Turbomachine comprising a permanent-magnet electric machine for powering a rotating load
Patent Information
- Authority / Receiving Office
- EP · EP
- Patent Type
- Applications
- Current Assignee / Owner
- SAFRAN AIRCRAFT ENGINES SAS
- Filing Date
- 2024-08-21
- Publication Date
- 2026-07-08
Smart Images
Figure FR2024051100_06032025_PF_FP_ABST
Abstract
Description
[0001] DESCRIPTION
[0002] TITLE: Turbomachine comprising a permanent magnet electric machine for powering a rotating load
[0003] Technical Field
[0004] The invention relates to the field of aircraft turbomachines and more particularly to a turbomachine comprising a synchronous electric machine with permanent magnets.
[0005] In this presentation, the term "aircraft turbomachine" designates a set of turbomachines or gas turbine devices producing motive power, dedicated to aircraft propulsion and equipped with a nacelle or not. Among these devices, a distinction is made in particular between turbojets providing the thrust necessary for propulsion by reaction to the high-speed ejection of gas, and turboshafts in which the motive power is provided by rotation of an engine shaft. For example, turboshafts are used as helicopter engines. Turboprops (turboshafts driving a propeller) are turboshafts used as aircraft engines.
[0006] State of the prior art
[0007] Climate change is a major concern for many legislative and regulatory bodies around the world. Indeed, various carbon emission restrictions have been, are being, or will be adopted by various states. In particular, an ambitious standard applies to both new aircraft types and those currently in operation, requiring the implementation of technological solutions to bring them into compliance with current regulations. Civil aviation has been mobilizing for several years now to contribute to the fight against climate change.
[0008] Technological research efforts have already led to very significant improvements in the environmental performance of aircraft. The Applicant takes into consideration the factors impacting all phases of design and development to obtain less energy-intensive, more environmentally friendly aeronautical components and products whose integration and use in civil aviation have moderate environmental impacts with the aim of improving the energy efficiency of aircraft.
[0009] Consequently, the Applicant is constantly working to reduce its climate impact by using methods and operating virtuous development and manufacturing processes that minimize greenhouse gas emissions to the minimum possible in order to reduce the environmental footprint of its activity. 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 onboard equipment, the development of the use of electric technologies to provide propulsion, and, as essential complements to technological progress, aeronautical biofuels.
[0010] There are devices arranged in a rotating part of a turbomachine, for example a rotor of a turbine, such as a device for controlling a pitch of the blades of a fan, devices for protecting small pitch of fan blades, devices for de-icing a cone or blades of the fan, etc. Such devices can be powered by electrical energy.
[0011] For this, it is known to have an electrical machine in a fixed part of a turbomachine and to transmit the electrical energy into the rotating part. This can, for example, be achieved by means of a slip ring. However, such a slip ring can be fragile and require regular maintenance operations.
[0012] A fixed part is a device 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.
[0013] The rotating part refers to the devices of the turbomachine configured to be mobile in rotation relative to the aircraft on which the turbomachine is installed.
[0014] 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 mass and volume of the turbomachine. In addition, an electromagnetic field generated by the rotating transformer can disturb measuring devices of the turbomachine such as a speed sensor or a fan pitch sensor.
[0015] There is therefore a need for a reliable, low-mass and small-sized power supply in the rotating part.
[0016] Statement of the invention
[0017] One embodiment relates to a turbomachine for an aircraft, the turbomachine extending along an axis of rotation and comprising at least:
[0018] - a part rotating around the axis of rotation,
[0019] - a fixed part rotating around the axis of rotation relative to the rotating part, the fixed part comprising a fan casing, the turbomachine being characterized in that it comprises at least one permanent magnet synchronous electric machine, 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, 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 being configured to circulate an electric current, the turbomachine comprising an electrical device positioned on the rotating part and being configured to be powered by said electric current.
[0020] Generally speaking, 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 relative to a normal gas flow direction (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 fan which are positioned in 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 comprise elements or devices forming the fixed part of the turbomachine relative to the aircraft, when the turbomachine is fixed to the aircraft via the nacelle. In other words, the fixed part is integral with the nacelle.
[0025] The turbine, compressor, and fan comprise moving elements that rotate around the axis of rotation. These elements form the rotating part of the turbomachine. These elements have relative movement with respect to the nacelle.
[0026] By means of an expansion of the gases of a combustion chamber, the turbomachine drives in rotation the axis of rotation on which the rotating part is fixed. The turbomachine also comprises at least one electric machine according to the subject of the present disclosure. The electric machine can be used in generator mode in which it produces electrical energy, or in motor mode in which it consumes energy in order to rotate the axis of rotation.
[0027] The motor mode of the electric machine can be used during a start-up of the turbomachine, or during a maintenance operation requiring rotation of the rotating part of the turbomachine, or to inject mechanical torque onto a shaft of the turbomachine to which the electric machine is coupled during any phase of flight of the aircraft. More precisely, the machine is a rotating machine that can convert mechanical energy into alternating current electrical energy and vice versa. The electric machine is synchronous. In other words, the rotating part rotates synchronously with a rotating field of the fixed part.The machine may for example be of the type of a permanent magnet synchronous motor with external rotor (PMSM in English for “Permanent Magnet Synchronous Motor”) of which an external part, comprising at least one permanent magnet, is positioned on the fixed part and of which an internal part, comprising at least one winding, is positioned on the rotating part.
[0028] The machine according to the subject of the present disclosure comprises at least one permanent magnet generating a constant field. The 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.
[0029] The permanent magnet is an inductor of the machine, that is, the permanent magnet has the function of inducing an electromagnetic field in the rotating part of the machine.
[0030] The rotating part of the machine consists of at least one winding which corresponds to an armature. In other words, during rotation, the 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 designate an electric coil.
[0031] The electric machine therefore supplies alternating electric current directly to the power grid in the rotating part of the turbomachine.
[0032] The electric current is therefore generated directly in the rotating part by the electric machine.
[0033] In this description, the terms "at least one permanent magnet" refer to at least one pair of north-south permanent magnets.
[0034] The machine, by using at least one permanent magnet, delivers a variable voltage which varies with a rotation speed and whose effective value and frequency vary with the rotation speed of the rotating part.
[0035] The electric current generated in the rotating part is used to power an electrical device, which can also be referred to as a "function", of the turbomachine which is also present in the rotating part. In this way, it is not necessary to pass the electric current from the fixed part to the rotating part. The efficiency, weight and volume of the turbomachine are improved.
[0036] An electrical function or device is any element of the turbomachine that consumes electricity. The functions of the turbomachine implemented electrically can also be called "electrical loads". A function can perform a physical action on the turbomachine, such as heating, or a regulation or control action. For example, the rotating part includes functions such as fan pitch control, small pitch protection, or defrosting of a fan cone or blades.
[0037] For example, defrosting a fan cone or blades requires an electrical power of approximately 30kW.
[0038] The subject matter of this disclosure may also exhibit one or more of the following characteristics, taken alone or in combination.
[0039] According to one embodiment, the turbomachine may comprise 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.
[0040] According to one embodiment, the turbomachine also comprises an intermediate body comprising an intermediate pressure compressor and an intermediate pressure turbine.
[0041] According to one embodiment, the electric machine is positioned axially between the blower and the compressor.
[0042] According to one embodiment, the electric machine is positioned axially between the blower and a reduction gearbox.
[0043] According to one embodiment, the electric machine is positioned between a reduction gearbox and the compressor.
[0044] This gives the machine a higher operating speed and therefore better efficiency.
[0045] According to one embodiment, the at least one electrical power network is electrically connected to an electrical supply network which is positioned in the fixed part of the turbomachine.
[0046] 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 in an aircraft cabin, or even a power supply for the cockpit.
[0047] Thus, when the power electrical network is connected to the supply electrical network, the power electrical network comprises two power sources, on the one hand by the turbomachine's electrical machine and on the other hand by the supply electrical network. There is therefore redundancy of the power sources. The electrical safety of the rotating part functions is improved.
[0048] Furthermore, when an electric current is generated by the electric machine but no function of the rotating part is in operation, the generated electric current can be sent to the supply electrical network. This ensures power supply redundancy on the supply electrical network.
[0049] According to one embodiment, the power electrical network is electrically connected to the power supply electrical network by means of a rotating power transformer.
[0050] A rotating transformer allows 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.
[0051] According to one embodiment, the electrical power network is configured to provide electrical power greater than or equal to 10 kW and less than or equal to 50 kW.
[0052] According to one embodiment, the turbomachine comprises an electrical control network positioned in the rotating part and connected to at least one power controller positioned in the rotating part.
[0053] The electrical control network allows operating and regulation orders to be transmitted to the various functions of the rotating part.
[0054] The power supply controller generates and regulates the various functions of the rotating part, such as electrical protection or management of the operation of a function.
[0055] According to one embodiment, the electrical control network is electrically connected to a general regulation network which is positioned in the fixed part.
[0056] The general regulation network can be connected to the full authority digital engine controls, also called FADEC (acronym for "Full Authority Digital Engine Control"). The general regulation network is a system that interfaces between a cockpit and the aircraft's turbomachine to ensure proper operation of the turbomachine. The FADEC receives all the information concerning the operation of the aircraft, or specifically the turbomachine, and controls the various functions based on this information.
[0057] A link between the electrical control network and the general regulation network makes it possible to transmit data between the two, but also to send back information, for example in the event of a breakdown in the turbomachine, and more particularly on a function of the rotating part of the turbomachine.
[0058] According to one embodiment, the control electrical network is electrically connected to the general regulation network by means of a rotating data transformer.
[0059] According to one embodiment, the turbomachine comprises a mechanical element for separating and disconnecting the electrical machine from a shaft of the turbomachine. Indeed, in the event of an electrical failure of the electrical machine or the electrical power network, it is necessary to have an element making it possible to mechanically disconnect the electrical machine.
[0060] According to one embodiment, the mechanical separation element can be positioned on the rotating part of the turbomachine.
[0061] According to one embodiment, the mechanical separation element may be a dog clutch.
[0062] According to one embodiment, the at least one electrical machine is positioned inside the fan housing.
[0063] Another aspect of the invention relates to an aircraft comprising a turbomachine according to any one of the embodiments of the present disclosure.
[0064] Brief description of the drawings
[0065] The object of the present disclosure will be better understood, thanks to the following description, which relates to several embodiments, given as non-limiting examples and explained with reference to the attached schematic drawings, in which:
[0066] [FIG. 1] is a representation of an aircraft;
[0067] [FIG. 2] is a schematic representation of an architecture of a turbomachine according to the subject of this presentation;
[0068] [FIG. 3] is a first embodiment of the subject of this presentation;
[0069] [FIG. 4] is a second embodiment of the subject of the present disclosure;
[0070] Description of the embodiments
[0071] 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. A single turbomachine 50 and a single wing 101 are represented in Figure 2. According to a variant, the aircraft 100 can be equipped with more than one turbomachine 50 per wing 101, each wing 101 being provided with the same number of turbomachines 50.
[0072] Figure 2 represents a schematic view, in section along plane II of figure 1, of an architecture of the turbomachine 50 according to the subject of the present presentation.
[0073] The turbomachine 50 includes a fan, also called a blower 52, which is positioned in a fan housing and a gas generator 54.
[0074] 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). The fan 52 can be driven in rotation by a shaft of the gas generator 54, for example directly by a shaft A of a low-pressure body, or by means of a reduction gear box Gb also called RGB (an English acronym for “Reduction Gear Box”) mechanically coupled to the shaft A of the low-pressure body. The reduction gear box Gb makes it possible to reduce the rotational speed of the fan 52 relative to that of the shaft A of the low-pressure body.
[0075] The gas generator 54 may be of the double-body type and comprise a low-pressure body and a high-pressure body.
[0076] The low pressure body may comprise a low pressure compressor 62A rotatably coupled with a low pressure turbine 66A via the low pressure shaft A.
[0077] The high-pressure body may comprise 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 via a high-pressure shaft B.
[0078] 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.
[0079] Figure 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.
[0080] The turbomachine 50 comprises elements that are mobile in rotation, hereinafter referred to as the rotating part Pt, around an axis of rotation, in a nacelle of the turbomachine 50. The nacelle is configured to be fixed to the aircraft 100. Hereinafter, the fixed part Pf refers to elements of the high-pressure body and the low-pressure body that are fixed relative to the nacelle. Figure 2 illustrates the positioning of the electrical machines M1, M2, M3 connected to an electrical power supply network 4 corresponding to a general electrical network of the turbomachine, and more generally of the aircraft 100. The electrical power 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.
[0081] A first electrical machine M1 is positioned between the blower 52 and the compressor 54A of the gas generator 54. More specifically, the electrical machine M1 is positioned axially (along the axis of rotation A) between the blower 52 and the reduction gearbox Gb, or alternatively positioned axially between the reduction gearbox Gb and the compressor 54A. The electrical machine M1 will be described more precisely with reference to FIG. 4.
[0082] A second electrical machine M2 is positioned downstream of the turbine 54C and a third electrical machine M3 is positioned at the high pressure compressor 62B. The electrical machines M1, M2 and M3 produce an electrical current intended to be consumed in the rotating part Pt of the turbomachine 50 or to be transmitted to the electrical supply network 4.
[0083] Having several electrical machines M1, M2, M3 makes it possible to reduce the dimensioning 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 simple electrical machines.
[0084] More particularly, a first embodiment of the turbomachine 50 according to the subject of the present disclosure is described with reference to FIG. 3.
[0085] The turbomachine 50 comprises a synchronous electric machine M1 with permanent magnets 11 mechanically coupled to a shaft of the gas generator 54 such as for example the low pressure shaft A. When the electric machine M1 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.
[0086] The electric machine M1 comprises elements positioned on the rotating part Pt and others on the fixed part Pf of the turbomachine.
[0087] On the fixed part Pf, the electrical machine M1 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 thereon. The permanent magnet 11 is an inductor of the machine, that is to say that the permanent magnet 11 has the function of inducing an electromagnetic field on the elements of the rotating part Pt of the electrical machine. According to one embodiment, the at least one permanent magnet 11 is arranged around the rotating part Pt.
[0088] According to one embodiment, the at least one permanent magnet 11 is fixed on a ring or a sleeve outside at least one winding 12.
[0089] The rotating part Pt of the machine M1 consists of at least one winding 12 which corresponds to an armature. In other words, during a 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 can designate an electric coil.
[0090] The electric machine M1 therefore supplies an alternating electric current directly into the rotating part Pt of the turbomachine 50.
[0091] The electric machine M1, by using at least one permanent magnet 11, delivers a variable voltage, which varies with a rotation speed and whose effective value and frequency vary with a rotation speed of the rotating part Pt. The electric machine M1 preferably comprises at least one pair of North-South permanent magnets.
[0092] The electrical machine M1 may for example be of the type of a permanent magnet synchronous motor with external rotor (PMSM in English for Permanent Magnet Synchronous 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.
[0093] The electrical machine M1 is connected to a power electrical network 3 which is positioned in the rotating part Pt of the turbomachine 50. In the power electrical network 3 flows an electric current whose power is between 10kW and 50kW. The electric current flowing in the power electrical network 3 is generated by the electrical machine M1 directly in the rotating part Pt.
[0094] The power electrical network 3 supplies at least one function F1, F2 of the turbomachine 50. The functions F1, F2 are positioned on the rotating part Pt, and for example in the vicinity of the windings 12, approximately a few millimeters. In this way, it is not necessary to pass the current from the fixed part Pf to the rotating part Pt. The efficiency, weight and volume of the turbomachine 50 are improved.
[0095] Any element of the turbomachine 50 that consumes electricity is called a function F1, F2. A function F1, F2 can perform a physical action on the turbomachine 50, such as heating, or a regulation or control action.
[0096] For example, the rotating part Pt comprises the functions F1, F2 such as a control of a pitch of the fan, a small pitch protection, or a de-icing of a cone or the blades of the fan. Furthermore, the turbomachine 50 comprises 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. In the electrical control network 2 circulates an electrical control current.
[0097] The electrical control network 2 allows operating and regulation orders to be transmitted to the various functions F1, F2 of the rotating part Pt.
[0098] The power supply controller Ctrl generates and regulates the different functions F1, F2 of the rotating part Pt such as for example electrical protection or management of the operation of a function F1, F2.
[0099] The control electrical network 2 is electrically connected to a general regulation network 22 which is positioned in the fixed part Pf.
[0100] The general regulation network 22 is preferably connected to the full authority digital electronic engine controls, also called FADEC (acronym for “Full Authority Digital Engine Control”). The general regulation network 22 is a system which interfaces between a cockpit and the turbomachine 50 of the aircraft 100 so as to ensure proper operation of the turbomachine 50.
[0101] The connection of the electrical control network 2 with the general regulation network 22 makes it possible to transmit data, but also to send back information, for example in the event of a breakdown on the turbomachine 50, and more particularly on a function F1, F2 of the rotating part Pt of the turbomachine 50.
[0102] The information is transmitted between the control electrical network 2 and the general regulation network 22 by a rotating data transformer 21.
[0103] The second embodiment illustrated in Figure 4 differs from the first embodiment in that the electrical power network 3 is electrically connected, by means of a rotating power transformer 41, to an electrical supply network 4 which is positioned in the fixed part Pf of the turbomachine 50.
[0104] Thus, when the power electrical network 3 is connected to the power supply electrical network 4, the power electrical network 3 comprises several power sources, on the one hand by the machine M1 of the turbomachine 50, and on the other hand by the power supply electrical network 4. There is therefore a redundancy of the power sources. The electrical safety of the functions F1, F2 of the rotating part Pt is improved. For example, the small pitch protection and the control of a pitch of the fan can be powered by independent power supplies.
[0105] Furthermore, when an electric current is generated by the electric machine M1 but no function F1, F2 of the rotating part Pt is in operation, the generated electric current can be sent to the power supply network 4. This makes it possible to ensure power supply redundancy on the power supply network 4.
[0106] Finally, the turbomachine 50 may comprise a mechanical element for separating and disconnecting the electrical machine M1 relative to a shaft A of the turbomachine 50. For example, the mechanical element for separating and disconnecting the electrical machine is positioned in the rotating part of the turbomachine 50.
[0107] In fact, in the event of an electrical failure of the electrical machine M1 or of the power electrical network 3, it is necessary to have an element allowing the electrical machine M1 to be mechanically disconnected.
[0108] Although the present invention has been described with reference to specific embodiments, it is obvious that modifications and changes may 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 various illustrated / mentioned embodiments may be combined in additional embodiments. Therefore, the description and drawings should be considered in an illustrative rather than a restrictive sense. It is also obvious that all features described with reference to a method are transposable, alone or in combination, to a device, and conversely, all features described with reference to a device are transposable, alone or in combination, to a method.
Claims
CLAIMS 1. Turbomachine (50) for an aircraft (100), the turbomachine (50) extending along an axis of rotation (A) and comprising at least: - a rotating part (Pt) around the axis of rotation (A), - a fixed part (Pf) rotating around 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 (M1, M2, M3), said machine (M1, 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 (M1, M2, M3) M3) and being configured to circulate an electric current,the at least one electrical power network (3) being electrically connected to an electrical supply network (4) which is positioned in the fixed part (Pf) of the turbomachine (50), the turbomachine (50) comprising an electrical device (F1, F2) positioned on the rotating part (Pt) and being configured to be powered by said electric current., 2. Turbomachine (50) according to claim 1, in which the electrical power network (3) is electrically connected to the electrical supply network (4) by means of a rotating power transformer (41).
3. Turbomachine (50) according to one of claims 1 to 2, 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.
4. 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).
5. Turbomachine (50) according to claim 4, in which the electrical control network (2) is electrically connected to a general regulation network (22) which is positioned in the fixed part (Pf).
6. 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).
7. Turbomachine (50) according to any one of the preceding claims, wherein the at least one electric machine (M1, M2, M3) is positioned inside the fan casing.
8. Aircraft (100) comprising a turbomachine (50) according to any one of the preceding claims.