Turbomachine comprising an electric machine equipped with a fixed winding, an excitation winding and a rotating winding arranged radially

Abstract

Turbomachine (50) for an aircraft (100) comprising at least: - a rotating part (Pt) about an 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), - an electrical machine (M1, M2, M3) adapted to operate in generator mode, the turbomachine (50) being characterized in that the electrical machine (M1, M2, M3) comprises at least one stationary winding (10) and one excitation winding (20), which are positioned on the stationary part (Pf) of the turbomachine (50), and at least one rotating winding (30) positioned on the rotating part (Pt) of the turbomachine (50), the stationary winding (10), the excitation winding (20) and the rotating winding (30) being arranged radially around the axis of rotation (A). Figure 3

Description

Title of the invention: Turbomachine comprising an electrical machine equipped with a fixed winding, an excitation winding and a rotating winding arranged radially. Technical field

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

[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] - an electrical machine adapted to operate in generator mode

[0017] the turbomachine being characterized in that the electrical machine comprises at less one fixed winding and one excitation winding, which are positioned on the fixed part of the turbomachine, and at least one rotating winding positioned on the rotating part of the turbomachine, the fixed winding, the excitation winding and the rotating winding being arranged radially around the axis of rotation.

[0018] Generally, the axial direction corresponds to the direction of the axis of rotation of the turbomachine (or of a disk of a blower), and a radial direction is a direction perpendicular to the axis of rotation.

[0019] Furthermore, upstream and downstream are defined with respect to a normal flow direction of the gases (from upstream to downstream) through the turbomachine.

[0020] 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.

[0021] The turbomachine may also include a nacelle.

[0022] 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.

[0023] 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.

[0024] By means of an expansion of the gases from a combustion chamber, the turbomachine drives, in rotation, the axis of rotation on which the rotating part is fixed.

[0025] The turbomachine also includes at least one electric machine as described in this document. The electric 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 shaft of rotation.

[0026] More specifically, the electric machine is a rotating machine that can convert mechanical energy into alternating current electrical energy and vice versa.

[0027] Generally speaking, a winding can refer to an electrical coil.

[0028] The machine according to the subject of this description comprises at least one fixed winding and an excitation winding, both of which are positioned on the fixed part of the turbomachine.

[0029] The machine also includes at least one rotating winding positioned on the rotating part of the turbomachine.

[0030] The fixed winding, the excitation winding and the rotating winding are arranged radially around the axis of rotation.

[0031] The fixed winding, the excitation winding and the rotating winding are positioned concentrically around the axis of rotation so that in- Electrical inductions are possible between each of the windings.

[0032] In motor mode operation of the electric machine, the stationary winding acts as an inductor, meaning its function is to induce an electromagnetic field in the rotating winding positioned on the rotating part. To achieve this, the stationary winding is electrically supplied, notably by a three-phase current. An electromagnetic field created by the stationary winding induces an electromagnetic field in the rotating winding, which in turn causes the rotating part to rotate. The rotating winding is thus an armature of the electric machine.

[0033] 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.

[0034] In generator mode, the rotating winding acts as both an armature and a field winding. Specifically, it is excited by the field winding, producing a three-phase electric current in the rotating section. Simultaneously, it induces an electromagnetic field in the stationary winding located on the stationary section, causing the stationary winding to generate a three-phase electric current in the stationary section. The rotating winding delivers a variable voltage whose RMS value and frequency vary with the supply voltage of the field winding.

[0035] The electric current generated by the fixed winding or the rotating winding is a sinusoidal alternating current.

[0036] The electric machine therefore has several functions depending on whether it operates in motor mode or in generator mode.

[0037] The object of this presentation may also have one or more of the following characteristics taken alone or in combination.

[0038] 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.

[0039] According to one embodiment, the turbomachine also includes an intermediate body comprising an intermediate pressure compressor and an intermediate pressure turbine.

[0040] According to one embodiment, the electric machine is positioned between the blower and the compressor.

[0041] According to one embodiment, the electrical machine is positioned between the a blower and a gearbox.

[0042] According to one embodiment, the electric machine is positioned between a gearbox and the compressor.

[0043] Thus, the electric machine has a higher operating regime and therefore a better efficiency.

[0044] According to one embodiment, the rotating winding is positioned on a low-pressure shaft of the turbomachine.

[0045] According to one embodiment, the turbomachine includes at least one electrical power network positioned in the rotating part, said at least one electrical power network being connected to at least one rotating winding, and configured to carry an electric current with a power greater than or equal to 10 kW and less than or equal to 50 kW.

[0046] The electrical machine, and more particularly the rotating winding, is sized to supply the electrical power current to the electrical power network which is positioned in the rotating part.

[0047] The electric power current is generated directly in the rotating part by the electric machine.

[0048] According to one embodiment, at least one electrical power network is configured to supply at least one electrical device of the turbomachine which is positioned on the rotating part.

[0049] The principal objective of this exposition is to generate an electric current in the rotating part in order to power functions, also called electrical devices, of the turbomachine located in the rotating part. In this way, it is not necessary to pass the current from the stationary part to the rotating part. The efficiency, weight, and volume of the turbomachine are improved.

[0050] An electrical device is any element of the turbomachine that consumes electricity. The functions of the turbomachine implemented electrically can also be referred to as "electrical loads." A device can perform a physical action on the turbomachine, such as heating, or a regulating or controlling action.

[0051] However, although the object of this description is to generate an electric current in the rotating part, the electric machine according to the invention also generates an electric current in the stationary part, as detailed above. The electric current generated in the stationary part is intended to power electrical components located in the stationary part.

[0052] According to one embodiment, at least one electrical device of the turbomachine positioned in the rotating part is a device for controlling the blade pitch of a fan, small blade pitch protection devices of the fan, de-icing devices for a cone or blower blades.

[0053] For example, defrosting a cone or the blower blades requires an electrical power of about 30kW.

[0054] According to one embodiment, the electric machine is a wound rotor machine.

[0055] According to one embodiment, the fixed winding and the excitation winding are electrically connected so that an electric supply current generated by the stationary winding can power the excitation winding.

[0056] In generator mode, the rotating winding induces an electromagnetic field in the fixed winding positioned on the stationary part, such that the fixed winding generates a three-phase electric current in the stationary part. This electric current can then power the excitation winding of the electric machine. This is known as self-supply. The frequency of the voltage of the electric current generated by the fixed winding then depends on the rotational speed of the rotating part.

[0057] According to one embodiment, the fixed winding is electrically connected to a general electrical network positioned on the fixed part.

[0058] The general electrical network corresponds to an electrical network of the turbomachine, and more generally of the aircraft, which supplies devices in the fixed part such as, for example, a power supply for the flight controls, an anti-icing system for the wings, a power supply for the cabin air conditioning system, lighting for a cabin of the aircraft, or a power supply for the cockpit.

[0059] This ensures redundancy of power supply on the general electrical network.

[0060] According to one embodiment, the excitation winding comprises a DC / DC converter or a DC / AC converter.

[0061] According to one embodiment, the turbomachine includes a mechanical element for separating and disconnecting the electrical machine from a shaft of the turbomachine.

[0062] 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.

[0063] According to one embodiment, at least one electrical machine is positioned inside the blower housing.

[0064] According to one embodiment, the mechanical separation element can be a dog clutch box.

[0065] 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

[0066] 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:

[0067] [Fig-1] is a representation of an aircraft;

[0068] [Fig.2] is a schematic representation of a turbomachine architecture according to an example of the subject of this presentation;

[0069] [Fig.3] illustrates one embodiment of the object of this presentation. Description of the implementation methods

[0070] Figure 1 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.

[0071] 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.

[0072] The turbomachine 50 includes a fan, also called a blower 52, which is positioned in a blower housing and a gas generator 54.

[0073] 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).

[0074] 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 via a reduction gearbox Gb, also called an RGB (Anglo-Saxon acronym for "Reduction Gear Box"), mechanically coupled to the shaft A of the low-pressure body. The reduction gearbox Gb reduces the rotational speed of the fan 52 relative to that of the shaft A of the low-pressure body.

[0075] The gas generator 54 can be of the twin-body type and comprise a low-pressure body and a high-pressure body.

[0076] The low-pressure body may include a low-pressure compressor 62A rotationally coupled with a low-pressure turbine 66A via a low-pressure shaft A.

[0077] The high-pressure unit 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 com- high pressure press 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 54 may include the low and high pressure turbines 66B and 66A.

[0079] Figure 2 is schematic; each compressor and each turbine may present one or more stages, each stage comprising a moving wheel and a stator.

[0080] 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.

[0081] Figure 2 illustrates the positioning of electrical machines M1, M2, M3 connected to a general electrical network 4 of the turbomachine, and more generally of the aircraft 100. The general electrical network 4 supplies devices in the fixed part Pf such as a power supply for the flight controls, an anti-icing system for the wings, a power supply for the cabin air conditioning system, lighting for a cabin of the aircraft, or a power supply for the cockpit.

[0082] 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.

[0083] The electrical machine Ml will be described more precisely with reference to [Fig.3].

[0084] A second electric machine M2 is positioned downstream of turbine 54C and a The third electric machine M3 is positioned at the level of the high-pressure compressor 62B.

[0085] 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 general electrical network 4.

[0086] 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 general electrical network 4, and on the other hand, to be able to install simpler electrical machines.

[0087] More particularly, an embodiment of the turbomachine 50 according to the subject of this presentation is described with reference to [Fig.3].

[0088] The turbomachine 50 comprises an electrical machine Ml which includes elements positioned on the rotating part Pt and on the other part on the fixed part Pf of the turbomachine.

[0089] On the fixed part Pf, the electric machine Ml comprises at least one fixed winding 10 and one excitation winding 20.

[0090] The rotating part Pt of the electrical machine Ml includes at least one rotating winding 30.

[0091] The fixed winding 10, the excitation winding 20 and the rotating winding 30 are arranged radially around the axis of rotation.

[0092] The fixed winding 10, the excitation winding 20 and the rotating winding 30 are positioned concentrically around the axis of rotation so that electrical inductions are possible between each of the windings 10, 20, 30.

[0093] The fixed winding is electrically connected to the general electrical network 4 positioned on the fixed part Pf.

[0094] In addition, the fixed winding 10 and the excitation winding 20 are electrically connected by an electrical link 41 so that an electrical supply current generated by the fixed winding 10 can supply the excitation winding 20.

[0095] The fixed winding 10 is connected to an AC / DC converter 11.

[0096] The excitation winding 20 includes a DC / DC converter 21 or a DC / AC converter.

[0097] The rotating winding 30 is arranged on the low-pressure shaft of the turbomachine. The rotating winding 30 is connected via a power electrical network 3 to a six-rotating-diode rectifier 31.

[0098] The power electrical network 3 is configured to carry an electric current of power greater than or equal to 10 kW and less than or equal to 50 kW so as to supply at least one electrical device Fl of the rotating part Pt, which may be for example a control device for the pitch of the blades of a blower, small pitch protection devices for the blower blades, de-icing devices for a cone or the blower blades.

[0099] In motor mode operation of the electric machine, the fixed winding 10 is an inductor of the machine, meaning that its function is to induce an electromagnetic field in the rotating winding 30 positioned on the rotating part Pt. For this purpose, the fixed winding 10 is electrically supplied, notably by a three-phase current via the general electrical network 4. An electromagnetic field created by the fixed winding 10 induces an electromagnetic field in the rotating winding 30, which has the effect of causing the rotating part Pt to rotate. The rotating winding 30 is then an armature of the machine.

[0100] The motor mode of the electric machine can be used during a start-up of the turbomachine 50 or during a maintenance operation requiring rotation of the rotating part Pt of the turbomachine 50, or to inject mechanical torque on a shaft of the turbomachine 50 to which the electric machine is coupled during all phases of flight of the aircraft.

[0101] In generator mode, the rotating shaft is driven by the combustion chamber 54B. The rotating winding 30 then acts as both an armature and an inductor of the machine. On the one hand, it is excited by the field winding 20, producing a three-phase electric current in the rotating part Pt, and on the other hand, it induces an electromagnetic field in the stationary winding 10, positioned on the stationary part Pf, so that the stationary winding 10 generates a three-phase electric current in the stationary part Pf. The rotating winding 30 delivers a variable voltage whose RMS value and frequency vary with the supply voltage of the field winding 20.

[0102] In generator mode, the rotating winding 30 induces an electromagnetic field in the fixed winding 10 positioned on the fixed part Pf, such that the fixed winding 10 generates a three-phase electric current in the fixed part Pf. This electric current can then supply the excitation winding 20 of the electric machine. This is referred to as self-supply. The frequency of the voltage of the electric current generated by the fixed winding 10 then depends on the rotational speed of the rotating part Pt.

[0103] The electric current generated by the fixed winding 10 or the rotating winding 30 is a sinusoidal alternating current.

[0104] The electric machine therefore has several functions depending on whether it operates in motor mode or in generator mode.

[0105] 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.

[0106] 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

[0107] The mechanical separating element can be a dog clutch box.

[0108] 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 various embodiments illustrated / mentioned can be combined in additional embodiments. Therefore, the description and drawings should be considered in an illustrative rather than a restrictive sense.

[0109] It is also evident that all the features described with reference to a processes 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), - an electrical machine (Ml, M2, M3) adapted to operate in generator mode, the turbomachine (50) being characterized in that the electrical machine (Ml, M2, M3) comprises at least one fixed winding (10) and one excitation winding (20), which are positioned on the fixed part (Pf) of the turbomachine (50), and at least one rotating winding (30) positioned on the rotating part (Pt) of the turbomachine (50), the fixed winding (10), the excitation winding (20) and the rotating winding (30) being arranged radially around the axis of rotation (A).

2. A turbomachine according to claim 1, wherein the rotating winding (30) is positioned on a low pressure shaft (A) of the turbomachine (50).

3. Turbomachine (50) according to any one of the preceding claims, comprising at least one electrical power network (3) positioned in the rotating part (Pt), said at least one electrical power network (3) being connected to the at least one rotating winding (30), and configured to circulate an electric current of power greater than or equal to 10 kW and less than or equal to 50 kW.

4. Turbomachine (50) according to claim 3, in which the at least one electrical power network (3) is configured to power at least one electrical device (Fl) of the turbomachine (50) which is positioned on the rotating part (Pt).

5. Turbomachine (50) according to claim 4, in which the at least one electrical device (Fl) of the turbomachine (50) positioned in the rotating part (Pt) is a device for controlling a pitch of the blades of a fan (52), devices for protecting the small pitch of the blades of the fan (52), devices for de-icing a cone or the blades of the fan (52).

6. Turbomachine (50) according to any one of the preceding claims- preceding, in which the electric machine (Ml, M2, M3) is a wound rotor machine.

7. A turbomachine (50) according to any preceding claim, wherein the fixed winding (10) and the excitation winding (20) are electrically connected (41) such that a supply electric current generated by the fixed winding (10) can supply the excitation winding (20).

8. A turbomachine (50) according to any preceding claim, wherein the excitation winding (20) comprises a DC / DC converter (21) or a DC / AC converter.

9. 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) of the turbomachine (50).

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

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