Alternator with voltage doubling circuit

Abstract

The invention relates to a power supply system configured to supply power to a load (2), the power supply system comprising a generator (4) comprising a rotor (6) and a stator (8), the stator (8) comprising three windings (10a, 10b, 10c), each winding comprising a first end (P1, P2, P3) and a second end (N1, N2, N3), the power supply system comprising a matching circuit (1), the invention relates to a matching circuit (1) in parallel with a load (2) and comprising three rectifying circuits (30a, 30b, 30c) in series, each rectifying circuit comprising a first branch (31a, 31b, 31c) and a second branch (32a, 32b, 32c) in parallel, the first branch being coupled to a first end (P1, P2, P3) and the second branch being coupled to a second end (N1, N2, N3), the matching circuit (1) being configured to switch from a first operating mode in which the first branch is coupled to the first end (P1, P2, P3) to a second operating mode in which the second branch is coupled to the second end (N1, N2, N3). In a first operating mode, only the first branch (31a, 31b, 31c) is conductive, and in a second operating mode, the first branch (31a, 31b, 31c) and the second branch (32a, 32b, 32c) are conductive.

Description

TECHNICAL FIELD

[0001] The present invention relates to the field of electric generators and power conversion circuits, and more particularly to an electric generator equipped with a circuit for selecting, as output voltage, between the rectified rated voltage or a voltage twice the rectified rated voltage. Such a device can be applied, among others, in aviation, for turbo shaft engines having electric generators driven by a drive shaft. BACKGROUND

[0002] Climate change is a major concern for many legislative and regulatory bodies worldwide. In fact, various restrictions on carbon emissions have already been, are being or will be adopted by states. In particular, a macro-standard applies to new aircraft and to aircraft currently in circulation, requiring the implementation of technical solutions to make them compliant with current regulations. For several years, the civil aviation industry has been actively contributing to the fight against climate change.

[0003] Technical research work has already led to very significant improvements in the environmental performance of aircraft. The Applicant has considered factors at all design and development stages to obtain more energy-efficient and environmentally friendly aeronautical components and products, the integration and use of which in civil aviation have a moderate environmental impact, with the aim of increasing the energy efficiency of these aircraft.

[0004] The Applicant has therefore always worked to reduce the climate impact by using methods and operating processes for the development and manufacture of benign processes that minimize greenhouse gas emissions to the minimum possible level, to reduce the environmental footprint of the activity.

[0005] These continuous research and development efforts focus on a new generation of aircraft turbines, on reducing the weight of the aircraft (in particular through the materials used and lighter on-board equipment), on developing the use of electric power technology to ensure propulsion, and on aviation biofuels as a necessary complement to technological progress.

[0006] Some elements of the aircraft require a permanent power supply to ensure the continuity of basic services. This power can be generated by an electric generator or alternator driven by a turbine drive shaft. The drive shaft is connected, for example, to a low-pressure turbine, a high-pressure turbine or any other element that rotates during the operation of the turbine. However, combustion in the turbine is sometimes stopped in flight, in which case the electric generator is no longer driven by the combustion of fuel from the turbine.

[0007] Even if the turbine is stopped, the electric generator must continue to generate electricity to power at least the basic turbine services, such as the Full Authority Digital Engine Control (FADEC) system, or to provide power to possible fuel metering motor pumps.

[0008] If the operation of the turbine stops, the generator is driven by the sole action of the dynamic pressure of the airplane advancement acting on the turbine elements, this operation being called autorotation operation.

[0009] The dynamic pressure driving the autorotation drive shaft is limited by the following phenomena: - at high altitudes, the available dynamic pressure decreases with the decrease of the air density, - at restart altitudes (~ 25,000 feet), the Mach number of the aircraft is low, which also limits the dynamic pressure, - the shaft driving the generator usually drives other equipment (flat pumps, lubrication equipment, etc.), which leads to a torque output that further decreases this autorotation speed.

[0010] The rectified voltage obtained from the generator depends on the rotation speed of the drive shaft driving it, this voltage can become too low for the power supply to allow some electronic components to operate. Then, the generator can not be able to power the basic services of the turbine.

[0011] In particular, it is conventionally known from US7327113 an electric power supply system configured to supply electric power to a load, the electric power supply system comprising a three-phase electric generator configured to be driven in rotation by a drive shaft, said electric generator comprising a rotor and a stator, the stator comprising three windings, each winding corresponding to a phase of the electric generator, each winding comprising a first end and a second end opposite the first end.

[0012] The patent application FR3050083 states that the electric power conversion circuits known from the prior art comprise an inverter coupled downstream of a synchronous rectification DC / DC converter, also called "Pulse Amplitude Modulation (PAM)", which can be of the step-down type, of the step-up type or of the step-down-step-up type.

[0013] However, such a step-up circuit generally uses components such as transformers, inductances and capacitors, and requires high-frequency, high-power switching. These requirements can lead to a complex, bulky and expensive circuit.

[0014] Thus, the generator is generally oversized in order to be able to provide a sufficient voltage at the autorotation speed, and more particularly at the restart altitude. The generator is therefore generally heavy, bulky and provides an overvoltage in the normal operating mode, requiring additional electronic components. SUMMARY

[0015] The aim of the present invention is to be able to provide a sufficient power supply voltage from the generator even when the drive shaft driving the generator rotates at a low speed, while limiting the oversizing of the generator in a compact, simple and economical manner, in particular in the case of autorotation operation of the aircraft turbine.

[0016] In this respect, a power supply system configured to supply electrical power to a load is proposed, the power supply system comprising a three-phase generator configured to be driven in rotation by a drive shaft, said generator comprising a rotor and a stator, said stator comprising three windings, each winding corresponding to a phase of the generator, each winding comprising a first end and a second end opposite the first end, wherein the power supply system comprises a matching circuit configured to be connected in parallel to the load and comprising three rectification circuits coupled in series, each rectification circuit comprising a first branch and a second branch in parallel to the first branch, the first branch being coupled to the first end of the corresponding winding and the second branch being coupled to the second end of said winding, said matching circuit being configured to switch from a first operating mode in which only the first branch is conducting and provides an output voltage to the load having a rated value, to a second operating mode in which the first branch and the second branch are conducting and provide an output voltage to the load having a value twice the rated value.

[0017] The invention allows adapting the rectified supply voltage obtained from the three-phase generator in order to allow the power supply to have sufficient voltage even in the event of a drop in the rotational speed of the voltage generator, while limiting the supply voltage when the generator is driven at a higher speed, without requiring complex and expensive or bulky components. It is then possible to use a less expensive and less voluminous generator with a lower electrical power generation capacity.

[0018] The power supply system is advantageously supplemented by the following features taken separately or in any technically possible combination thereof: - for each rectification circuit: • the first branch comprises a first diode and a second diode having the same forward direction and the first branch is coupled to the first end of the corresponding winding between the first diode and the second diode, • the second branch comprises a first diode and a second diode having the same forward direction and a switch between the first diode and the second diode, the second diode being downstream of the first diode in the forward direction, the second branch being coupled to the second end of said winding between the switch and the first diode; - in the first operating mode, the switch is blocked and in the second operating mode, the switch is conducting; - none of the ends of the stator windings is connected to the other end of the stator winding; - each winding extends radially with respect to the axis of rotation of the rotor and the first end of the winding is between the rotor and the second end of said winding; - if the second ends of the windings of the generator are connected together, said second ends would correspond to a neutral phase; - the matching circuit comprises a first terminal and a second terminal configured to be connected to the load, the three rectification circuits being installed in series between the first terminal and the second terminal.

[0019] The present application also relates to a turbomachine comprising a drive shaft configured to be driven in rotation during operation of the turbomachine, and an electric power supply system according to the present application, the electric power supply system comprising a three-phase electric generator configured to be driven in rotation by the drive shaft.

[0020] The present application also relates to an aircraft comprising a turbomachine according to the present application, the turbomachine being attached to a wing or a fuselage of the aircraft.

[0021] The present application also relates to a method for adapting the electric power supply to the load by an electric power supply system according to the present application, wherein, when a state is determined that leads to a drop in rotation of the drive shaft or a drop in output voltage below a voltage threshold, the matching circuit switches from a first operating mode, in which only the first branch is conducting and provides an output voltage to the load having a rated value, to a second operating mode, in which the first branch and the second branch are conducting and provide an output voltage to the load having a value twice the rated value. BRIEF DESCRIPTION OF DRAWINGS

[0022] The application will be better understood by the following description, which refers to one preferred exemplary embodiment given by way of non-limiting example and explained with reference to the appended schematic drawings, in which: - Figure 1 is a simplified electrical diagram of an electric power supply system according to one possible embodiment of the present application; - Figure 2 shows an example of the rated output voltage and the voltage across the voltage rectification circuit when the switch is open, for one possible embodiment of the first operating mode according to the present application; - Figure 3 shows an example of the rated output voltage doubled and the phase voltages when the switch is conducting, for one possible embodiment of the second operating mode according to the present application; - Figure 4 shows an example of an aircraft equipped with a turbomachine, for one possible embodiment according to the present application.

[0023] In the various drawings, identical references denote similar or equivalent elements. DETAILED DESCRIPTION

[0024] REFERENCE Figure 1An example of an electric power supply system 1 configured to supply electric power to a load 2 is described. The electric power supply system 1 can advantageously form part of a turbomachine. The load 2 can notably be an element of an aircraft, and preferably an element of a basic service connected to the turbomachine, such as a Full Authority Digital Engine Control (FADEC) system, or a possible motor pump for fuel metering.

[0025] The electric power supply system 1 comprises a three-phase electric generator 4 comprising a rotor 6 configured to be driven in rotation by a drive shaft and a stator 8. The electric generator 4 is generally a synchronous machine, more particularly an alternator. The electric generator 4 converts rotational mechanical energy into electric energy in the form of alternating current.

[0026] The stator 8 comprises three windings 10a, 10b, 10c, each winding corresponding to one phase of the three-phase electric current. More particularly, the three windings 10a, 10b, 10c are distributed at 120° from each other in a plane orthogonal to the rotation axis of the rotor, and thus each deliver a phase current phase-shifted by 120° with respect to the other phase currents.

[0027] Each winding 10a, 10b, 10c comprises a first end P1, P2, P3 and a second end N1, N2, N3 opposite the first end P1, P2, P3. Typically, the windings 10a, 10b, 10c are electrically conductive coils or solenoids wound around an axis extending radially from the rotor 6, each winding 10a, 10b, 10c extending radially with respect to the rotation axis of the rotor 6, and the first end P1, P2, P3 of the winding being between the rotor 6 and the second end N1, N2, N3 of said winding. The first end P1, P2, P3 of the winding is on the side of the rotor 6, the second end N1, N2, N3 being opposite the rotor 6. Thus, the first winding 10a comprises a first end P1 and a second end N1, the second winding 10b comprises a first end P2 and a second end N2, and the third winding 10c comprises a first end P3 and a second end N3.

[0028] What is illustrated and described below is a non-limiting embodiment, but the first end can also be on one side of the rotor 6 and the second end on the opposite side of the rotor 6, in which case the terms "first end" and "second end" can be reversed in the rest of the description.

[0029] In this configuration, in contrast to the first ends P1, P2, P3 designated as hot spots, the second ends N1, N2, N3 can also be designated as cold spots. Typically, the second ends N1, N2, N3 are connected together to form the neutral point of the generator 4. In this power supply system, none of the ends of the windings 10a, 10b, 10c of the stator 8 are connected to the other end of the windings 10a, 10b, 10c of the stator 8. Therefore, the second ends N1, N2, N3 are not connected together and do not form a neutral point. Similarly, the first ends P1, P2, P3 are not connected together.

[0030] The power supply system 1 includes a matching circuit 1 configured to be connected in parallel to a load 2, and the first ends P1, P2, P3 and the second ends N1, N2, N3 of windings 10a, 10b, 10c are connected to the matching circuit 1. The matching circuit 1 is configured to switch from a first operating mode to a second operating mode, in which a voltage with a rated value is supplied to the load 2, and in the second operating mode, a voltage with twice the rated value is supplied to the load 2.

[0031] For this purpose, the matching circuit 1 includes three rectifier circuits 30a, 30b, and 30c connected in series. Each rectifier circuit 30a, 30b, and 30c includes a first branch 31a, 31b, and 31c connected in parallel and a second branch 32a, 32b, and 32c. The first branches 31a, 31b, and 31c are coupled to the first ends P1, P2, and P3 of the corresponding windings 10a, 10b, and 10c, and the second branches 32a, 32b, and 32c are coupled to the second ends N1, N2, and N3 of the windings.

[0032] Specifically, the first branch 31a of the first rectifier circuit 30a is connected to the first end P1 of the first winding 10a, the second branch 32a of the first rectifier circuit 30a is connected to the second end N1 of the first winding 10a, the first branch 31b of the second rectifier circuit 30b is connected to the first end P2 of the second winding 10b, the second branch 32b of the second rectifier circuit 30b is connected to the second end N3 of the second winding 10b, the first branch 31c of the third rectifier circuit 30c is connected to the first end P3 of the third winding 10c, and the second branch 32c of the third rectifier circuit 30c is connected to the second end N3 of the third winding 10c.

[0033] Matching circuit 1 includes a first terminal 12 and a second terminal 14 configured to be connected to load 2, with three rectifier circuits 30a, 30b, and 30c connected in series between the first terminal 12 and the second terminal 14. Each branch 31a, 31b, 31c, 32a, 32b, and 32c of the rectifier circuits 30a, 30b, and 30c includes a diode having the same forward orientation in the series connection of the rectifier circuits 30a, 30b, and 30c, thereby defining the downstream and upstream current in matching circuit 1. The forward orientation of a diode refers to the direction along which the diode allows current to flow when it is conducting.

[0034] Specifically, the first branch 31a and the second branch 32a of the first rectifier circuit 30a are coupled upstream to the first terminal 12 and thus to the load 2, and downstream to the upstream of the first branch 31b and the second branch 32b of the second rectifier circuit 30b. The downstream of the first branch 31b and the second branch 32b of the second rectifier circuit 30b are coupled upstream to the first branch 31c and the second branch 32c of the third rectifier circuit 30c. The downstream of the first branch 31c and the second branch 32c of the third rectifier circuit 30c are connected to the second terminal 14 of the matching circuit 1 and thus to the load 2.

[0035] More specifically, for each rectifier circuit 30a, 30b, 30c, the first branches 31a, 31b, 31c include first diodes 311a, 311b, 311c and second diodes 312a, 312b, 312c having the same forward orientation, and are coupled between the first diodes 311a, 311b, 311c and the second diodes 312a, 312b, 312c to the first ends P1, P2, P3 of the corresponding windings 10a, 10b, 10c. For example, the first end P2 of the second winding 10b is coupled between the first diode 311b and the second diode 312b to the first branch 31b of the second rectifier circuit 30b.

[0036] For each rectifier circuit 30a, 30b, 30c, the second branch 32a, 32b, 32c includes a first diode 321a, 321b, 321c and a second diode 322a, 322b, 322c having the same forward direction, and switches S1, S2, S3 between the first diode 321a, 321b, 322c and the second diode 322a, 322b, 322c. The second diodes 322a, 322b, 322c are located downstream of the first diodes 321a, 321b, 321c in the forward direction. The second branch 32a, 32b, 32c is coupled to the second ends N1, N2, N3 of the corresponding winding between the switches S1, S2, S3 and the first diodes 321a, 321b, 321c. For example, for the second rectifier circuit 30b, the second branch 32b includes a first diode 321b and a second diode 322b having the same forward direction, and a switch S2 between the first diode 321b and the second diode 322b. The second diode 322b is located downstream of the first diode 321b in the forward direction. The second branch 32b is coupled to the second end N2 of the second winding 10b between the switch S2 and the first diode 321b.

[0037] Because the first terminals P1, P2, P3 and the second terminals N1, N2, N3 are coupled to the branches 31a, 31b, 31c, 32a, 32b, 32c of the rectifier circuits 30a, 30b, 30c, these circuits are bidirectional when switches S1, S2, S3 are on, and unidirectional when switches S1, S2, S3 are off.

[0038] Switches S1, S2, and S3 are configured to change state between a closed state where current can pass through the switch and an open state where current cannot pass through the switch, according to a command. Switches S1, S2, and S3 are typically transistors, such as insulated-gate bipolar transistors (IGBTs) or metal-oxide-semiconductor field-effect transistors (MOSFETs), but switches S1, S2, and S3 can also be thyristors or electromechanical relays.

[0039] Matching circuit 1 is configured to switch from a first operating mode of supplying a voltage with a rated value to load 2 to a second operating mode of supplying a voltage with twice the rated value to load 2. For this purpose, switches S1, S2, and S3 are used in the following situations: - When switches S1, S2, and S3 are open, only the first branches 31a, 31b, and 31c of the rectifier circuits 30a, 30b, and 30c connected to the first terminals P1, P2, and P3 are allowed to pass current in the positive direction, while the second branches 32a, 32b, and 32c are interrupted by switches S1, S2, and S3; and due to the presence of diodes 311a, 311b, 311c, 312a, 312b, and 312c in the first branches 31a, 31b, and 31c, the phase currents from the first terminals P1, P2, and P3 of the windings 10a, 10b, and 10c are positive (only positive values ​​are retained) to provide an output current with a rated voltage corresponding to the sum of the positive voltages of the phase voltages at each moment; When switches S1, S2, and S3 are closed, both the first branches 31a, 31b, and 31c and the second branches 32a, 32b, and 32c of rectifier circuits 30a, 30b, and 30c allow current to flow in the positive direction. Since in each rectifier circuit 30a, 30b, and 30c, the first branches 31a, 31b, and 31c are connected to the first ends P1, P2, and P3 of the windings, while the second branches 32a, 32b, and 32c are connected to the second ends N1, N2, and N3 opposite to the first ends P1, P2, and P3, the first branches 31a, 31b, and 31c and the second branches 32a, 32b, and 32c alternately conduct current in the positive direction, thereby generating an output voltage corresponding to the sum of the absolute values ​​of the phase voltages (i.e., twice the rated value corresponding to the sum of the positive voltages of the phase voltages obtained in the first operating mode).

[0040] Coupling the second ends N1, N2, N3 of windings 10a, 10b, 10c to the second branches 32a, 32b, 32c does indeed allow rectification of the negative portion of the sinusoidal voltage of windings 10a, 10b, 10c. Switches S1, S2, S3 allow selection of whether to implement this rectification of these negative portions.

[0041] Figure 2An example of the output voltage 22 and positive voltages 20a, 20b, 20c at their rated values ​​is shown in volts as a function of time when the switch is open (i.e., in the first operating mode). The positive voltages 20a, 20b, 20c correspond to the voltages across each of the rectifier circuits 30a, 30b, 30c. The positive voltages 20a, 20b, 20c have a sinusoidal shape for half of their cycle and are zero for the other half. More specifically, due to diodes 311a, 311b, 311c, 312a, 312b, 312c, only the phase voltages of coils 10a, 10b, 10c are kept positive. Due to the series mounting of the rectifier circuits 30a, 30b, and 30c in parallel with load 2, the positive voltages 20a, 20b, and 20c are added together to form an output voltage 22, the rated value of which remains close to the maximum value taken by each of the positive voltages 20a, 20b, and 20c (1 in this example).

[0042] Figure 3 The example shown, expressed in volts as a function of time, illustrates the phase voltages 24a, 24b, 24c and the output voltage 26 at a value corresponding to the sum of the absolute values ​​of the phase voltages when switches S1, S2, and S3 are closed. The phase voltages 24a, 24b, 24c correspond to the voltages of coils 10a, 10b, and 10c, and therefore have a sinusoidal shape. These phase voltages 24a, 24b, 24c are rectified by diodes, and the series connection of rectifier circuits 30a, 30b, and 30c results in the summation of voltages. The value of the output voltage 26 corresponds to the sum of the absolute values ​​of the phase voltages 24a, 24b, 24c at each moment, and is twice the maximum value of each phase voltage 24a, 24b, 24c. That is, in this example, for a maximum value of 1 for each phase voltage 24a, 24b, 24c, the output voltage is close to 2.

[0043] Therefore, by simply closing switches S1, S2, and S3, the output voltage at terminals 12 and 14 of matching circuit 1 can be doubled. Thus, when the generator's drive speed is sufficient, switches S1, S2, and S3 can remain open, thereby limiting potential overvoltage. When the generator's drive speed becomes insufficient, switches S1, S2, and S3 can be closed to ensure a sufficient supply voltage.

[0044] The commands to close switches S1, S2, and S3 can be implemented using a calculator or a simpler device (e.g., analog or mechanical). Specifically, the commands to close switches S1, S2, and S3 can be generated by determining a state that causes a decrease in the rotation of the drive shaft or by switching the rectified voltage below a voltage threshold. The mechanical rotational speed of the drive shaft can be measured, for example, using a tachometer or a centrifugal force sensor (such as an electromechanical relay with centrifugal force). The output voltage or its associated value can be measured using a suitable sensor (voltmeter, etc.). The measurement result is compared to a first threshold (related to voltage or speed); if the value falls below this first threshold, the command to close switches S1, S2, and S3 is sent to the switches.

[0045] Using a closing command, the switches S1, S2, and S3 of the second branches 32a, 32b, and 32c of the three rectifier circuits 30a, 30b, and 30c are turned on, so as to double the output voltage value.

[0046] Similarly, the command to open switches S1, S2, and S3 can be implemented, for example, by comparing a voltage- or speed-related measurement with a second corresponding threshold (preferably different from the first threshold). Using the open command, switches S1, S2, and S3 of the second branches 32a, 32b, and 32c of the three rectifier circuits 30a, 30b, and 30c are blocked, thereby halving the output voltage value.

[0047] This strategy is particularly advantageous for handling the turbine's rotational speed: in the event of rotation and therefore a significant drop in the output voltage at terminals 12, 14 of the matching circuit 1, the closing of switches S1, S2, S3 allows for the restoration of a sufficiently high output voltage to ensure proper power supply to most necessary loads.

[0048] Previously, the size of generator 4 had to be set to provide sufficient output voltage (typically between 10V and 20V) to the necessary load at its rotational speed. This required a heavy, bulky, and expensive generator 4, which was too large and could cause excessive voltage (e.g., above 100-150V) during normal operation.

[0049] Due to the proposed power supply system, generator 4 can have a smaller size because the output voltage can be doubled at its rotational speed via matching circuit 1, resulting in lower cost, smaller footprint, and lower output voltage during normal operation.

[0050] Advantageously, the power supply system is installed in the turbine 101 of the aircraft 100, such as Figure 4 As shown.

[0051] This invention is defined by the claims and is not limited to the embodiments described and illustrated in the drawings. Modifications are still possible without departing from the scope of protection of this invention, particularly with respect to the composition of various elements or by substitution with technical equivalents.

Claims

1. A power supply system configured to supply power to a load (2), the power supply system comprising a three-phase generator (4) configured to be driven to rotate by a drive shaft, the generator (4) comprising a rotor (6) and a stator (8), the stator (8) comprising three windings (10a, 10b, 10c), each of the three windings corresponding to a phase of the generator (4), each winding comprising a first end (P1, P2, P3) and a second end (N1, N2, N3) opposite to the first end. Its features are, The power supply system includes a matching circuit (1) configured to be connected in parallel to the load (2) and includes three rectifier circuits (30a, 30b, 30c) coupled in series. Each rectifier circuit (30a, 30b, 30c) includes a first branch (31a, 31b, 31c) and a second branch (32a, 32b, 32c) connected in parallel with the first branch (31a, 31b, 31c). The first branch (31a, 31b, 31c) is coupled to a first end (P1, P2, P3) of a corresponding winding (10a, 10b, 10c), and the second branch (32a, 32b, 32c) is coupled to a second end (N1, N2, N3) of the winding. The matching circuit (1) is configured to switch from a first operating mode to a second operating mode. In the first operating mode, only the first branch (31a, 31b, 31c) is turned on and provides the load (2) with an output voltage of a rated value. In the second operating mode, the first branch (31a, 31b, 31c) and the second branch (32a, 32b, 32c) are turned on and provide the load with an output voltage of twice the rated value.

2. The power supply system according to claim 1, wherein, For each rectifier circuit (30a, 30b, 30c): • The first branch (31a, 31b, 31c) includes a first diode (311a, 311b, 311c) and a second diode (312a, 312b, 312c) having the same forward orientation, and is coupled between the first diode and the second diode to the first end (P1, P2, P3) of the respective winding (10a, 10b, 10c). • The second branch (32a, 32b, 32c) includes a first diode (321a, 321b, 321c) and a second diode (322a, 322b, 322c) having the same forward direction, and a switch (S1, S2, S3) between the first diode (321a, 321b, 321c) and the second diode (322a, 322b, 322c), wherein the second diode (322a, 322b, 322c) is located downstream of the first diode (321a, 321b, 321c) in the forward direction, and the second branch (322a, 322b, 322c) is coupled to the second end (N1, N2, N3) of the winding (10a, 10b, 10c) between the switch (S1, S2, S3) and the first diode (321a, 321b, 321c).

3. The power supply system according to claim 2, wherein, In the first operating mode, the switches (S1, S2, S3) are blocked, and in the second operating mode, the switches (S1, S2, S3) are open.

4. The power supply system according to any one of the preceding claims, wherein, None of the ends (P1, P2, P3) of the windings (10a, 10b, 10c) of the stator (8) are connected to the other end (N1, N2, N3) of the windings (10a, 10b, 10c) of the stator (8).

5. The power supply system according to any one of the preceding claims, wherein, Each winding (10a, 10b, 10c) extends radially relative to the rotation axis of the rotor (6), and the first end of the winding (10a, 10b, 10c) is located between the rotor (6) and the second end (N1, N2, N3) of the winding.

6. The power supply system according to any one of the preceding claims, wherein, If the second ends (N1, N2, N3) of the windings (10a, 10b, 10c) of the generator (4) are connected together, then the second ends (N1, N2, N3) will correspond to the neutral phase.

7. The power supply system according to any one of the preceding claims, wherein, The matching circuit (1) includes a first terminal (12) and a second terminal (14), the first terminal and the second terminal being configured to be connected to the load (2), and the three rectifier circuits (30a, 30b, 30c) being connected in series between the first terminal (12) and the second terminal (14).

8. A turbine (101) comprising a drive shaft configured to be driven to rotate during operation of the turbine, and a power supply system according to any one of the preceding claims, the power supply system comprising a three-phase generator (4) configured to be driven to rotate by the drive shaft.

9. An aircraft (100) comprising a turbine (101) according to the preceding claim, the turbine being attached to the wing or fuselage of the aircraft.

10. A method for adapting a power supply to a load (2) via a power supply system, said power supply system being a power supply system according to any one of claims 1 to 7, wherein, When it is determined that the rotation of the drive shaft decreases or the output voltage drops below the voltage threshold, the matching circuit (1) switches from a first operating mode to a second operating mode. In the first operating mode, only the first branch (31a, 31b, 31c) is turned on and provides the load (2) with an output voltage of the rated value. In the second operating mode, both the first branch (31a, 31b, 31c) and the second branch (32a, 32b, 32c) are turned on and provide the load with an output voltage of twice the rated value.

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