Method for compensating the electrical power of a hybrid turbine engine

Abstract

The invention relates to a method (100) for compensating the electrical power of a hybrid turbine engine comprising an electrical network of a propulsion assembly connected to an external electrical network, which method comprises: o a step (101) of determining external electrical power; o a step of calculating the propulsion electrical power (102) during which additional power to be supplied to, or to be dissipated by, the electrical network of the propulsion assembly is calculated; o a step (103) of calculating compensation electrical power during which compensation electrical power needed to supply the electrical power required by the external electrical network during the transient state is calculated; and o a step (104) of drawing or injecting power during which the compensation electrical power is drawn or injected by an electrical compensation member so as to supply the electrical power required by the external electrical network.

Description

DESCRIPTION TITLE: Method for compensating the electrical power of a hybrid turbomachine FIELD OF THE INVENTION

[0001] The invention belongs to the field of turbomachines for aeronautics, and in particular to the field of hybrid turbomachines. The invention relates to a method for compensating the electrical power of a hybrid turbomachine. The invention also relates to a hybrid turbomachine implementing such an electrical power compensation method. Finally, the invention further relates to an aircraft implementing the method according to the invention. STATE OF THE ART

[0002] The hybridization of turbomachines today meets various needs, such as limiting the temperature of exhaust gases, distributing power draws between the different bodies of the turbomachine, adjusting the engine operating line during a transient engine regime or even optimizing stability.

[0003] A hybrid twin-spool / dual-flow turbomachine known to those skilled in the art comprises a high-pressure spool and a low-pressure spool, such that air flowing through the high-pressure spool forms a first flow and air flowing through the low-pressure spool forms a second flow.

[0004] The high-pressure body consists of a high-pressure compressor and a combustion chamber. The combustion chamber mixes air and fuel. After the air is burned, the gases are expanded in a high-pressure turbine.

[0005] The expansion of the gases continues in a low-pressure body comprising a low-pressure turbine and driving a fan, placed at the front of the turbomachine, and making it possible to obtain the necessary thrust.

[0006] The hybridization of such a double-body / double-flow turbomachine is achieved by connecting an electric machine to the high-pressure shaft, subsequently called the machine high-pressure electric, and a low-pressure shaft electric machine, subsequently called a low-pressure electric machine.

[0007] The high-pressure electric machine and the low-pressure electric machine are not connected to each other and several modes of use are possible. The high-pressure electric machine, respectively the low-pressure electric machine, can operate as a motor, by converting electrical energy into mechanical energy, or as a generator, by converting mechanical energy into electrical energy.

[0008] An electric machine working as a motor will inject power into one of the turbomachine's shafts. An electric machine working as a generator will draw power from one of the turbomachine's shafts, for example by applying resistive torque to one of the motor shafts.

[0009] An aircraft's electrical system requires electrical power to supply systems external to the turbomachine, such as the aircraft's electrical systems, the de-icing system, and / or the avionics. Such electrical power requirements are also referred to as "external requirements" and, from the engine's perspective, result in power being drawn from the turbomachine's shafts.

[0010] The management of such electrical power draws is well known in stabilized engine speed, namely when the engine power requirements, also called "engine needs", are constant over time and only the variations in external needs need to be compensated.

[0011] On the contrary, during a transient engine regime, such as acceleration or deceleration, more complex dynamics must be managed dynamically.

[0012] Dynamic compensation of external needs is particularly complex in a hybrid turbomachine which is only operable in certain engine speeds with electric assistance.

[0013] In other words, during acceleration, the high-pressure compressor is sized to exactly what is needed. At certain points, it will be limited by the fuel flow and the electric machine assists the engine to obtain the nominal acceleration, without putting more fuel than the imposed limits, to protect the machine from a thermodynamic and aerodynamic point of view.

[0014] In steady state, when the turbomachine receives a request for electrical power from the aircraft, the necessary electrical power is taken, in open loop, on the engine. The stabilized regulation, carried out only on the fuel flow, will simply adjust the engine speed to maintain the required thrust.

[0015] Concretely, when we take energy or put a resistive torque on a low-pressure shaft or a high-pressure shaft, we slow down the engine speed and a closed loop of speed maintenance compensates by increasing the fuel flow to maintain the engine speed and thrust.

[0016] On a hybrid turbomachine, when we move into transient mode, such as acceleration or deceleration, the torque requirement includes • an external need, reflecting the electrical power required by the aircraft, and • an internal need, reflecting the electrical assistance required by the engine to perform the transient regime.

[0017] In hybrid turbomachines known to those skilled in the art, during transient engine regimes, the internal needs of the engine are met by deviating from the constant electrical power required for the external needs of the aircraft.

[0018] In other words, there is currently no hybrid turbomachine that can compensate, in real time, the electrical power injected or taken by the engine during transient engine conditions, such as acceleration or deceleration. SUMMARY OF THE INVENTION

[0019] The invention offers a solution to at least some of the problems mentioned above thanks to a method of compensating a hybrid turbomachine allowing dynamic compensation of external injection and / or electrical power extraction needs, in particular during a transient engine regime, namely acceleration or deceleration.

[0020] To this end, a first aspect of the invention relates to a method for dynamically compensating the electrical power of a hybrid turbomachine, in particular a dual-spool / dual-flow hybrid turbomachine, the turbomachine comprising an electrical network of a propulsion unit connected to an external electrical network. More specifically, the compensation method comprises at least: - a step of determining external electrical power, during which an electrical power required by the external electrical network is determined; - a step of calculating the propulsion electrical power, during which, during a transient engine regime, additional power to be supplied or dissipated by the electrical network of the propulsion unit is calculated in order to ensure the operation of the engine during the transient regime; - a step of calculating the compensation electrical power, during which, in particular in real time, a compensation electrical power necessary to provide the electrical power required by the external electrical network during the transient regime is calculated, in particular, from the electrical power required by the external electrical network and the electrical power to be provided by the electrical network of the propulsion unit in order to ensure the operation of the engine during the transient, - a power sampling or injection step, during which the compensation electrical power is sampled or injected by an electrical compensation device, so as to provide the electrical power required by the external electrical network during the transient regime.

[0021] The term "turbomachine propulsion system" means a set of devices providing the engine's thrust.

[0022] The term "electrical system of the propulsion unit" means all the electrical machines connected to the propulsion unit. The electrical system of the propulsion unit includes at least one electrical compensation device.

[0023] For example, in a hybrid twin-spool / double-flow turbomachine, the electrical system of the propulsion unit includes a low-pressure electric machine and a high-pressure electric machine.

[0024] The term "external electrical system" refers to the aircraft's electrical network responsible for drawing or injecting electrical power. The external electrical network can also be called the interface electrical network.

[0025] The term "electrical compensation device" means an electrical system capable of injecting or drawing electrical power to compensate for external needs during a transient regime. The electrical device may be an electrical machine included in the electrical network of the propulsion system. Alternatively, the electrical device may be a battery, an auxiliary power unit or a power dissipation element included in the external electrical network.

[0026] The term "external electrical power extraction requirements" or "external electrical power injection requirements" refers to the electrical requirements of the external electrical network to which the hybrid turbomachine is connected. The external electrical network is, for example, the aircraft's electrical network and the external electrical requirements are the electrical requirements of the aircraft's electrical systems, such as the de-icing system, avionics or other electrical devices present in the aircraft.

[0027] Thanks to the compensation method according to the invention, it is possible to ensure constant electrical power on the external electrical network, particularly during transient conditions.

[0028] Unlike the control methods known to those skilled in the art, the compensation method according to the invention makes it possible to compensate in real time for the additional electrical power required during acceleration or deceleration of the engine speed.

[0029] The compensation method according to the invention therefore makes it possible not to deviate from external electrical power requirements during all phases of flight, including transient regimes.

[0030] In addition to the characteristics which have just been mentioned in the preceding paragraphs, the compensation method according to one aspect of the invention may have one or more additional characteristics among the following, considered individually or according to all technically possible combinations: - the electrical network of the propulsion unit comprises o a low-pressure electrical machine, connected to the low-pressure shaft of the hybrid turbomachine and / or o a high-pressure electrical machine, connected to the high-pressure shaft of the hybrid turbomachine - the step of determining the electrical power required by the external electrical network comprises a determination of the distribution of the electrical power required by the external electrical network among the low-pressure electrical machine and / or the high-pressure electrical machine; - the electrical compensation member used during the power sampling or injection step comprises at least one element chosen from an assembly comprising: o a low-pressure electrical machine, o a high-pressure electrical machine, o a battery, o an auxiliary power unit and / or o an electrical power dissipation element; - the step of calculating the compensation electrical power is carried out using a control loop having as input at least one variable chosen from a set comprising: o a low-pressure electric machine / external requirements pair, o a high-pressure electric machine / external requirements pair, o a low-pressure electric machine / transient regime requirements pair, o a high-pressure electric machine / transient regime requirements pair, o a high-pressure turbine regime, o a low-pressure turbine regime, and / or o a fan regime, - the control loop provides, at output, at least o a torque command to be applied to the low-pressure electric machine and / or o a torque command to be applied to the high-pressure electric machine. - the method further comprises a power conversion step, during which a conversion of the compensation power into compensation electric torque is carried out, the step of drawing off or injecting compensation electrical power comprises an application of the compensation electrical torque by the low-pressure electrical machine and / or by the high-pressure electrical machine; the compensation electrical torque is applied by the low-pressure electrical machine and calculated according to the following formula: where NH is the high-pressure turbine speed, Transient TRQHP is the electrical torque applied by the high-pressure electric machine during the engine transient and NFan is the fan speed of the hybrid turbomachine; - during the power sampling or injection stage, the compensation electrical power is supplied by the low-pressure electrical machine and by an additional compensation electrical device; - the electrical power supplied by the additional electrical compensation unit is calculated according to the following formula:

[0031] A second aspect of the invention relates to a hybridized turbomachine, in particular a dual-spool / dual-flow hybridized turbomachine, comprising the following elements: a propulsion assembly comprising o a fan, o a low-pressure shaft, o a high-pressure compressor, o a combustion chamber, o a high-pressure shaft, o a high-pressure turbine and o a low-pressure turbine; an electrical network of the propulsion assembly comprising o a low-pressure electrical machine, connected to the low-pressure shaft and o a high-pressure electrical machine, connected to the high-pressure shaft, the electrical system of the propulsion unit being connected to an external electrical network; an electrical compensation member and calculation means configured for implementing the compensation method according to the first aspect of the invention.

[0032] The hybridized turbomachine, in particular the dual-spool / dual-flow hybridized turbomachine, according to one aspect of the invention may have one or more complementary characteristics among the following, considered individually or according to all technically possible combinations: - the turbomachine according to the invention comprises an additional electrical compensation member; - the electrical compensation member and the additional electrical compensation member are chosen from an assembly comprising: o a low-pressure electrical machine, o a high-pressure electrical machine, o a battery, o an auxiliary power unit and / or o an electrical power dissipation element.

[0033] A third aspect of the invention relates to an aircraft comprising - a hybridized turbomachine according to the second aspect of the invention, and / or - an electrical compensation member and calculation means for implementing the compensation method according to the first aspect of the invention. BRIEF DESCRIPTION OF THE FIGURES

[0034] The figures are presented for information purposes only and in no way limit the invention.

[0035] [Figure 1] is a schematic representation of a compensation method according to the invention;

[0036] [Figure 2] illustrates a schematic representation of an arrangement of an electrical network of a propulsion unit and an external electrical network;

[0037] [Figure 3] schematically illustrates an example of dynamic electrical power compensation according to the invention;

[0038] [Figure 4] illustrates an example of a hybridized transient maneuver;

[0039] [Figure 5] illustrates an example of a hybridized transient operation in the absence of compensation according to the invention;

[0040] [Figure 6] illustrates an example of a hybridized transient maneuver with dynamic compensation according to the invention; and

[0041] [Figure 7] shows a schematic representation of a hybridized turbomachine according to the invention. DETAILED DESCRIPTION

[0042] Unless otherwise specified, the same element appearing in different figures has a single reference.

[0043] Figure 1 schematically illustrates an embodiment of the compensation method 100 according to the invention.

[0044] The compensation method 100 comprises a step of determining external electrical power 101, during which an electrical power required by an external electrical network is determined. The determination step 101 makes it possible to determine the electrical power required by the external electrical network. In other words, the external electrical power represents the external needs to be ensured during operation of the turbomachine, including during transient engine conditions.

[0045] According to one embodiment of the compensation method 100 according to the invention, an electrical network of a propulsion assembly comprises a low-pressure electrical machine connected to the low-pressure shaft of the hybridized turbomachine and a high-pressure electrical machine connected to the high-pressure shaft of the hybridized turbomachine.

[0046] The step of determining the external electrical power 101 required by the external electrical network further comprises a determination of a distribution of the electrical power required by the external electrical network between the low-pressure electrical machine and / or the high-pressure electrical machine.

[0047] The compensation method 100 further comprises a step of calculating the propulsion electrical power 102, during which an electrical power to be supplied by the electrical network of the propulsion unit is determined in order to ensure operation of the engine during a transient engine regime. The step of calculating the propulsion electrical power 102 is carried out during a transient regime. engine, so as to determine additional power to be supplied or dissipated during the transient engine regime. The transient engine regime may include, for example, an acceleration or deceleration of the engine speed.

[0048] The compensation method 100 further comprises a step of calculating compensation electrical power 103, during which, in particular in real time, a compensation electrical power necessary to provide the electrical power required by the external electrical network during the transient engine regime is calculated.

[0049] The calculation of the compensation electrical power is carried out from the electrical power required by the external electrical network and the electrical power to be supplied by the electrical network of the propulsion unit in order to ensure the operation of the engine during the transient engine regime. In other words, the compensation electrical power is sized to balance the transient engine requirements so as not to deviate from the external requirements.

[0050] The compensation method 100 further comprises a power sampling or injection step 104, during which the compensation electrical power is then sampled or injected, so as to provide the electrical power required by the external electrical network during the transient engine regime. The compensation electrical power is, for example, supplied and / or stored by an electrical compensation member.

[0051] The compensation electrical power can be taken from or injected into the propulsion unit depending on the type of transient engine regime achieved.

[0052] For example, during engine acceleration, the additional electrical power required by the propulsion unit must be compensated by a power draw performed by the electrical compensation member. Alternatively, during engine deceleration, the excess electrical power must be stored by the electrical compensation member, so as not to be rejected to the external electrical network. According to one embodiment, the compensation method 100 further comprises a power conversion step 104a, during which a conversion of the compensation power into compensation electrical torque is performed. In this case, the power draw or injection step 104 comprises an application of the compensation electrical torque by a low-pressure electrical machine and / or by a high-pressure electrical machine of the hybridized turbomachine, in particular the turbomachine hybridized double body / double flux. In the event of power extraction, the applied torque is a resistive torque.

[0053] According to one embodiment of the compensation method 100, the electrical compensation member used during the power sampling or injection step 104 comprises at least one element chosen from an assembly comprising a low-pressure electrical machine, a high-pressure electrical machine, a battery, an auxiliary power unit and / or an electrical power dissipation element.

[0054] The electrical compensation device can therefore be included in the electrical network of the propulsion unit or in the external electrical network.

[0055] The compensation method 100 therefore makes it possible to dynamically compensate the engine's electrical power requirements during a transient regime, so as to ensure external electrical requirements, for example the electrical requirements of the aircraft. In other words, the compensation method 100 allows regulation of the regimes using a hybridized control of fuel flow and electric torque in a closed loop, so as to ensure the acceleration and deceleration performances of the turbomachine with constrained operability limits.

[0056] Figure 2 illustrates a schematic representation of an arrangement of the electrical network of the propulsion unit and the external electrical network. Figure 2 shows how the compensation method 100 according to the invention makes it possible to have the electrical power supplied by the electrical network of the propulsion unit always equal to the electrical power requested by the external electrical network or interface network.

[0057] According to the example in Figure 2, the electrical network of the propulsion unit comprises a low-pressure MEL BP electrical machine and a high-pressure MEL HP electrical machine. In such a case, the electrical power supplied by the propulsion unit is the sum of the electrical powers supplied by the low-pressure MEL BP electrical machine and the high-pressure MEL HP electrical machine. The electrical power required by the external electrical network is the product of the aircraft requirements, which may vary over time, and the architecture of an interface electrical network.

[0058] The interface electrical network therefore draws energy from the propulsion system to satisfy an electrical load of the aircraft, i.e. the electrical power required by the external electrical network. The interface electrical network interface may also include an electrical power dissipation element to eliminate excess electrical power if Pmotor > Pdemanded.

[0059] The external electrical network may include electrical storage elements that store electrical power, such as a battery or an auxiliary power unit. Such electrical storage elements act as electrical compensation devices and can store the surplus electrical power produced by the propulsion system, for example during a transient engine speed during deceleration.

[0060] Figure 3 schematically illustrates an example of dynamic compensation of electrical power according to the invention with transfer of power from the high-pressure body to the low-pressure body of a hybridized double-body / double-flow turbomachine.

[0061] In particular, Figure 3 illustrates an embodiment of the step of calculating the compensation electrical power 103. In this case, the step of calculating the compensation electrical power 103 is carried out using a regulation loop 300 having, - as input, at least one variable chosen from a set comprising: o a high-pressure electric machine-external requirements pair 301, in particular in open loop, o a low-pressure electric machine / external requirements pair 302, in particular in open loop, o a high-pressure electric machine / engine transient regime requirements pair 303, in particular in closed loop, o a low-pressure electric machine-engine transient regime requirements pair 304, in particular in closed loop, o a high-pressure turbine regime 305, o a low-pressure turbine regime 306, and / or o a fan regime; - at the output, at least o one torque command to be applied to the high-pressure electric machine 307, and / or o one torque command to be applied to the low-pressure electric machine 308.

[0062] Advantageously, the power sampling or injection step 104 according to the embodiment of FIG. 3 allows dynamic compensation of the aircraft's external needs by transferring electrical power from the high-pressure body to the low-pressure body.

[0063] For this purpose, according to an exemplary embodiment, the control loop 300 provides: - on the one hand, a summation of the high-pressure electric machine-external requirements torque 301 and the high-pressure electric machine-engine transient regime requirements torque 303, - on the other hand, a summation of the low-pressure electric machine torque - external requirements 302 and low-pressure electric machine torque - transient engine regime requirements 304, - furthermore, a calculation of compensation electrical power from the high-pressure turbine speed 305, the low-pressure turbine speed 306 and the high-pressure electrical machine torque - transient engine speed requirements 303, and, - a summation of the compensation electrical power and a resultant of the summation of the high-pressure electric machine-external requirements torque 301 and the high-pressure electric machine-engine transient regime requirements torque 303.

[0064] The summation of the high-pressure electric machine-external requirements torque 301 and the high-pressure electric machine-engine transient requirements torque 303 makes it possible to provide the torque command to be applied to the high-pressure electric machine 307.

[0065] The summation of the compensation electrical power and the resultant of the summation of the high-pressure electric machine-external requirements torque 301 and the high-pressure electric machine-engine transient requirements torque 303 makes it possible to provide the torque command to be applied to the low-pressure electric machine 308, thus compensated.

[0066] According to one embodiment, the compensation electrical torque calculated during the power conversion step 104a of the compensation method 100 according to the invention is applied by the low-pressure electrical machine and calculated according to the following formula: where NH is the high-pressure turbine speed, Transient TRQHP is the electrical torque applied by the high-pressure electric machine during the engine transient regime and NFan is the fan speed of the hybrid turbomachine.

[0067] The implementation of such dynamic compensation then makes it possible to meet the needs of the high-pressure compressor in a closed loop without degrading power supply for open-loop needs, namely electrical power needs external to the engine, such as the power needs requested by the aircraft, or draws, on transient regimes.

[0068] Compensation can be achieved up to the design and protection limits of the electric machine and the turbomachine. Beyond this, compensation can no longer be achieved because the total power on the low-pressure body will be at the electric machine or turbomachine protection limit. It will then be necessary: - either it is acceptable for the electricity network, in particular by a loss of part of the power or dissipation of excess power, - either it is compensated by a third-party device, such as a battery or an auxiliary power device.

[0069] Such a solution is also applicable in the case where one wishes to compensate for a reduction in power of the low-pressure body using the high-pressure electric machine.

[0070] The solution provides a general principle to enable the extraction of information from the power reduced by regulation in a hybridized transient regime. It can therefore be reused for compensation using any other device that would allow such power to be compensated.

[0071] Another embodiment is to rely on an external device to provide part of the compensation, whether in supply or dissipation, of the power difference during transient conditions.

[0072] An advantage of this embodiment is that it overcomes the limitations of the turbomachine. However, it may require integrating an additional component into the architecture of the propulsion system's electrical network.

[0073] The additional body will have to allow: - the supply of deficit power, for example with a charged battery or an auxiliary power unit; - excess power consumption, for example with a discharged battery or a dissipation device in the event of a fully charged battery or no battery.

[0074] The compensation will then be formulated as follows: NH. TRQ HP transitoire TRQBP compensation NFan

[0075] We will then obtain the saturated torque to be applied to the low-pressure shaft:

[0076] Note that the TRQ quantities BPn , nx and TRQ BP. , corresponding respectively to the maximum and minimum torques of the low-pressure shaft, can be chosen to include different protections. For example, they can take into account the minimum and maximum torques achievable by the electric machine at a given speed, the minimum and maximum torques authorized to limit the impact on the thrust...

[0077] We then have a power PA / C requested by the external electrical network defined according to the following formula:

[0078] According to this embodiment of the power sampling or injection step 104 of the compensation method 100 according to the invention, the compensation electrical power is supplied by the low-pressure electrical machine MEL BP and by an additional compensation electrical member.

[0079] In this case, the electrical power supplied by the additional electrical component is calculated according to the following formula: [ L 0081] J It should be noted that P o c / r / yaa U no additional supplement is zero, if the move 1 the electric machine 1 low-pressure MEL BP is not saturated, namely that TR Q B P max > TRQBP > TRQ BPmin .

[0082] Figure 4 illustrates an example of a hybridized transient maneuver. Thus, Figure 4 shows the variation over time of the control parameters of a hybridized turbomachine.

[0083] Figure 4 shows more particularly inserts 400 highlighting the transient engine regimes during which a regime of the high-pressure body 401 varies to carry out accelerations or decelerations.

[0084] Figure 4 presents more precisely - the high-pressure body regime 401; - the high speed limit of the high-pressure body 402; - the low speed limit of the high-pressure body 403; - the torque control of the high-pressure electric machine 404; - the external torque requirement taken from the high-pressure body 405; and - the torque control of the low-pressure electric machine 406;

[0085] Figure 5 illustrates an example of a hybridized transient operation in the absence of compensation according to the invention.

[0086] Figure 5 shows more specifically 500 inserts highlighting the transient engine regimes.

[0087] Figure 5 shows more precisely: - the need for electrical power 501, to be supplied to the aircraft; - the total electrical power 502, supplied by the high-pressure electric machine MEL HP and the low-pressure electric machine MEL BP; - the power supplied by the high-pressure electric machine 503; and - the power supplied by the low-pressure electric machine 504. for a hybridized turbomachine without dynamic power compensation according to the invention. The inserts 500 highlight the transient engine speeds.

[0088] Figure 5 shows that in correspondence with a transient engine regime, the total power 502 supplied by the high-pressure electric machine MEL HP and the low-pressure electric machine MEL BP deviates from the electrical power requirement 501.

[0089] In other words, we can see that the total power 502 supplied or consumed by the high-pressure electric machine MEL HP and the low-pressure electric machine MEL BP does not match the electrical power requirement 501 to be supplied to the aircraft outside of stabilized regimes, due to the extraction of energy required for the operability needs of the high-pressure compressor of the turbomachine.

[0090] The necessary compensation cannot be calculated in advance by static laws derived from operability since, by nature, the need is processed in a closed loop. An adaptation to the power demand is made in relation to: - the dynamics of the transient regime of the high-pressure body and - a position of the operating line of the regulated motor relative to an operability stop.

[0091] This shows the need for a compensation method 100 such as that of the invention to ensure external electrical needs during transient engine conditions.

[0092] Figure 6 illustrates an example of a hybridized transient mode maneuver with compensation according to the invention.

[0093] Figure 6 shows more specifically 600 inserts highlighting the transient engine regimes.

[0094] Figure 6 shows more precisely - the need for electrical power 601, to be supplied to the aircraft; - the total power 602, supplied by the high-pressure electric machine MEL HP and the low-pressure electric machine MEL BP; - the power supplied by the high-pressure electric machine 603; and - the power supplied by the low-pressure electric machine 604 for a hybrid turbomachine with dynamic power compensation according to the invention.

[0095] It is obvious that in the event of implementation of the compensation method 100 according to the invention, the curves of electrical power requirement 601 and total power 602 are always identical, which demonstrates that the external requirements are always met, including during transient engine conditions.

[0096] Figure 7 illustrates a schematic representation of a hybrid turbomachine 700, of the double-body / double-flow type according to the example presented, implementing the compensation method 100 according to the invention. The hybrid turbomachine 700 comprises a propulsion assembly comprising a fan 701, a low-pressure shaft, a high-pressure compressor 703, a combustion chamber 704, a high-pressure shaft, a high-pressure turbine 705 and a low-pressure turbine 706.

[0097] The hybrid turbomachine 700 further comprises an electrical network of the propulsion assembly comprising a low-pressure electrical machine 707 connected to the low-pressure shaft and a high-pressure electrical machine 708, connected to the high-pressure shaft.

[0098] In addition, the propulsion system's electrical network is connected to an external electrical network.

[0099] Furthermore, the hybrid turbomachine 700 may comprise a reducer 702, in particular arranged between the fan 701 and the high-pressure compressor 703.

[0100] The hybridized turbomachine 700 comprises an electrical compensation member and calculation means configured for implementing the compensation method 100 according to the invention.

[0101] The hybridized turbomachine 700 according to the invention can, thanks to the implementation of the compensation method 100 according to the invention, dynamically compensate for external electrical needs, ensuring the electrical power necessary for the external electrical network even during transient engine speeds.

[0102] According to one embodiment, the hybridized turbomachine 700 according to the invention comprises an additional electrical compensation member.

[0103] According to another embodiment, the hybridized turbomachine 700 according to the electrical compensation member and the additional electrical compensation member are chosen from an assembly comprising a low-pressure electrical machine, a high-pressure electrical machine, a battery, an auxiliary power group and / or an electrical power dissipation element.

Claims

CLAIMS

1. Method for compensating (100) dynamically compensating the electrical power of a hybrid twin-body / double-flow turbomachine, the turbomachine comprising an electrical network of a propulsion unit connected to an external electrical network, the electrical network of the propulsion unit comprising: - a low-pressure electric machine, connected to a low-pressure shaft of the hybrid turbomachine, included in the low-pressure body of the hybrid turbomachine and / or - a high-pressure electric machine, connected to a high-pressure shaft of the hybrid turbomachine, included in the high-pressure body of the hybrid turbomachine, the method comprising at least: - a high-pressure electric machine, connected to a high-pressure shaft of the hybrid turbomachine, included in the high-pressure body of the hybrid turbomachine, - a step of determining external electrical power (101), during which an electrical power required by the external electrical network is determined; - a step of calculating the propulsive electrical power (102), during which, during a transient engine regime, an additional power to be supplied or dissipated by the electrical network of the propulsion unit is calculated in order to ensure the operation of the engine during the transient regime; - a step of calculating the compensation electrical power (103), during which, in particular in real time, a compensation electrical power necessary to provide the electrical power required by the external electrical network during the transient regime is calculated, in particular, from the electrical power required by the external electrical network and the electrical power to be provided by the external electrical network the propulsion system in order to ensure the operation of the engine during the transient regime, and - a power sampling or injection step (104), during which the compensation electrical power (104) is sampled or injected by an electrical compensation device, so as to provide the electrical power required by the external electrical network during the transient regime, - a power conversion step (104a), during which a conversion of the compensation electric power into compensation electric torque is carried out, the compensation electric torque being applied by the low-pressure electric machine by transferring electric power from the high-pressure body to the low-pressure body.

2. Compensation method (100) according to the preceding claim, characterized in that the electrical compensation member further comprises an element chosen from a set comprising: - a battery, - an auxiliary power unit and / or - an electrical power dissipation element.

3. Compensation method (100) according to the preceding claim, characterized in that the step of determining the electrical power required by the external electrical network (101) comprises a determination of the distribution of the electrical power required by the external electrical network among the low-pressure electrical machine and / or the high-pressure electrical machine.

4. Compensation method (100) according to claim 2 or 3, characterized in that the step of calculating the compensation electrical power (103) is carried out using a regulation loop (300) having as input at least one variable chosen from a set comprising: - a high-pressure electric machine / external needs pair (301), - a low-pressure electric machine / external needs pair (302), - a high-pressure electric machine / transient engine regime requirements couple (303), - a low-pressure electric machine / transient engine regime requirements pair (304), - a high-pressure turbine regime (305), - a low-pressure turbine regime (306), and / or - a blowing diet.

5. Compensation method (100) according to the preceding claim, characterized in that the regulation loop (300) provides at least as output, - a torque command to be applied to the high-pressure electric machine (307) and / or - a torque command to be applied to the low-pressure electric machine (308).

6. Compensation method (100) according to one of the preceding claims, characterized in that the compensation electrical torque is calculated according to the following formula: Or : • NH is the high-pressure turbine speed, • TRQ HP transient is the electrical torque applied by the high-pressure electric machine during the engine transient regime and • NFan is the fan speed of the hybrid turbomachine.

7. Compensation method (100) according to any one of claims 3 to 5, characterized in that, during the step of sampling or injecting power (104), the compensation electrical power is supplied by the low-pressure electrical machine and by an additional compensation electrical member.

8. Compensation method (100) according to the preceding claim, characterized in that the electrical power supplied by the additional electrical component is calculated according to the following formula:

9. Hybridized turbomachine (700), in particular a dual-spool / dual-flow hybridized turbomachine (700), comprising: - a propulsion unit comprising: o a fan (701), o a low-pressure shaft, o a high-pressure compressor (703), o a combustion chamber (704), o a high-pressure shaft, o a high-pressure turbine (705) and o a low-pressure turbine (706); - an electrical network of the propulsion unit comprising o a low-pressure electrical machine (707), connected to the low-pressure shaft, and o a high-pressure electrical machine (708), connected to the high-pressure shaft, the electrical network of the propulsion unit being connected to an external electrical network; and - an electrical compensation member and calculation means configured for implementing the compensation method (100) according to any one of the preceding claims.

10. Hybridized turbomachine (700) according to the preceding claim, characterized in that it comprises an additional electrical compensation member.

11. Hybridized turbomachine (700) according to claim 9 or 10, characterized in that the electrical compensation member and the additional electrical compensation member are chosen from a set comprising: - a low-pressure electric machine, - a high-pressure electric machine, - a battery, - an auxiliary power unit and / or - an electrical power dissipation element.

12. Aircraft comprising - a hybridized turbomachine (700) according to any one of claims 9 to 11, and / or - an electrical compensation member and calculation means for implementing the compensation method according to any one of claims 1 to 8.

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