Method for controlling a turbine engine of an aircraft

Abstract

The invention relates to a method for controlling a turbine engine of an aircraft, the turbine engine being provided with a high-pressure system and a low-pressure system, the method comprising the steps of extracting a portion of the power produced by the turbine engine to power one or more devices of the aircraft according to a power extraction law, the power extraction law providing that the portion of the power produced by the turbine engine is to be extracted at the high-pressure system and / or is to be extracted at the low-pressure system, the method further comprising the step of monitoring the high-pressure system and / or the low-pressure system. The invention also relates to a system for implementing such a method. The invention also relates to an aircraft comprising such a system.

Description

[0001] This invention relates to a method for controlling a turbine engine of an aircraft.

[0002] The present invention also relates to a system for performing this method and an aircraft equipped with such a system. Background Technology

[0003] Climate change is a major concern for many legislative and regulatory bodies worldwide. Indeed, various countries have already adopted, are adopting, or will adopt carbon emission limits. In particular, an ambitious standard applies to both new and currently in-service aircraft, requiring the implementation of technological solutions to bring them into compliance with existing regulations. Civil aviation has been mobilizing for years to contribute to addressing climate change.

[0004] Technological research has led to significant improvements in the environmental performance of aircraft. The applicant has considered factors influencing all stages of design and development to obtain more energy-efficient and environmentally friendly aerospace components and products, whose integration and use in civil aviation have a moderate environmental impact, with the aim of improving the energy efficiency of aircraft.

[0005] Therefore, the applicant continuously strives to reduce its climate impact by using benign development and manufacturing methods and processes that minimize greenhouse gas emissions as much as possible to reduce the environmental footprint of its activities.

[0006] These ongoing research and development efforts target next-generation aircraft engines, aircraft weight reduction (particularly through the use of materials and lighter avionics), the development of electric propulsion technologies, and aviation biofuels as an important complement to technological advancements.

[0007] An aircraft turbine engine typically comprises, from upstream to downstream (in the direction of airflow through the turbine engine): a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, a low-pressure turbine, and an exhaust nozzle. The low-pressure compressor, high-pressure compressor, high-pressure turbine, and low-pressure turbine each include a rotor rotating within a casing connected to each other and to the combustion chamber and nozzle, forming a tubular assembly defining an annular main gas flow space. The rotor of the high-pressure turbine is rotatably connected to the rotor of the high-pressure compressor to drive the latter's rotation, and the rotor of the low-pressure turbine is rotatably connected to the rotor of the low-pressure compressor to drive the latter's rotation. The assembly including the high-pressure turbine and high-pressure compressor is called the high-pressure system, and the assembly including the low-pressure turbine and low-pressure compressor is called the low-pressure system.

[0008] With the increasing integration of electrical components within aircraft, it has been proposed to provide at least one electrical interface between the turbine engine and one or more electrical grids of the aircraft.

[0009] This electrical interface is therefore used to perform one or more functions, such as assisting the turbine engine during startup, or extracting a portion of the power generated by the turbine engine to power one or more devices on the aircraft (most of the power generated by the turbine engine is naturally used for the propulsion of the aircraft).

[0010] For this purpose, the electrical interface follows a predetermined extraction law that specifies that a portion of the power generated by the turbine engine is extracted from the high-pressure system and / or from the low-pressure system.

[0011] While extremely useful, this extraction could impose strict limitations on turbine engines.

[0012] In fact, turbine engines are already sensitive to the phenomenon of "surge," which, it's important to note, corresponds to aerodynamic stall caused by an excessive pressure differential between the low-pressure and high-pressure systems. Furthermore, this extraction increases the temperature of the expanding gas in the turbine. However, extraction often amplifies these phenomena, especially in cases of sudden and / or large-scale extraction in response to the demands of one or more devices.

[0013] Furthermore, once a turbocharged engine enters a degraded state with surge, it is difficult for it to escape this state.

[0014] Purpose of the invention

[0015] The present invention aims to overcome at least partially the above-mentioned disadvantages. Summary of the Invention

[0016] Therefore, the present invention provides a method for controlling a turbine engine of an aircraft, the turbine engine having a high-pressure system and a low-pressure system, the method comprising the steps of: extracting a portion of the power generated by the turbine engine according to an extraction law to supply power to one or more devices of the aircraft, the extraction law specifying that the portion of the power generated by the turbine engine is extracted from the high-pressure system and / or from the low-pressure system, the method further comprising: The following steps are used to monitor this high-voltage system: - Measure at least one characteristic data related to the high-voltage system. -- The operating point of the high-voltage system is determined based on this measurement. as well as The following steps are used to monitor this low-pressure system: - Measure at least one characteristic data point related to the low-pressure system. - The operating point of the low-voltage system is determined based on this measurement. The method also includes the following steps: - If the operating point of the high-voltage system is outside the safe operating area of ​​the high-voltage system, and the operating point of the low-voltage system is within the safe operating area of ​​the low-voltage system, then the extraction law is modified to facilitate extraction from the low-voltage system. The safe operating area of ​​the high-voltage system is defined based on at least one data point of the surge line of the high-voltage system, and the safe operating area of ​​the low-voltage system is defined based on at least one data point of the surge line of the low-voltage system. - and / or if the operating point of the low-voltage system is outside the safe operating area of ​​the low-voltage system and the operating point of the high-voltage system is inside the safe operating area of ​​the high-voltage system, then the extraction law is modified to facilitate extraction at the high-voltage system, wherein the safe operating area of ​​the low-voltage system is defined based on at least one data point of the surge line of the low-voltage system.

[0017] Therefore, the present invention manages extraction from a turbine engine by acting on an extraction law to increase extraction from either a high-pressure system or a low-pressure system.

[0018] This allows high-pressure or low-pressure systems to more easily return to their safe operating area, and / or prevents them from leaving their safe operating area and / or moving too far from it. Therefore, this invention is the result of technical research aimed at significantly improving aircraft performance and, in this respect, contributing to reducing the environmental impact of aircraft.

[0019] Optionally, if the operating point of the high-voltage system is outside the safe operating area of ​​the high-voltage system, the extraction law remains unchanged; or if the operating point of the low-voltage system is outside the safe operating area of ​​the high-voltage system, the extraction law remains unchanged.

[0020] Optionally, if the operating point remains outside the safe operating zone despite the modification of the extraction law, then at least one of the devices powered by the portion of the power extracted from the turbine engine is unloaded.

[0021] Optionally, the device is classified into at least two different priority categories, with the device belonging to the lower priority category being the one that is given priority for load shedding.

[0022] Optionally, the method includes at least one energy storage component associated with the turbine engine.

[0023] Alternatively, if the operating point remains outside the safe operating area despite the modification of the extraction law, the energy storage component is used to participate in supplying power to at least one of the devices.

[0024] Optionally, if at least one of the operating points of the high-voltage system or the low-voltage system remains outside the safe operating area despite the use of the energy storage component, then at least one of the devices powered by the portion of the power extracted from the turbine engine is unloaded.

[0025] Optionally, when the energy storage component is invoked, the extraction law can be modified to reduce the load on at least one of the high-voltage system and the low-voltage system, without increasing the load on the other system.

[0026] The present invention also relates to a management system for performing the methods described above.

[0027] The present invention also relates to an aircraft comprising at least one management system as described above.

[0028] Other features and advantages of the invention will become apparent when reading the following description of specific, non-limiting embodiments of the invention.

[0029] Brief description of the attached figures

[0030] The invention will be better understood through the following illustrative and non-limiting description, with reference to the accompanying drawings, in which: [ Figure 1 ] Figure 1 This is a schematic diagram of a system for performing a method for controlling a turbine engine of an aircraft according to a first specific embodiment of the present invention; [ Figure 2 ] Figure 2 It is shown in Figure 1 A flowchart showing the sequence of steps executed by the methods in the system shown. [ Figure 3 ] Figure 3 This is a schematic diagram of a system for performing a method for controlling a turbine engine of an aircraft according to a second embodiment of the present invention; [ Figure 4 ] Figure 4 It is shown in Figure 3 The flowchart shows the sequence of steps executed by the method in the system shown.

[0031] Specific embodiments of the present invention

[0032] refer to Figure 1 and Figure 2 Hereinafter, the electrical management system 10 according to the first embodiment of the present invention will be described with reference to the twin-ducted turbine engine 1 of aircraft A.

[0033] The turbine engine 1 includes, from upstream to downstream, the following components in the direction of airflow through the turbine engine 1: a fan 2, a low-pressure compressor 3, a high-pressure compressor 4, a combustion chamber 5, a high-pressure turbine 6, and a low-pressure turbine 7. Each of the low-pressure compressor 3, high-pressure compressor 4, high-pressure turbine 6, and low-pressure turbine 7 includes a rotor rotatably mounted in a casing.

[0034] The rotors of the high-pressure turbine 6 and the low-pressure turbine 7 are rotatably coupled to the rotors of the high-pressure compressor 4 and the low-pressure compressor 3, respectively, so that the rotors of the high-pressure turbine 6 and the low-pressure turbine 7 drive the rotors of the high-pressure compressor 4 and the low-pressure compressor 3 to rotate around the longitudinal axis X of the turbine engine 1 by the thrust of the gas from the combustion chamber 5.

[0035] The air mass drawn in by fan 2 is divided into two airflows: the main flow F1 flowing in the main flow annular channel C1, and the secondary flow F2 flowing concentrically with the main flow F1 in the secondary flow annular channel C2.

[0036] The turbine engine 1 also includes an intermediate casing, which, as is known per se, refers to a casing with a hub arranged between the casing of the upstream low-pressure compressor 3 and the casing of the downstream high-pressure compressor 4.

[0037] The assembly including the low-pressure turbine and the low-pressure compressor 3 is referred to below as the "high-pressure system", and the assembly including the high-pressure turbine and the high-pressure compressor 4 is referred to below as the "low-pressure system".

[0038] The general layout of the turbine engine described is conventional and will not be described in further detail here.

[0039] The management system 10 includes at least one master controller 11 associated with the turbine engine 1.

[0040] The management system 10 also includes a busbar 12, such as a DC busbar 12. The busbar 12 is controlled by the main controller 11.

[0041] One or more devices of aircraft 1 that are to be powered by busbar 12 are connected to busbar 12. These devices may be: - Directly connected to the busbar (e.g.) Figure 1 (The device marked as 13 in the middle). - Indirect connection via electrical and / or electronic components (e.g., electronic power converters) Figure 1 (The device marked as 14 in the middle). - Indirectly connected via multiple electrical and / or electronic components, such as a power converter, with an additional busbar connected to the power converter, and the device (e.g. Figure 1 The device marked 15 is itself connected to this additional busbar.

[0042] Preferably, and as will be detailed below, the main controller 11 controls one or more of the electrical and / or electronic components so as to be able to temporarily interrupt the power supply to one or more devices via the busbar 12.

[0043] Alternatively, an external power supply (not shown here) may also be connected to busbar 12.

[0044] Optionally, busbar 12 can also transmit data to the main controller 11.

[0045] Furthermore, the management system 10 includes at least one high-pressure system controller 16 and one low-pressure system controller 17. The main controller 11 controls the low-pressure system controller 17 and the high-pressure system controller 16. The main controller 11 controls the low-pressure system controller 17 and the high-pressure system controller 16, in particular, based on at least one characteristic data of the turbine engine 1 and / or at least one characteristic data of the busbar 12 (and thus the equipment connected thereto).

[0046] The low-pressure system controller 17 is associated with a first electrical interface 18 of the management system 10, which is configured to extract at least a portion of the electrical power generated by the turbine engine 1 at the low-pressure system. The first interface 18 is controlled in particular by the low-pressure system controller 17, and in return, at least one characteristic information of the first interface 18 is transmitted to the low-pressure system controller 17.

[0047] The first interface 18 includes: - An electric motor 19 is connected to the low-pressure system of the turbine engine 1, and is, for example, a permanent magnet synchronous motor. The electronic power converter 20 is connected to the motor 19 on one side and to the busbar 12 on the other.

[0048] For example, the first interface 18 is controlled by the low-voltage system controller 17 via its electronic power converter 20.

[0049] Similarly, the high-voltage system controller 16 is associated with a second electrical interface 21 of the management system 10, which is configured to extract a portion of the electrical power generated by the turbine engine 1 from the high-voltage system. The second interface 21 is controlled, in particular, by the high-voltage system controller, and in return, at least one characteristic information of the second interface 21 is transmitted to the high-voltage system controller.

[0050] The second interface 21 includes: The motor 22 is connected to the low-pressure system of the turbine engine 1, and is, for example, a permanent magnet synchronous motor. The electronic power converter 23 is connected to the motor 22 on one side and to the busbar 12 on the other.

[0051] For example, the second interface 21 is controlled by the high-voltage system controller 16 via its electronic power converter 23.

[0052] Optionally, busbar 12 can transmit data to the low-voltage system controller and / or the high-voltage system controller.

[0053] In operation, the main controller 11 controls the high-voltage system controller 16 and the low-voltage system controller 17 according to an extraction law that stipulates that a portion of the power generated by the turbine engine 1 is extracted from the high-voltage system and / or from the low-voltage system. The high-voltage system controller 16 and the low-voltage system controller 17 thus extract the power required by the main controller 11 to supply power to the busbar 12.

[0054] Therefore, it will be noted that bus 12 is powered by the first interface 18 and the second interface 21 connected in parallel to a channel of bus 12. The channel is therefore a DC channel.

[0055] refer to Figure 2 According to the first option, the management system 10 is configured to prioritize monitoring the high-voltage system.

[0056] Subsequently, the various modules described belong to the management system 10, and for example to the main controller 11 and / or the high-voltage system controller 16.

[0057] In the initial step 100, performed in the determination module, the safe operating area of ​​the high-voltage system is determined based on at least one data point of the surge line of the high-voltage system.

[0058] The data regarding surge lines is provided by the manufacturer and is therefore known.

[0059] The safe operating area is defined as being far from the surge line. This defines a zone in which the high-voltage system can operate without surge phenomena impairing its performance.

[0060] According to the first step 101, performed in the first measurement module, at least one characteristic data related to the high-voltage system is measured.

[0061] For example, characteristic data include: pressure in the high-pressure system, temperature in the high-pressure system, rotational speed in the high-pressure system, and fuel flow rate consumed by the high-pressure system.

[0062] According to step 102, executed in the second calculation module, at least one operating point of the high-pressure system is determined based on measurements. It should be noted that the operating point corresponds to the ratio between the mass flow rate (of air passing through the high-pressure system) and the compression ratio of the high-pressure system. The calculation of the operating point can be based on at least one table, at least one simplified model, at least one inverse model, at least one integrated thermodynamic model, etc.

[0063] According to step 103, performed in the third calculation module, it is determined whether the operating point is outside the safe operating area of ​​the high-voltage system. Therefore, it should be understood that the safe operating area is thus defined by a set of mass flow rate to compression ratio ratios, and the operating point is preferably kept within the operating area.

[0064] Therefore, during step 104, the fourth calculation module is executed, and decisions are made according to the following decision order based on the location of the working point.

[0065] First Decision 105

[0066] If the operating point is within the safe operating area, the operating law remains unchanged. Therefore, it should be understood that the fourth calculation module communicates with the main controller 11 to indicate that the law remains unchanged. During the first phase 106, the main controller 11 transmits control commands to the high-voltage system controller 16 and the low-voltage system controller 17.

[0067] The process then returns to the first measurement step 101.

[0068] Second Decision 107

[0069] If the operating point is outside the safe operating area, and the extraction law has not been modified at least once to favor extraction from the low-voltage system, then the extraction law is modified to favor extraction from the low-voltage system. Therefore, it should be understood that the fourth calculation module thus communicates with the main controller 11 to ensure that this modification of the law is taken into account.

[0070] As a result, if the operating point is too high, the extraction law is modified to further shift the load demand to the low-voltage system. The high-voltage system thus bears a lower load, thereby enabling it to lower its operating point.

[0071] Therefore, it should be understood that in this second decision, the extraction law is modified to favor extraction from the low-voltage system. For example, the extraction law is modified to require extraction only from the low-voltage system, or to require extraction to be distributed between the low-voltage and high-voltage systems, with extraction primarily from the low-voltage system. In the latter case, for example, extraction is distributed between the low-voltage and high-voltage systems such that the ratio of the amount of power extracted from the high-voltage system to the amount of power extracted from the low-voltage system is between 0 and 0.5.

[0072] During the second phase 108, the main controller 11 transmits control commands to the high-voltage system controller 16 and the low-voltage system controller 17.

[0073] The process then returns to the first measurement step 101.

[0074] Third Decision

[0075] If the operating point is located outside the safe operating area, and the extraction law has been modified at least once to facilitate extraction from the low-voltage system, the fourth calculation module commands a power supply reduction to at least one device that has so far been powered by the management system 10 via busbar 12. It should therefore be understood that the fourth calculation module communicates with the main controller 11 to ensure that this power reduction command is taken into account.

[0076] Therefore, during the third phase 109, the main controller 11 controls the components that connect one or more devices to the busbar 12 in order to temporarily interrupt the power supply to the relevant devices.

[0077] The high-voltage system therefore bears a lower load, which allows it to lower its operating point.

[0078] Preferably, the devices powered by the management system 10 are classified into at least two different priority categories. This classification is predetermined and can optionally be modified during operation of the turbine engine 1.

[0079] For example, equipment is classified into high-priority, medium-priority, and low-priority categories. High-priority equipment includes, for example, equipment related to the propulsion of aircraft A (e.g., de-icing components of turbine engine 1). Medium-priority equipment includes, for example, equipment related to system functions of aircraft A other than propulsion (e.g., avionics systems). Low-priority equipment includes, for example, equipment related to passenger entertainment (e.g., game controllers, microwave ovens, etc.).

[0080] Therefore, if a third decision is made, the main controller 11 prioritizes the load shedding of devices classified as low priority. Optionally, if this is insufficient, the main controller 11 performs load shedding of devices classified as medium priority. Optionally, if this is still insufficient, the main controller 11 performs load shedding of devices classified as high priority.

[0081] The process then returns to the first measurement step 101.

[0082] Therefore, it should be understood that regardless of the decision made, the process returns to the first measurement step 101. Thus, the aforementioned successive steps 101, 102, 103, and 104 are repeated at regular intervals, such as between 5 milliseconds and 200 milliseconds, which enables proper control of the high-voltage system.

[0083] According to the second option, the management system 10 is configured to prioritize monitoring the low-voltage system.

[0084] Subsequently, the various modules described belong to the management system 10, and for example to the main controller 11 and / or the low-voltage system controller 17.

[0085] In the initial step 100, performed in the determination module, the safe operating area of ​​the low-voltage system is determined based on at least one data point of the surge line of the low-voltage system.

[0086] The data regarding surge lines is provided by the manufacturer and is therefore known.

[0087] The safe operating area is defined as being far from the surge line. This defines a region where low-voltage systems can operate without surge phenomena impairing their performance.

[0088] According to the first step 101, performed in the first measurement module, at least one characteristic data related to the low-pressure system is measured.

[0089] For example, characteristic data include: pressure in the low-pressure system, temperature in the low-pressure system, speed in the low-pressure system, and fuel flow rate consumed by the low-pressure system.

[0090] According to step 102, executed in the second calculation module, at least one operating point of the low-pressure system is determined based on measurements. The calculation of the operating point can be based on at least one table, at least one simplified model, at least one inverse model, at least one integrated thermodynamic model, etc.

[0091] According to step 103, performed in the third calculation module, it is determined whether the operating point is outside the safe operating area of ​​the low-pressure system. Therefore, it should be understood that the safe operating area is thus defined by a set of mass flow rate to compression ratio ratios, and the operating point is preferably kept within the operating area.

[0092] Therefore, during step 104, the fourth calculation module is executed, and decisions are made according to the following decision order based on the location of the working point.

[0093] First Decision 105

[0094] If the operating point is within the safe operating area, the operating law remains unchanged. Therefore, it should be understood that the fourth calculation module communicates with the main controller 11 to indicate that the law remains unchanged. During the first phase 106, the main controller 11 transmits control commands to the high-voltage system controller 16 and the low-voltage system controller 17.

[0095] The process then returns to the first measurement step 101.

[0096] Second Decision 107

[0097] If the operating point is outside the safe operating area, and the extraction law has not been modified at least once to favor extraction from the low-voltage system, then the extraction law is modified to favor extraction from the low-voltage system. Therefore, it should be understood that the fourth calculation module thus communicates with the main controller 11 to ensure that this modification of the law is taken into account.

[0098] As a result, if the operating point is too high, the extraction law is modified to further shift the load demand to the high-voltage system. The low-voltage system thus bears a lower load, thereby allowing it to lower its operating point.

[0099] Therefore, it should be understood that in this second decision, the extraction law is modified to favor extraction from the high-voltage system. For example, the extraction law is modified to require extraction only from the low-voltage system, or to require extraction to be distributed between the high-voltage and low-voltage systems, with extraction primarily from the high-voltage system. In the latter case, for example, extraction is distributed between the low-voltage and high-voltage systems such that the ratio of the amount of power extracted from the low-voltage system to the amount of power extracted from the high-voltage system is between 0 and 0.5.

[0100] During the second phase 108, the main controller 11 transmits control commands to the high-voltage system controller 16 and the low-voltage system controller 17.

[0101] The process then returns to the first measurement step 101.

[0102] Third Decision

[0103] If the operating point is located outside the safe operating area, and the extraction law has been modified at least once to facilitate extraction from the high-voltage system, the fourth calculation module commands a power supply reduction to at least one device that has been powered by the management system 10 via busbar 12. It should therefore be understood that the fourth calculation module communicates with the main controller 11 to ensure that this power reduction command is taken into account.

[0104] Therefore, during the third phase 109, the main controller 11 controls the components that connect one or more devices to the busbar 12 in order to temporarily interrupt the power supply to the relevant devices.

[0105] Low-voltage systems therefore withstand lower loads, thus enabling them to lower their operating point.

[0106] Preferably, if a third decision is made, the main controller 11 prioritizes the load shedding of devices classified as low priority. Optionally, if this is insufficient, the main controller 11 performs load shedding of devices classified as medium priority. Optionally, if this is still insufficient, the main controller 11 performs load shedding of devices classified as high priority.

[0107] The process then returns to the first measurement step 101.

[0108] Therefore, it should be understood that regardless of the decision made, the process will return to the first measurement step 101. Thus, the aforementioned successive steps 101, 102, 103, and 104 are repeated at intervals, such as between 5 milliseconds and 200 milliseconds, which enables proper control of the low-pressure system.

[0109] According to the third option, the management system is configured to monitor both the low-voltage and high-voltage systems simultaneously.

[0110] The first three steps, 101, 102, and 103, are the same as the steps described above, and can be performed independently for high-voltage and low-voltage systems.

[0111] On the other hand, step 104 cannot be executed independently. The management system 10 then preferably applies the following controlled rules: If both the high-voltage and low-voltage systems are within their safe operating range, the operating law remains unchanged. The main controller 11 transmits the corresponding control commands to the high-voltage system controller 16 and the low-voltage system controller 17. The process then returns to the first measurement step 101.

[0112] If one system is within its safe operating area but the other is not, the operating law is modified to prioritize extraction from the other system, which is still within its safe operating area. The main controller 11 transmits corresponding control commands to the high-voltage system controller 16 and the low-voltage system controller 17. The process then returns to the first measurement step 101.

[0113] If both systems are outside their safe operating areas, the management system 10 commands a power supply reduction to at least one device that has been powered by the management system 10 via the busbar 12 so far, to alleviate the burden on both the high-voltage and low-voltage systems. The process then returns to the first measurement step 101.

[0114] Therefore, it should be understood that regardless of the rules applied, the process will return to the first measurement step 101. Thus, the four successive steps described above are repeated at regular intervals, such as between 5 milliseconds and 200 milliseconds, which enables control of both low-pressure and high-pressure systems.

[0115] refer to Figure 3 and Figure 4 The second embodiment of the present invention will now be described. This second embodiment is the same as the first embodiment, except that the aircraft A includes at least one energy storage component 24 associated with the turbine engine 1. For example, the energy storage component 24 is controlled by the main controller 11.

[0116] For example, energy storage component 24 is a fuel cell and / or battery pack.

[0117] The energy storage component 24 enables temporary assistance to the turbine engine 1, for example, during periods when the equipment powered by the turbine engine 1 has particularly high load demands.

[0118] For this purpose, the energy storage component 24 is connected to the busbar 12 directly or via at least one electrical and / or electronic component (e.g., an electronic power converter). For example, the electronic power converter may be a DC / DC converter. The electronic power converter is preferably reversible, allowing the energy storage component 24 to be recharged via the busbar 12. For example, the energy storage component 24 is charged by the busbar 12 when the busbar 12 is capable of doing so given the load demands of the device, or by an external power source.

[0119] The energy storage component 24 is connected to the busbar 12 via a channel (e.g., a DC channel), which is connected in parallel to other channels connected to the busbar 12 (particularly the channels that connect electrical interfaces 18 and 21 to the busbar 12).

[0120] In fact, it is possible that even if the extraction law is modified, at least one of the low-pressure system and the high-pressure system will remain outside its safe operating area.

[0121] Therefore, during additional decision 110 (whether the first option, the second option, or the third option is used), the main controller 11 uses the energy storage component 24 to supplement and / or replace the power portion extracted from the turbine engine 1 to supply power to the equipment.

[0122] Low-voltage and high-voltage systems therefore bear lower loads, which allows them to lower their operating points.

[0123] According to the first possibility, additional decision 110 can be performed between the second decision 107 and the third decision. Therefore, if the operating point of at least one of the low-pressure and high-pressure systems is outside the safe zone, and the extraction law has been modified at least once to favor extraction from the other system, and the energy storage component 24 is at least partially charged, then during the fourth stage 111, the main controller 11 commands the energy storage component 24 to supply power to the device via the busbar 12. The main controller 11 may optionally change the extraction law again to further reduce the extraction proportion from the system whose operating point is outside the safe zone (without increasing the extraction proportion from the other system, which the energy storage component 24 is capable of absorbing), and / or may optionally modify the extraction law again to ensure that the extraction proportion from the low-pressure system is the same as the extraction proportion from the high-pressure system. The process then returns to the first measurement step 101.

[0124] If, despite the intervention of the energy storage component 24, the low-pressure and / or high-pressure systems remain outside their respective safe operating areas, then during the next step 104, the main controller 11 unloads according to the aforementioned third decision command.

[0125] According to the second possibility, the additional decision 110 can be executed after or during the third decision. For example, the main controller 11 can command a load shedding to be performed on at least one device (e.g., a low-priority device), and if, despite the load shedding, the low-voltage and / or high-voltage system remains outside its safe operating area, the main controller 11 commands the energy storage component 24 to intervene in an attempt to bring the low-voltage and / or high-voltage system back into its safe operating area. If, despite the assistance of the energy storage component 24, the low-voltage and / or high-voltage system remains outside its safe operating area, the main controller 11 commands continued load shedding.

[0126] The management system 10 is preferably configured to switch between two possibilities when necessary, for example, based on at least one characteristic of the energy storage component 24, such as its charging state.

[0127] Of course, the present invention is not limited to the described embodiments, but includes any variations that fall within the scope of the invention as defined by the claims.

[0128] This invention is applicable to any type of turbine engine, such as turbofan engines, turbojet engines, turbojet engines with two or more rotors, hybrid turboprop engines, hybrid turbojet engines, etc.

[0129] Therefore, a turbofan engine may or may not include a reduction gearbox. Thus, a turbofan engine may be ducted or unducted (a turbofan engine may therefore be called an unducted fan, or more commonly, an "open fan").

[0130] The aircraft can be drones, airplanes, helicopters, etc.

[0131] When a turbine engine is associated with an energy storage component, the extraction law can be modified to reduce the load on the high-voltage and / or low-voltage systems, regardless of the equipment powered by the management system, as long as the energy storage component is at least partially charged.

[0132] The management system may differ from the management system described above, and may include, for example, at least one communication bus. Therefore, the management system may include at least one communication channel.

[0133] The first electrical interface and / or the second electrical interface may differ from those described above. For example, the motor may be synchronous, asynchronous, or variable reluctance. If the motor is synchronous, it may include a wound rotor instead of a permanent magnet.

[0134] Although each safe working area is defined here as being far away from the associated surge line, the safe working area can be closer to the surge line and, for example, terminate at the surge line.

[0135] Although at least one safe operating area is defined here based on the surge line, at least one safe operating area may be defined based on at least one other constraint, such as the maximum permissible extraction capacity on the system associated with the safe operating area (e.g., to avoid one or more thermal problems on a turbine engine).

[0136] Regardless of the definition and circumstances of high-pressure and low-pressure systems, the extraction law may include at least one upper limit and / or one lower limit for extraction from high-pressure and / or low-pressure systems.

[0137] Regardless of the definitions and conditions of the high-voltage and low-voltage systems, the extraction law will preferably be defined such that the sum of the power to be extracted from the high-voltage and low-voltage systems is greater than or equal to the sum of the power consumption of the various devices connected to the busbar. This will enable the maintenance of an acceptable voltage level in the management system, especially at the busbar. External power sources and / or energy storage components can help maintain the available power level at the busbar such that, if extraction from the turbine engine is insufficient, this level is permanently greater than or equal to the sum of the power consumption of the various devices.

Claims

1. A method for controlling a turbine engine (1) of an aircraft (A), the turbine engine having a high-pressure system and a low-pressure system, the method comprising the steps of: A portion of the power generated by the turbine engine is extracted according to an extraction law to power one or more devices (13, 14, 15) of the aircraft, the extraction law specifying that the portion of the power generated by the turbine engine (1) is extracted at the high-pressure system and / or at the low-pressure system, the method further comprising: The following steps are used to monitor the high-voltage system: - Measure (101) at least one characteristic data related to the high-voltage system, - The operating point of the high-voltage system (102) is determined based on the measurements. as well as The following steps are used to monitor the low-pressure system: - Measure (101) at least one characteristic data related to the low-pressure system, - Determine the operating point of the low-voltage system (102) based on the measurements. The method further includes the following steps: - If the operating point of the high-voltage system is outside the safe operating area of ​​the high-voltage system, and the operating point of the low-voltage system is within the safe operating area of ​​the low-voltage system, then the extraction law (106) is modified to facilitate extraction at the low-voltage system, wherein the safe operating area of ​​the high-voltage system is defined based on at least one data point of the surge line of the high-voltage system, and the safe operating area of ​​the low-voltage system is defined based on at least one data point of the surge line of the low-voltage system. - and / or if the operating point of the low-voltage system is outside the safe operating area of ​​the low-voltage system and the operating point of the high-voltage system is inside the safe operating area of ​​the high-voltage system, then the extraction law (106) is modified to facilitate extraction at the high-voltage system, the safe operating area of ​​the low-voltage system being defined based on at least one data point of the surge line of the low-voltage system.

2. The method as described in claim 1, characterized in that, If the operating point of the high-voltage system is outside the safe operating area of ​​the high-voltage system, the extraction law remains unchanged; or if the operating point of the low-voltage system is outside the safe operating area of ​​the high-voltage system, the extraction law remains unchanged.

3. The method as described in claim 1 or 2, characterized in that, If the operating point remains outside the safe operating zone despite the modification of the extraction law, then a load reduction (109) is performed on at least one of the devices (13, 14, 15) powered by the portion of the power generated by the extracted turbine engine (1).

4. The method as described in any one of the preceding claims, characterized in that, The devices (13, 14, 15) are classified into at least two different priority categories, with the devices belonging to the lower priority category being the ones that are given priority to perform load shedding.

5. The method as described in any one of the preceding claims, characterized in that, Includes at least one energy storage component (24) associated with the turbine engine (1).

6. The method as described in claim 5, characterized in that, If the operating point remains outside the safe operating area despite the modification of the extraction law, the energy storage component (24) is used to participate in supplying power to at least one of the devices.

7. The method as described in claim 6, characterized in that, If, despite the use of the energy storage component (24), at least one of the operating points of the high-voltage system or the low-voltage system remains outside the safe operating area, then a load reduction is performed on at least one of the devices (13, 14, 15) powered by the portion of the power generated by the turbine engine (1).

8. The method according to any one of claims 5 to 7, characterized in that, When the energy storage component (24) is invoked, the extraction law is modified to reduce the load on at least one of the high-voltage system and the low-voltage system, but without increasing the load on the other system.

9. A management system (10) for performing the method as described in any of the preceding claims.

10. An aircraft (A) comprising at least one management system as described in claim 9.

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