, the gas generator 54 comprises, from upstream to downstream, the gases flowing within the turbomachine 50 from upstream to downstream, a compressor 54A (or compressor section 54A), a combustion chamber 54B, and a turbine 54C (or turbine section 54C).

[0077] The fan 52 can be driven in rotation by a shaft of the gas generator 54, by For example, directly via a shaft A of a low-pressure body, or via a Gb reduction gearbox, also known as an RGB (an English acronym for "Reduction Gear Box"), mechanically coupled to the A shaft of the low-pressure body. The Gb reduction gearbox reduces the rotational speed of the fan 52 relative to that of the A shaft of the low-pressure body.

[0078] The gas generator 54 can be of the twin-body type and comprise a low-pressure body and a high-pressure body.

[0079] The low pressure body may include a low pressure compressor 62A rotationally coupled with a low pressure turbine 66A via the low pressure shaft A.

[0080] The high-pressure body may include a high-pressure compressor 62B disposed downstream of the low-pressure compressor 62A and upstream of the combustion chamber 54B, and a high-pressure turbine 66B, disposed downstream of the combustion chamber 54B and upstream of the low-pressure turbine 66A, and coupled in rotation with the high-pressure compressor 62B by means of a high-pressure shaft B.

[0081] The compressor 54A of the gas generator 54 may include the low and high pressure compressors 62A and 62B. The turbine 54C of the gas generator 30 may include the low and high pressure turbines 66B and 66A.

[0082] The [Fig.2] is schematic, each compressor and each turbine being able to have one or more stages, each stage comprising a moving wheel and a stator.

[0083] The turbomachine 50 comprises rotating moving elements, hereafter referred to as rotating part Pt, about an axis of rotation, in a nacelle of the turbomachine 50. The nacelle is configured to be fixed on the aircraft 100. Hereafter, fixed parts Pf are designated as elements of the high-pressure body, of the low-pressure body which are fixed relative to the nacelle.

[0084] Fig. 2 illustrates the positioning of the electrical machines M1, M2, M3 connected to an electrical supply network 4 corresponding to a general electrical network of the turbomachine, and more generally of the aircraft 100. The electrical supply network 4 supplies functions in the fixed part Pf such as, for example, a power supply for the flight controls, wing anti-icing, a power supply for the cabin air conditioning system, lighting for a cabin of the aircraft, or a power supply for the cockpit.

[0085] A first electric machine Ml is positioned between the blower 52 and the compressor 54A of the gas generator 54. More specifically, the electric machine Ml is positioned axially (along the axis of rotation A) between the blower 52 and the gearbox Gb, or alternatively positioned axially between the gearbox Gb and the compressor 54A.

[0086] The electrical machine Ml will be described more precisely with reference to [Fig.4].

[0087] A second electric machine M2 is positioned downstream of the turbine 54C and a third electric machine M3 is positioned at the high-pressure compressor 62B.

[0088] The electrical machines M1, M2 and M3 produce an electric current intended to be consumed in the rotating part Pt of the turbomachine 50 or to be transmitted on the electrical supply network 4.

[0089] Having several electrical machines M1, M2, M3 allows for a reduction in the sizing of each of the electrical machines M1, M2, M3. Thus, they are more easily integrated into the overall architecture of the turbomachine. Another advantage of positioning several electrical machines M1, M2, M3 is, on the one hand, to have redundancy and therefore better overall reliability of the electrical supply network 4, and on the other hand, to be able to install simpler electrical machines.

[0090] More particularly, a first embodiment of the turbomachine 50 according to the object of this presentation is described with reference to [Fig.3].

[0091] The turbomachine 50 comprises a permanent magnet synchronous electric machine Ml 11 mechanically coupled to a shaft of the gas generator 54 such as for example the low pressure shaft A. When the electric machine Ml operates in machine mode, it takes mechanical torque from the shaft to which it is coupled so as to convert mechanical energy into alternating current electrical energy.

[0092] The electric machine Ml comprises elements positioned on the rotating part Pt and others on the fixed part Pf of the turbomachine.

[0093] On the fixed part Pf, the electric machine Ml comprises at least one permanent magnet 11 generating a constant field. The permanent magnet 11 is fixed relative to the nacelle and relative to the aircraft 100 when the turbomachine 50 is installed on it. The permanent magnet 11 is an inductor of the machine; that is, the permanent magnet 11's function is to induce an electromagnetic field on the elements of the rotating part Pt of the electric machine.

[0094] According to one embodiment, at least one permanent magnet 11 is arranged around the rotating part Pt.

[0095] According to one embodiment, at least one permanent magnet 11 is fixed on a ring or sleeve outside of at least one winding 12.

[0096] The rotating part Pt of the machine M1 consists of at least one winding 12 which corresponds to an armature. In other words, during rotation, the at least one winding 12 receives an induction from the inductor, the permanent magnet 11, and transforms it into electricity, and more precisely into a sinusoidal alternating current, in the rotating part Pt of the turbomachine 50. The at least one winding 12 may designate an electrical coil.

[0097] The electric machine Ml therefore supplies directly to the rotating part Pt of the turbomachine 50 an alternating electric current.

[0098] The electrical machine Ml, by using at least one permanent magnet 11, delivers a variable voltage, which varies with a rotational speed and whose RMS value and frequency vary with a rotational speed of the rotating part Pt. The electrical machine Ml preferably comprises at least one pair of North-South permanent magnets.

[0099] The electric machine Ml can for example be of the type of a permanent magnet synchronous motor with external rotor (PMSM in English for Permanent Magnet Syn-chronous Motor) of which an external part, comprising at least one permanent magnet 11, is positioned on the fixed part Pf and of which an internal part, comprising at least one short-circuited winding 12, is positioned on the rotating part Pt.

[0100] The electric machine M1 is connected to a power electrical network 3 which is positioned in the rotating part Pt of the turbomachine 50. An electric current with a power between 10 kW and 50 kW flows through the power electrical network 3. The electric current flowing through the power electrical network 3 is generated by the electric machine M1 directly in the rotating part Pt.

[0101] The power supply 3 feeds at least one function Fl, F2 of the turbomachine 50. The functions Fl, F2 are positioned on the rotating part Pt, and for example in the vicinity of the windings 12, approximately a few millimeters away. In this way, it is not necessary to pass the current from the stationary part Pf to the rotating part Pt. The efficiency, weight, and volume of the turbomachine 50 are improved.

[0102] A function Fl, F2 is any electrically consuming element of the turbomachine 50. A function Fl, F2 can perform a physical action on the turbomachine 50, such as heating, or a regulating or controlling action.

[0103] For example, the rotating part Pt includes functions Fl, F2 such as a control of a step of the blower, a small step protection, or a defrosting of a cone or the blades of the blower.

[0104] Furthermore, the turbomachine 50 includes an electrical control network 2 positioned in the rotating part Pt and connected to at least one power controller Ctrl positioned in the rotating part Pt. A control electrical current flows through the electrical control network 2.

[0105] The electrical control network 2 allows the transmission of operating and regulation commands to the various functions Fl, F2 of the rotating part Pt.

[0106] The power supply controller Ctrl generates and regulates the various functions Fl, F2 of the rotating part Pt such as electrical protection or management of the start-up of a function Fl, F2.

[0107] The electrical control network 2 is electrically connected to a general regulation network 22 which is positioned in the fixed part Pf.

[0108] The general control network 22 is preferably connected to the full authority digital engine electronic controls, also known as FADEC (Full Authority Digital Engine Control). The general control network 22 is a system that interfaces between a cockpit and the turbomachine 50 of the aircraft 100 so as to ensure proper operation of the turbomachine 50.

[0109] The link of the electrical control network 2 with the general regulation network 22 allows data to be transmitted, but also information to be sent back, for example in the event of a failure on the turbomachine 50, and more particularly on a function Fl, F2 of the rotating part Pt of the turbomachine 50.

[0110] Information is transmitted between the electrical control network 2 and the general regulation network 22 by a rotating data transformer 21.

[0111] The second embodiment illustrated in [Fig.4] differs from the first embodiment in that the power electrical network 3 is electrically connected, by means of a rotating power transformer 41, to a supply electrical network 4 which is positioned in the fixed part Pf of the turbomachine 50.

[0112] Thus, when the power network 3 is connected to the supply network 4, the power network 3 comprises several power sources, on the one hand from the machine M1 of the turbomachine 50, and on the other hand from the supply network 4. There is therefore redundancy of the power sources. The electrical safety of the functions Fl, F2 of the rotating part Pt is improved. For example, the small-step protection and the one-step control of the blower can be powered by independent power supplies.

[0113] Furthermore, when an electric current is generated by the electric machine Ml but no function Fl, F2 of the rotating part Pt is in operation, the generated electric current can be sent to the electrical supply network 4. This ensures redundancy of electrical supply on the electrical supply network 4.

[0114] Finally, the turbomachine 50 may include a mechanical element for separating and disconnecting the electric machine Ml from a shaft A of the turbomachine 50. For example, the mechanical element for separating and disconnecting the electric machine is positioned in the rotating part of the turbomachine 50.

[0115] Indeed, in the event of an electrical failure of the electrical machine ML or of the power electrical network 3, it is necessary to have a component allowing the electrical machine ML to be mechanically disconnected

[0116] Although the present invention has been described with reference to specific embodiments, it is evident that modifications and changes can be made to these examples without departing from the general scope of the invention as defined by the claims. In particular, individual features of the The various embodiments illustrated / mentioned can be combined in additional embodiments. Therefore, the description and drawings should be considered in an illustrative rather than restrictive sense.

[0117] It is also evident that all the characteristics described with reference to a process are transposable, alone or in combination, to a device, and conversely, all the characteristics described with reference to a device are transposable, alone or in combination, to a process.

Claims

Claims

1. A turbomachine (50) for an aircraft (100), the turbomachine (50) extending along an axis of rotation (A) and comprising at least: - a rotating part (Pt) about the axis of rotation (A), - a fixed part (Pf) rotating about the axis of rotation (A) relative to the rotating part (Pt), the fixed part (Pf) comprising a fan casing (52), the turbomachine (50) being characterized in that it comprises at least one permanent magnet synchronous electric machine (Ml, M2, M3), said machine (Ml, M2, M3) comprising at least one permanent magnet (11) positioned on the fixed part (Pf) of the turbomachine (50) and at least one winding (12) positioned on the rotating part (Pt) of the turbomachine (50), the at least one permanent magnet (11) being arranged radially around the at least one winding (12), the turbomachine (50) comprising an electrical power network (3) positioned in the rotating part (Pt),said at least one electrical power network (3) being connected to the electrical machine (Ml, M2, M3) and being configured to circulate an electric current, the turbomachine (50) comprising an electrical device (Fl, F2) positioned on the rotating part (Pt) and being configured to be powered by said electric current.,

2. Turbomachine (50) according to claim 1, wherein the at least one electrical power network (3) is electrically connected to an electrical supply network (4) which is positioned in the fixed part (Pf) of the turbomachine (50).

3. Turbomachine (50) according to claim 2, in which the electrical power network (3) is electrically connected to the electrical supply network (4) by means of a rotating power transformer (41).

4. Turbomachine (50) according to one of claims 1 to 3, in which the electrical power network (3) is configured to provide electrical power greater than or equal to 10 kW and less than or equal to 50 kW.

5. Turbomachine (50) according to any one of the preceding claims, comprising an electrical control network (2) positioned in the rotating part (Pt) and connected to at least one power supply controller (Ctrl) positioned in the rotating part (Pt).

6. Turbomachine (50) according to claim 5, in which the electrical control network (2) is electrically connected to a general regulation network (22) which is positioned in the fixed part (Pf).

7. Turbomachine (50) according to any one of the preceding claims, comprising a mechanical element for separating and disconnecting the electrical machine from a shaft (A, B) of the turbomachine (50).

8. A turbomachine (50) according to any preceding claim, wherein at least one electrical machine (M1, M2, M3) is positioned within the fan casing.

9. Aircraft (100) comprising a turbomachine (50) according to any one of the preceding claims.

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