Aircraft power generation system and related method

Abstract

A power generation system for supplying power to at least one electrical grid of an aircraft, the power generation system comprising a control device configured to receive a universal operational setpoint and to output a first parameterized setpoint (PCONS1) of a first converter (C1) and a second parameterized setpoint (PCONS2) of a second converter (C2), each parameterized setpoint (PCONS1, PCONS2) being a power supply for switching between the converters (C1, C2) and the first converter (C1) and the second converter (C2). The control device is controlled by a voltage regulation setpoint (RegU) of the distribution voltage or an auxiliary regulation setpoint (RegA) for the turbine, the control device being configured to output a parameterized setpoint with a stable delay with respect to the parameterized setpoint of the voltage conversion (TransU) for the auxiliary conversion (TransA) such that the voltage regulation (RegU) is extended during the auxiliary conversion (TransA).

Description

Technical Field

[0001] This invention relates to a power generation system for an aircraft, and more particularly to an electric hybrid system for an aircraft. Background Technology

[0002] Climate change has become a major issue of concern for many legislative and regulatory bodies worldwide. In fact, countries have already adopted, are adopting, or will adopt various measures to limit carbon emissions. In particular, an ambitious standard applies to both new and existing aircraft, requiring the implementation of technical solutions to ensure compliance with current regulations. The civil aviation industry has been continuously mobilizing for many years to contribute to addressing climate change.

[0003] Technological research has significantly improved the environmental performance of aircraft. By comprehensively considering the influencing factors at each stage of design and development, the applicant is committed to developing more energy-efficient and environmentally friendly aviation components and products, ensuring that their integration and application in the civil aviation field have a controllable environmental impact, thereby improving the energy efficiency of aircraft.

[0004] Current research and development efforts focus particularly on next-generation thermoelectric hybrid aircraft engines. The applicant's goal is to develop an aircraft equipped with a high-powered power generation system. This allows for an increase in the number of onboard electrical devices, thereby reducing fuel consumption.

[0005] In fact, it is known that generators are integrated into conventional aircraft turbines. These generators extract mechanical energy from the low-pressure shaft of the aircraft turbine to produce electrical energy, which is then delivered to the power distribution unit.

[0006] To increase power generation, refer to Figure 1 A power generation system 100 is proposed, configured to extract mechanical energy from both the low-pressure shaft BP and the high-pressure shaft HP of the aircraft turbine T to provide a calibrated distribution voltage to the aircraft power grid REA. In other words, the power generation system 100 includes at least two power supply paths, namely path BP and path HP in this embodiment. The power generation system 100 can also be connected to a power source BAT or a charge load.

[0007] In fact, the power generation system 100 is configured to receive the operating setpoint P from the computer electronic control unit (ECU) of the turbine T. ECU The operating setting P ECU This allows for the determination of parameters such as the amount of electricity to be generated and the mechanical extraction amount on each axis. In other words, it enables the operation of the setpoint P. ECU It can determine the selected hybrid power strategy.

[0008] refer to Figure 2The power generation system 100 includes two generators G1 and G2 (power sources) respectively connected to the low-pressure shaft BP and high-pressure shaft HP of the turbine T. The power generation system 100 also includes two converters C1 and C2 respectively connected to the two generators G1 and G2, specifically inverters. Each generator G1 and G2 generates alternating current, which is then rectified by the converters C1 and C2 to provide a distribution voltage V to the power distribution unit EDU, which is electrically connected to the aircraft electrical grid REA, power source BAT, or charge load. DC .

[0009] This example illustrates an application related to power generation, but the invention is more generally applied to the field of hybrid power, where the motor acts as both a generator, obtaining mechanical energy from the low-voltage shaft BP or the high-voltage shaft HP, and a motor, injecting mechanical energy into the low-voltage shaft HP or the high-voltage shaft HP. When performing the motor function, the converters C1 and C2 can also convert the DC voltage V... DC The current is converted to alternating current to supply AC power to the two motors G1 and G2 respectively, thereby achieving power injection.

[0010] For clarity and simplicity, only the power generation function is shown. When the motor function is executed, the electronic control unit (ECU) provides the operating setpoint P. ECU This is to determine the amount of mechanical energy injected, such as the amount injected into each axis. The hybrid power system is bidirectional, enabling it to both generate electrical energy and inject mechanical energy. The electronic control unit (ECU) determines an operating setpoint P that depends on the availability, capacity, and charge demand of the power source. ECU To achieve global monitoring.

[0011] As is well known, each converter C1, C2 includes multiple switches, particularly power transistors, enabling the regulation of the electrical energy generated and acquired by each generator G1, G2 on each shaft BP, HP. The power generation system 100 includes a control device 200, which is used to adjust the operating setpoint P. ECU Set the parameter setting value P CONS1 P CONS2 The output is sent to each converter C1 and C2 to obtain the distribution voltage V adapted to the power distribution unit EDU. DC .

[0012] It is known that each converter C1, C2 is configured to receive several types of parameterized setting values ​​P CONS1 P CONS2 :

[0013] The voltage regulation setting value RegU is configured to control converters C1 and C2 to the distribution voltage V. DC ,

[0014] The auxiliary adjustment setting RegA is configured to make converters C1 and C2 subject to the requested power or torque of the aircraft turbine T.

[0015] Specifically, the control device 200 can determine the parameterized setpoint P. CONS1 P CONS2 To determine the adjustment type of each converter C1, C2.

[0016] In practice, the control device 200 is connected to each converter C1, C2 via one or more communication cables (point-to-point or multi-user link) to transmit the parameterized setpoint P. CONS1 P CONS2 This communication cable, especially the CAN type, enables the transmission of parameterized setting values ​​P. CONS1 P CONS2 The cycle time is approximately 15ms, which is very slow. Therefore, rapid dynamic adjustment is not possible.

[0017] During normal operation, the first converter C1 is typically set to voltage regulation mode RegU to optimally control the distribution voltage V. DC The second converter C2 uses the auxiliary adjustment mode RegA.

[0018] Depending on operational requirements, the roles of converters C1 and C2 can be switched. For this purpose, refer to... Figure 3 The computer ECU determines the operating setting value P for issuing the role switching command. ECU The control device 200 determines the parameterized setting value P for switching the roles of converters C1 and C2. CONS1 P CONS2 Therefore, when the first parameterized setting value P is received... CONS1 At that time, the first converter C1 switches from voltage regulation mode RegU to auxiliary regulation mode RegA. Conversely, upon receiving the second parameterized setpoint P... CONS2 At that time, the second converter C2 switches from auxiliary regulation mode RegA to voltage regulation mode RegU.

[0019] In practice, the distribution voltage V must be optimally controlled during the switching between the two regulation modes. DC Therefore, this role switching is complex. Furthermore, when one or more parameterized settings P on the communication cable... CONS1 P CONS2 In the event of a loss, the power generation system must be robust. In fact, refer to... Figure 4 If the second set value P CONS2 If a parasitic delay Tp occurs during transmission, both converters C1 and C2 will be in auxiliary adjustment mode RegA, such as... Figure 5 As shown, this will cause the distribution voltage VDC Instability INST. Summary of the Invention

[0020] This invention proposes a method for regulating a power generation system, aiming to at least partially eliminate the above-mentioned drawbacks and overcome the shortcomings of the prior art.

[0021] This invention relates to a power generation system for supplying power to at least one electrical grid for an aircraft, the aircraft including at least one aircraft turbine, the aircraft turbine including a low-pressure shaft and a high-pressure shaft configured to be driven to rotate, the power generation system being configured to receive general operating setpoints defining a hybrid power strategy, the power generation system comprising:

[0022] • A power distribution unit with distribution voltage,

[0023] • The first power supply path includes:

[0024] The first generator is configured to produce alternating current by extracting mechanical energy from either the low-voltage shaft or the high-voltage shaft.

[0025] A first converter, connected to the first generator, supplies power to the power distribution unit and converts the generated alternating current into a first distribution current according to its parameter settings.

[0026] • The second power supply path includes:

[0027] • The second generator is configured to produce alternating current by extracting mechanical energy from the other of the low-voltage shaft and the high-voltage shaft.

[0028] The second converter, connected to the second generator, supplies power to the power distribution unit and converts the generated AC power into a second distribution current according to its parameter settings.

[0029] The control device is configured to receive general operating settings and output a first parameterized setting value for the first converter and a second parameterized setting value for the second converter.

[0030] • Each parameterized setting should be a voltage regulation setting used to control the converter to the distribution voltage, or an auxiliary regulation setting used for the turbine.

[0031] • The control device is configured to output a parameterized setpoint with a stable delay relative to the parameterized setpoint of the voltage conversion for auxiliary conversion, such that voltage regulation is extended during the auxiliary conversion, which refers to the conversion period from the voltage regulation setpoint to the auxiliary regulation setpoint, and the voltage conversion refers to the conversion period from the auxiliary regulation setpoint to the voltage regulation setpoint.

[0032] Introducing a stabilization delay during the auxiliary switching process advantageously allows the distribution voltage of the distribution unit to remain stable. This time setting provides ample time for voltage switching. In other words, it forces the voltage regulation of both converters to operate in parallel temporarily, thereby ensuring grid quality. This allows switching to voltage regulation mode before switching to auxiliary regulation mode.

[0033] The stable delay is at least greater than the maximum delay time for the converter to receive the general operating settings.

[0034] In one respect, the stable latency is greater than 2ms. This stable latency ensures that the time delay is greater than the maximum parasitic latency.

[0035] In one respect, the stabilization latency is less than 45ms. This stabilization latency means that a high level of response speed can be maintained when the regulation system changes.

[0036] According to one aspect, the stabilization delay is greater than the maximum parasitic delay, which is determined between the moment of transmission of the parameterized setpoint related to the conversion and the effective switching moment from one regulation mode to another. This allows switching to voltage regulation mode before switching to auxiliary regulation mode.

[0037] In one respect, the stable delay is less than three times the maximum parasitic delay. This stable delay means that a high level of response speed can be maintained when the regulation system changes. In another respect, the stable delay is approximately twice the maximum parasitic delay. This stable delay achieves a balance between stability and response speed.

[0038] According to one aspect, the control device includes an adjustment module configured to calculate the deviation between a measured value of the distribution voltage and a set value of the distribution voltage, the adjustment module including a gain parameter proportional to the deviation. This can prevent energy drift during temporary parallel operation.

[0039] In one respect, the adjustment module is of the "proportional-integral" type, with the gain parameter being the integral gain. When the voltage error is low, the gain parameter is very low, and it increases as the voltage error rises. This avoids energy drift between the two converters during parallel operation.

[0040] An aircraft is also shown, comprising at least one aircraft turbine and at least one power generation system as described above, the aircraft turbine including a low-pressure shaft and a high-pressure shaft configured to be driven to rotate, the power generation system supplying power to at least one electrical grid of the aircraft.

[0041] Also shown is a method for powering at least one power grid to an aircraft via a power generation system as described above, the aircraft including at least one aircraft turbine comprising a low-pressure shaft and a high-pressure shaft configured to be driven to rotate, the method comprising the following steps:

[0042] - Receives general operating settings that define the hybrid power strategy.

[0043] - Output the first parameterized setting value of the first converter and the second parameterized setting value of the second converter based on the general operating setting value.

[0044] - For auxiliary conversion, the output parameterized setpoint has a stable delay relative to the parameterized setpoint of the voltage conversion, thereby extending the voltage regulation during the auxiliary conversion.

[0045] A computer program product is also proposed, comprising at least one instruction sequence stored by a processor and readable by the processor, which, when read by the processor, is able to execute the steps of the method described above. Attached Figure Description

[0046] The invention will be better understood by reading the following description given by way of example and by referring to the accompanying drawings given by way of non-limiting example, wherein the same reference numerals denote similar objects.

[0047] Figure 1 This is a schematic diagram of a power generation system that extracts mechanical energy from an aircraft turbine.

[0048] Figure 2 It is a schematic diagram of a power generation system with a generator, converter, power distribution unit and control device.

[0049] Figure 3 This is a schematic diagram illustrating the theoretical changes in converter regulation.

[0050] Figure 4 This is a schematic diagram illustrating the changes in converter regulation after the occurrence of parasitic delay.

[0051] Figure 5 This is a schematic diagram illustrating the instability of power distribution voltage caused by parasitic delay.

[0052] Figure 6 This is a schematic diagram of a power generation system for extracting mechanical energy from an aircraft turbine, according to an embodiment of the present invention.

[0053] Figure 7 An auxiliary transition with a stable delay and voltage conversion is schematically illustrated.

[0054] Figure 8 This is a schematic diagram of transmission with parameterized settings for a stable delay.

[0055] Figure 9 This is a schematic diagram illustrating the switching delay between two converters.

[0056] Figure 10 This is a diagram illustrating the stabilization delay and switching delay.

[0057] Figure 11 This is a schematic diagram showing that no unstable distribution voltage occurred after the introduction of a stable delay.

[0058] Figure 12 This is a schematic diagram of the adjustment module used for parallel adjustment during the switching delay.

[0059] Figure 13 The illustration schematically shows the evolution of distribution voltage and power generated by the prior art and the present invention.

[0060] It should be noted that the accompanying drawings illustrate the invention in detail and are used to implement the invention; if applicable, the drawings can certainly be used to better define the invention. Detailed Implementation

[0061] Figure 6 A power generation system 1 for an aircraft is shown. The aircraft includes a turbine T having a low-pressure shaft BP and a high-pressure shaft HP. In this example, the turbine T includes a low-pressure compressor 71 and a low-pressure turbine 74 connected by the low-pressure shaft BP, and a high-pressure compressor 72 and a high-pressure turbine 73 connected by the high-pressure shaft HP.

[0062] The power generation system 1 is configured to obtain mechanical energy from both the low-voltage shaft BP and the high-voltage shaft HP to provide calibrated electrical energy to the aircraft's electrical grid REA. The power generation system 1 can also be connected to the power supply BAT or the LOAD of the electrical equipment to be powered.

[0063] In fact, as will be shown later, the power generation system 1 more extensively achieves electrical hybridization, enabling it to both obtain energy from the turbine T and inject energy into the turbine.

[0064] The power generation system 1 is configured to receive general operating setpoints P from the computer ECU of the turbine T. ECUG The general operating setting P ECUG Used to determine factors such as the amount of electricity to be generated and the mechanical load on each axis. In other words, the general operating setpoint P ECUG Used to determine the selected hybrid power strategy. In practice, the general operating setpoint P ECUG It adopts a power setting value in the form of "Setting Value PS" or a power sharing setting value in the form of "Mode PS".

[0065] refer to Figure 6The power generation system 1 includes two generators G1 and G2, respectively connected to the low-pressure shaft BP and high-pressure shaft HP of the turbine T. The power generation system 1 includes:

[0066] - The first power supply path V1 includes:

[0067] The first generator G1 is configured to generate alternating current by obtaining mechanical energy from the low-voltage shaft BP.

[0068] • The first converter C1, connected to the first generator G1, is used to convert the generated alternating current into a first distribution current I according to its parameter settings. DC1 ,

[0069] • The second power supply path V2 includes:

[0070] • The second generator G2 is configured to generate alternating current by extracting mechanical energy from the high-voltage shaft HP.

[0071] The second converter C2, connected to the second generator G2, is used to convert the generated alternating current into a second distribution current I according to its parameter settings. DC2 .

[0072] In this example, generators G1 and G2 are preferably motors capable of operating in generator or motor mode. Each motor is known to include a rotor fixed to a rotating shaft (here, shaft BP or shaft HP) and a stator including windings to generate three-phase alternating current. The structure and operation of such motors are well known and will not be discussed further in detail.

[0073] refer to Figure 6 The power generation system 1 includes a power distribution unit (EDU) that is electrically connected to the aircraft's power grid REA, power supply BAT, or charge load.

[0074] Each converter C1 and C2 can provide the distribution voltage V to the power distribution unit EDU. DC Preferably, the power distribution unit (EDU) includes a voltage bus.

[0075] Knownly, each converter C1, C2 includes multiple switches, specifically transistors, enabling regulation of the generated electrical energy and the mechanical energy obtained from each BP, HP shaft, so as to adjust the distribution current I as needed. DC1 I DC2 .

[0076] According to the present invention, reference Figure 6 The power generation system 1 includes a control device 2, which is configured to receive a general operating setpoint P. ECUG And determine the first parameterization setting value P of the first converter C1. CONS1 The second parameterization setting value P of the second converter C2CONS2 The parameterized setting value P CONS1 P CONS2 Used to control the switching of converter transistors C1 and C2.

[0077] Subsequently, each parameterized setting P CONS1 P CONS2 To enable converters C1 and C2 to be controlled by the distribution voltage V DC The voltage regulation setting RegU, or the auxiliary regulation setting RegA (e.g., power regulation setting or torque regulation setting), is configured to control the power / torque of the converters C1 and C2 to the high-pressure HP shaft or low-pressure BP shaft of the aircraft turbine.

[0078] As mentioned earlier, the voltage regulator RegU can be used to control the distribution voltage V of the power distribution unit EDU. DC .

[0079] In the following text, see references Figure 7 When the parameter setting value P CONS1 P CONS2 The transition from the voltage regulation setpoint RegU to the auxiliary regulation setpoint RegA is called "Auxiliary Transition TransA". Similarly, when the parameterized setpoint P... CONS1 P CONS2 When the control switches from the auxiliary adjustment setpoint RegT, RegP to the voltage adjustment setpoint RegU, it is called "voltage conversion TransU".

[0080] refer to Figure 8 Control device 2 is configured to output a parameterized setpoint with a stable delay Ts relative to the parameterized setpoint of voltage conversion TransU during auxiliary conversion TransA. This causes a time shift in the parameterized setpoint of auxiliary conversion TransA relative to the parameterized setpoint of voltage conversion TransU. This allows converters C1 and C2, affected by auxiliary conversion TransA, to temporarily stabilize the distribution voltage V. DC This avoids instability. This design is particularly advantageous if the converters C1 and C2 affected by the voltage conversion TransU have parasitic delays when receiving their parameterized settings.

[0081] In the prior art, the control device 2 is configured to directly output the first parameterized setpoint P of the first converter C1 essentially simultaneously. CONS1 The second parameterization setting value P of the second converter C2 CONS2 The introduction of the stabilization delay Ts thus makes the control device 2 send its parameterized setpoint P. CONS1 P CONS2It can adjust its time delay.

[0082] refer to Figures 8 to 10 In the nominally operating embodiment, the first converter C1 is in voltage regulation mode RegU, and the second converter C2 is in auxiliary regulation mode RegA. It goes without saying that the roles of converters C1 and C2 can be interchanged.

[0083] like Figure 8 As shown, the computer ECU outputs the general operating setting value P. ECUG The general operating setting indicates that the first converter C1 is in auxiliary regulation mode RegA and the second converter C2 is in voltage regulation mode RegU. The control device 2 outputs a value relative to the second parameterized setting P. CONS2 The first parameterized setting P with stable delay Ts CONS1 .

[0084] refer to Figure 9 and Figure 10 The first parameter setting value P CONS1 The first converter C1 switches to auxiliary adjustment mode RegA during the auxiliary switching time BascA. Similarly, the second parameterized setpoint P... CONS2 The second converter C2 is switched to voltage regulation mode RegU during the voltage switching time BascU.

[0085] like Figure 10 As shown, the auxiliary switching time BascA occurs after the voltage switching time BascU, which has a switching delay Tb. During the switching delay Tb, the two converters C1 and C2 operate in parallel in voltage regulation mode RegU. In reality, due to the presence of parasitic delay Tp (transmission delay, frame loss, etc.), it is difficult to determine the time interval from the transmission of the parameterized setpoint to the relevant switching instant.

[0086] Furthermore, the stable delay Ts must be calibrated to be greater than the parasitic delay Tp. Preferably, the maximum parasitic delay Tpmax is determined, for example, through statistics, simulation, or feedback. The stable delay Ts is greater than the maximum parasitic delay Tpmax, and preferably less than three times the maximum parasitic delay Tpmax, thereby avoiding excessive delay to the auxiliary conversion TransA. In this example, the stable delay Ts is twice the maximum parasitic delay Tpmax.

[0087] According to one aspect, the stable latency Ts is greater than 2ms, and preferably less than 45ms. This achieves a balance between stability and response speed.

[0088] The stability delay Ts implements a time delay to ensure grid quality during the transition of TransA to regulation type during auxiliary conversion.

[0089] like Figure 9 As shown, after introducing a stabilization delay Ts, the two converters C1 and C2 are in parallel voltage regulation RegU during the switching time Tb. Figure 11 As shown, this temporary voltage regulation allows the power distribution unit (EDU) to be powered in parallel and reduces the distribution voltage V. DC The instability.

[0090] It is known that a motor operates in four quadrants based on its speed and torque. To reduce motor wear, it is best to avoid changing quadrants during regulation. Parallel power supply remains complex because it is necessary to minimize quadrant changes (motor, generator) while ensuring that energy drift between the two converters C1 and C2 is minimized.

[0091] In this example, reference Figure 12 The control device 2 includes a proportional-integral type adjustment module 20, which implements the function of the subtractor 21 and is used to calculate the distribution voltage V. DC The measured value and the distribution voltage setting value V DC The deviation Δ between the parameters, the proportional gain constant Kp, the integral gain Ki, the integrator 22, and the summer 23 are used to determine the parameterized setpoint P. CONS1 P CONS2 .

[0092] In this example, to introduce a stable delay Ts, the integral gain Ki is not a constant value, but a variable dependent on the deviation Δ (Ki = f(Δ)), where f is a proportional function. This allows for convenient adjustment of the regulation module 20. Therefore, to reduce any voltage drift, the integral gain Ki depends on the voltage deviation Δ. Advantageously, when the deviation Δ is small, the integral gain Ki is also small. Conversely, when the deviation Δ is large, the integral gain Ki is also large.

[0093] The proportional function f can take various forms, such as a step function (or "all or nothing"). If the deviation Δ is less than a predetermined threshold, the integral gain Ki can be equal to a first value Ki1; if the deviation Δ is greater than the predetermined threshold, the integral gain Ki can be equal to a second value Ki2, which is greater than the first value Ki1. The proportional function f can also be a lag function, a saturated or unsaturated linear function.

[0094] The voltage regulation RegU based on the voltage difference Δ enables each converter C1 and C2 to achieve optimal self-adjustment, thereby realizing transient parallel operation of converters C1 and C2. This allows for convenient adjustment of each converter C1 and C2 to supply power to the power distribution unit EDU. This enables the two voltage loops to operate in parallel.

[0095] When the two converters C1 and C2 are in voltage regulation mode RegU, the regulation module 20 is enabled.

[0096] refer to Figure 13 When the two generators G1 and G2 are running in parallel, the two converters C1 and C2 provide power Pbp and Php respectively to provide a distribution voltage Vdc that conforms to the predetermined voltage standard GAB in order to ensure grid quality.

[0097] In existing technologies, such as Figure 13 As shown by curves a1 and b1, the distribution voltage Vdc is at the limit of the voltage standard GAB, and the operating quadrants QUAD of generators G1 and G2 will change, which will increase the risk of wear and instability.

[0098] To minimize quadrant changes of generators G1 and G2 during parallel operation, such as Figure 13 As shown in curve b2, converters C1 and C2 are controlled to meet the power distribution voltage requirements V of their respective power distribution units (EDUs). DC Half of. For example... Figure 13 As shown in curve a2, the distribution voltage Vdc also conforms to the voltage standard GAB.

[0099] Therefore, even if the power output of the two generators G1 and G2 drifts during parallel operation, the operating quadrants of generators G1 and G2 will not change, which advantageously reduces the risk of wear and instability.

[0100] Because of this invention, by introducing a stable delay Ts that allows converters C1 and C2 to temporarily run in parallel, the role switching of converters C1 and C2 will not cause instability in the distribution voltage VDC.

Claims

1. A power generation system (1) for supplying power to at least one electrical grid (REA) of an aircraft, the aircraft including at least one aircraft turbine (T), the aircraft turbine including a low-pressure shaft (BP) and a high-pressure shaft (HP) configured to be driven to rotate, the power generation system (1) being configured to receive a general operating setpoint (P) defining a hybrid power strategy. ECUG ), characterized in that, The power generation system (1) includes: - Has power distribution voltage (V) DC Power distribution unit (EDU), - The first power supply path (V1) includes: The first generator (G1) is configured to generate alternating current by extracting mechanical energy from one of the low-voltage shaft (BP) and the high-voltage shaft (HP). A first converter (C1) connected to the first generator (G1) is used to supply power to the power distribution unit (EDU). Power supply, wherein the first converter (C1) is configured to convert the generated alternating current into a first distribution current (I) according to its parameter settings. DC1 ), - The second power supply path (V2) includes: • The second generator (G2) is configured to generate alternating current by extracting mechanical energy from the other of the low-voltage shaft (BP) and the high-voltage shaft (HP). A second converter (C2), connected to the second generator (G2), is used to supply power to the power distribution unit (EDU). Power supply, the second converter (C2) is configured to convert the generated alternating current into a second distribution current (I) according to its parameter settings. DC2 ), - Control device (2), configured to receive the general operating setpoint (P) ECUG And output the first parameterized setting value (P) of the first converter (C1). CONS1 ) and the second parameterization setting value (P) of the second converter (C2) CONS2 ), - Each parameter setting (P) CONS1 P CONS2 ) is used to control the converters (C1, C2) under the distribution voltage (V) DC The voltage regulation setting (RegU) or the auxiliary regulation setting (RegA) for the turbine (T); - The control device (2) is configured to output a parameterized setting value with a stable delay (Ts) relative to the parameterized setting value of the voltage transition (TransU) for the auxiliary transition (TransA), such that the voltage regulation (RegU) is extended during the auxiliary transition (TransA), the auxiliary transition (TransA) being the transition period from the voltage regulation setting value (RegU) to the auxiliary regulation setting value (RegA), and the voltage regulation (RegU) being the transition period from the auxiliary regulation setting value (RegA) to the voltage regulation setting value (RegU).

2. The power generation system (1) as described in claim 1, characterized in that, The stable delay (Ts) is greater than 2ms.

3. The power generation system (1) as described in claim 1 or 2, characterized in that, The stable delay (Ts) is less than 45ms.

4. The power generation system (1) as described in any one of claims 1 to 3, characterized in that, The stable delay (Ts) is greater than the maximum parasitic delay, which is determined between the moment of transmission of the parameterized setpoint associated with the conversion and the effective switching moment of switching from one regulation mode to another.

5. The power generation system (1) as described in claim 4, characterized in that, The stable delay (Ts) is less than three times the maximum parasitic delay.

6. The power generation system (1) as described in claim 5, characterized in that, The stable delay (Ts) is approximately twice the maximum parasitic delay.

7. The power generation system (1) as described in any one of claims 1 to 6, characterized in that, The control device (2) includes an adjustment module (20) configured to calculate the distribution voltage (V). DC The measured value of ) and the distribution voltage setting value (V) DC The adjustment module (20) includes a gain parameter (Ki) that is proportional to the deviation (Δ) between the two (*).

8. An aircraft, characterized in that, The device includes at least one aircraft turbine (T) and at least one power generation system (1) as claimed in any one of claims 1 to 7, the aircraft turbine including a low-pressure shaft (BP) and a high-pressure shaft (HP) configured to be driven to rotate, the power generation system supplying power to at least one power grid (REA) of the aircraft.

9. A method for supplying power to at least one power grid (REA) of an aircraft via a power generation system (1) as described in any one of claims 1 to 7, characterized in that, The aircraft includes at least one aircraft turbine (T), the aircraft turbine including a low-pressure shaft (BP) and a high-pressure shaft (HP) configured to be driven to rotate, and the method includes the following steps: • Receive the general operating settings (P) that define the hybrid power strategy. ECUG ), • Based on the general operating settings (P) ECUG Output the first parameterized setting value (P) of the first converter (C1). CONS1 ) and the second parameterization setting value (P) of the second converter (C2) CONS2 ), • For the auxiliary conversion (TransA), the output has a parameterized setting with a stable delay (Ts) relative to the parameterized setting of the voltage conversion (TransU), such that the voltage regulation (RegU) is extended during the auxiliary conversion (TransA).

10. A computer program product, characterized in that, It includes at least one instruction sequence stored by a processor and readable by the processor, wherein when the instruction sequence is read by the processor, the steps of the method of claim 9 are performed.

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