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 equipped with a high-pressure system and with a low-pressure system, the method comprising the step of drawing a portion of power generated by the turbine engine in order to power one or more devices of the aircraft according to a power draw law governing whether the portion of the power generated by the turbine engine is to be drawn at the high-pressure system and / or the low-pressure system, the method further comprising steps 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] METHOD FOR CONTROLLING AN AIRCRAFT TURBOMACHINE

[0002] The present invention relates to a method for controlling a turbomachine of an aircraft.

[0003] The invention also relates to a system implementing such a method as well as an aircraft equipped with such a system.

[0004] BACKGROUND OF THE INVENTION

[0005] Climate change is a major concern for many legislative and regulatory bodies around the world. Indeed, various carbon emission restrictions have been, are being, or will be adopted by various states. In particular, an ambitious standard applies to both new aircraft types and those currently in operation, requiring the implementation of technological solutions to bring them into compliance with current regulations. Civil aviation has been mobilizing for several years now to contribute to the fight against climate change.

[0006] Technological research efforts have already led to very significant improvements in the environmental performance of aircraft. The Applicant takes into consideration the impact factors in all phases of design and development to obtain less energy-intensive, more environmentally friendly aeronautical components and products whose integration and use in civil aviation have moderate environmental impacts with the aim of improving the energy efficiency of aircraft.

[0007] Consequently, the Applicant is constantly working to reduce its climate impact by using methods and operating virtuous development and manufacturing processes that minimize greenhouse gas emissions to the minimum possible in order to reduce the environmental footprint of its activity. This sustained research and development work covers new generations of aircraft engines, the weight reduction of aircraft, in particular through the materials used and lighter on-board equipment, the development of the use of electrical technologies to provide propulsion, and, as essential complements to technological progress, aeronautical biofuels.

[0008] An aircraft turbomachine conventionally comprises, from upstream to downstream (according to a gas flow direction in the turbomachine): a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, a low-pressure turbine and a gas exhaust nozzle. The low-pressure compressor, the high-pressure compressor, the high-pressure turbine, and the low-pressure turbine comprise rotors rotating in casings connected to each other and to the combustion chamber and the nozzle to form a tubular assembly which delimits an annular primary gas flow space. The rotor of the high-pressure turbine is rotationally connected to the rotor of the high-pressure compressor to drive the latter in rotation and the rotor of the low-pressure turbine is rotationally connected to the rotor of the low-pressure compressor to drive the latter in rotation.The assembly comprising the high-pressure turbine and the high-pressure compressor is called the high-pressure system and the assembly comprising the low-pressure turbine and the low-pressure compressor is called the low-pressure system.

[0009] With the increasing integration of electrical elements within aircraft, it has been proposed to associate turbomachines with at least one electrical interface between the turbomachine and one or more electrical networks of the aircraft.

[0010] The electrical interface is thus used to fulfill one or more functions such as, for example, assisting the turbomachine with start-up or even taking part of the power generated by the turbomachine to supply one or more devices of the aircraft (the majority of the power produced by the turbomachine being of course used for the propulsion of the aircraft).

[0011] For this purpose, the electrical interface obeys a predetermined sampling law which governs whether the part of the power generated by the turbomachine must be taken from the high pressure system and / or the low pressure system.

[0012] Although very useful, this sampling can be extremely restrictive for the turbomachine.

[0013] Indeed, a turbomachine is already sensitive to "surge" problems, it being recalled here that surge corresponds to an aerodynamic stall due to an excessively large pressure differential between the low pressure and high pressure systems. Furthermore, this bleed increases the temperature of the expanded gases in the turbine. However, bleeds tend to amplify these problems, particularly in the event of sudden and / or significant bleed following the demand of one or more devices.

[0014] Moreover, when the turbomachine enters a degraded regime, in which the pumping phenomenon is present, it is difficult for it to exit this state.

[0015] SUBJECT OF THE INVENTION

[0016] The invention aims to at least partially overcome the aforementioned drawbacks.

[0017] SUMMARY OF THE INVENTION

[0018] To this end, the invention proposes a method for controlling a turbomachine of an aircraft, the turbomachine being equipped with a high pressure system and a low pressure system, the method comprising the step of taking a portion of a power generated by the turbomachine to supply one or more devices of the aircraft according to a taking law governing whether the portion of the power generated by the turbomachine must be taken from the high pressure system and / or the low pressure system, the method further comprising:

[0019] • The following steps for monitoring the high pressure system:

[0020] - Measure at least one characteristic data linked to the high pressure system,

[0021] - Determine an operating point of the high pressure system from said measurement,

[0022] And

[0023] • The following steps for monitoring the low pressure system:

[0024] - Measure at least one characteristic data linked to the low pressure system,

[0025] - Determine an operating point of the low pressure system from said measurement,

[0026] The method further comprising the following step:

[0027] - If the operating point of the high pressure system is outside a safe operating zone of the high pressure system and the operating point of the low pressure system is itself in a safe operating zone of the low pressure system, modify the sampling law to favor sampling at the level of the low pressure system, the safe operating zone of the high pressure system being defined from at least one pumping line data item of said high pressure system, the safe operating zone of the low pressure system being defined from at least one pumping line data item of said low pressure system,

[0028] - And / or if the operating point of the low pressure system is outside the safe operating zone of the low pressure system, and the operating point of the high pressure system is itself in the safe operating zone of the high pressure system, modify the sampling law to favor sampling at the level of the high pressure system, the safe operating zone of the low pressure system being defined from at least one pumping line data of said low pressure system.

[0029] Thus, the invention manages the withdrawals from the turbomachine by acting on the withdrawal law to accentuate the withdrawals from one of the high pressure or low pressure systems.

[0030] This allows the high pressure system or the low pressure system to return more easily to its safe operating zone and / or to prevent the high pressure system or the low pressure system from leaving and / or moving too far from its safe operating zone. The invention is thus the result of technological research aimed at significantly improving aircraft performance and, in this sense, contributes to reducing the environmental impact of aircraft.

[0031] Optionally, if the operating point of the high pressure system is outside a safe operating zone of the high pressure system then the sampling law remains unchanged or if the operating point of the low pressure system is outside a safe operating zone of the high pressure system then the sampling law remains unchanged.

[0032] Optionally, if despite the modification of the sampling law the operating point remains outside the safe zone, at least one of the devices supplied by the sampling of the part of the power generated by the turbomachine is unloaded.

[0033] Optionally, devices are classified into at least two different priority categories, with devices in the lower priority category being the ones offloaded first.

[0034] Optionally, the method includes at least one energy storage device associated with the turbomachine.

[0035] Optionally, if despite the modification of the sampling law the operating point remains outside the secure zone, the energy storage device is used to participate in the power supply of at least one of the devices.

[0036] Optionally, if despite the use of the energy storage device, at least one of the operating points of the high pressure or low pressure system remains outside the safe operating zone, at least one of the devices supplied by the extraction of part of the power generated by the turbomachine is relieved.

[0037] Optionally, the withdrawal law is modified in the event of recourse to the energy storage device so as to place less strain on at least one of the high pressure or low pressure systems without, however, placing more strain on the other system.

[0038] The invention also relates to a management system implementing the method as mentioned above.

[0039] The invention also relates to an aircraft comprising at least one management system as mentioned above.

[0040] Other characteristics and advantages of the invention will emerge from reading the following description of a particular non-limiting embodiment of the invention.

[0041] BRIEF DESCRIPTION OF THE DRAWINGS

[0042] The invention will be better understood in light of the following description, which is illustrative and not limiting, and must be read in conjunction with the appended drawings, among which:

[0043] [Fig. 1] Figure 1 is a schematic view of a system according to a first particular embodiment of the invention making it possible to implement a method for controlling a turbomachine of an aircraft;

[0044] [Fig. 2] Figure 2 is a flowchart schematically illustrating a series of steps of the process implemented in the system shown in Figure 1;

[0045] [Fig. 3] Figure 3 is a schematic view of a system according to a second particular embodiment of the invention making it possible to implement a method for controlling a turbomachine of an aircraft;

[0046] [Fig. 4] Figure 4 is a flowchart schematically illustrating a series of steps of the process implemented in the system shown in Figure 3.

[0047] DETAILED DESCRIPTION OF THE INVENTION

[0048] With reference to figures 1 and 2, an electrical management system 10 according to a first particular embodiment of the invention is described here in application to a double-flow turbomachine 1 of an aircraft A.

[0049] The turbomachine 1 comprises, from upstream to downstream in a direction of flow of the gases in said turbomachine 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. The low-pressure compressor 3, the high-pressure compressor 4, the high-pressure turbine 6 and the low-pressure turbine 7 each comprise a rotor which rotates in a casing.

[0050] The rotor of the high-pressure turbine 6 and the rotor of the low-pressure turbine 7 are respectively integral in rotation with the rotor of the high-pressure compressor 4 and the rotor of the low-pressure compressor 3, so that the rotor of said high-pressure turbine 6 and the rotor of said low-pressure turbine 7 respectively drive the rotor of said high-pressure compressor 4 and the rotor of said low-pressure compressor 3 in rotation about a longitudinal axis X of the turbomachine 1 under the effect of the thrust of the gases coming from the combustion chamber 5.

[0051] The air mass sucked in by the blower 2 is divided into two flows: a primary flow Fl which circulates in an annular primary flow channel Cl, and a secondary flow F2 which is concentric with the primary flow Fl and which circulates in an annular secondary flow channel C2.

[0052] The turbomachine 1 also comprises an intermediate casing designating, in a manner known per se, a casing of which a hub is arranged between the casing of the low pressure compressor 3, located upstream, and the casing of the high pressure compressor 4, located downstream.

[0053] The assembly comprising the low pressure turbine and the low pressure compressor 3 is hereinafter called the “high pressure system” and the assembly comprising the high pressure turbine and the high pressure compressor 4 is hereinafter called the “low pressure system”.

[0054] The general arrangement of the turbomachine described is conventional and will not be detailed further here. The management system 10 comprises at least one general controller 11 associated with the turbomachine 1.

[0055] The management system 10 also comprises a bus bar 12 and for example a direct current bus bar 12. The bus bar 12 is controlled by the general controller 11.

[0056] To the bus bar 12 are connected one or more devices of the aircraft 1 intended to be powered by said bus bar 12. The devices can be: connected directly to this bar (like the device referenced 13 in figure 1); connected indirectly via an electrical and / or electronic component such as for example an electronic power converter (like the devices referenced 14 in figure 1); connected indirectly via several electrical and / or electronic components such as for example a power converter to which an additional bus bar is connected and to which the devices are themselves connected (like the devices referenced 15 in figure 1).

[0057] Preferably, and as will be detailed below, the general controller 11 controls one or more of these electrical and / or electronic components to be able to temporarily stop the electrical supply of one or more devices via the bus bar 12.

[0058] Optionally an external power source (not shown here) can also be connected to bus bar 12.

[0059] Optionally, bus bar 12 can also transmit data to general controller 11.

[0060] Furthermore, the management system 10 comprises at least one high pressure system controller 16 and one low pressure system controller 17. The general controller 11 controls the controllers 16, 17 of the low pressure system and of the high pressure system. The general controller 11 controls in particular the controllers 16, 17 of the low pressure system and of the high pressure system from at least one characteristic data item of the turbomachine 1 and / or from at least one characteristic data item of the bus bar 12 (and therefore of the devices connected thereto).

[0061] The controller of the low pressure system 17 is associated with a first electrical interface 18 of the management system 10, first interface 18 making it possible to at least take, at the level of the low pressure system, a part of an electrical power generated by the turbomachine 1. The first interface 18 is in particular controlled by the controller of the low pressure system 17 and transmits to it in return at least one piece of information characteristic of the first interface 18.

[0062] The first interface 18 here comprises: an electrical machine 19 connected to the low pressure system of the turbomachine 1 and for example a permanent magnet synchronous machine, an electronic power converter 20 which is connected to the electrical machine 19 on the one hand and to the bus bar 12 on the other hand.

[0063] The first interface 18 is for example controlled by the low pressure system controller 17 at its electronic power converter 20.

[0064] In an identical manner, the controller of the high pressure system 16 is associated with a second electrical interface 21 of the management system 10, second interface 21 making it possible to take from the high pressure system part of an electrical power generated by the turbomachine 1. The second interface 21 is in particular controlled by the controller of the high pressure system and transmits to it in return at least one piece of information characteristic of the second interface 21.

[0065] The second interface 21 here comprises: an electrical machine 22 connected to the low pressure system of the turbomachine 1 and for example a permanent magnet synchronous machine, an electronic power converter 23 which is connected to the electrical machine 22 on the one hand and to the bus bar 12 on the other hand.

[0066] The second interface 21 is for example controlled by the high pressure system controller 16 at its electronic power converter 23.

[0067] Optionally, bus bar 12 may transmit data to the low pressure system controller and / or the high pressure system controller.

[0068] In operation, the general controller 11 controls the controllers of the high pressure and low pressure systems 16, 17 according to a sampling law governing whether the portion of the power generated by the turbomachine 1 taken from the high pressure system and / or the low pressure system must be taken from the high pressure system and / or the low pressure system. The controllers of the high pressure and low pressure systems 16, 17 thus take the power required by the general controller 11 in order to supply the bus bar 12.

[0069] It is thus noted that the power supply of the bus bar 12 by the first interface 18 and the second interface 21 is carried out by channels which are connected in parallel to said bus bar 12. Said channels are therefore direct current channels here.

[0070] With reference to Figure 2, and according to a first option, the management system 10 is configured to monitor the high pressure system as a priority.

[0071] Subsequently, the various modules described belong to the management system 10 and for example to the general controller 11 and / or to the high pressure system controller 16.

[0072] In an initial step 100, implemented in a determination module, a safe operating zone of the high pressure system is determined from at least one piece of data from a pumping line of said high pressure system.

[0073] The data linked to the pumping line is manufacturer data which is therefore known.

[0074] The safe operating zone is defined so as to be away from this pumping line. This defines an area in which the high-pressure system can operate without any pumping phenomena degrading its performance.

[0075] According to a first step 101, implemented in a first measurement module, at least one characteristic data item linked to the high pressure system is measured.

[0076] The characteristic data is for example: a pressure prevailing in the high pressure system, a temperature prevailing in the high pressure system, a rotation speed of the high pressure system, a flow rate of the fuel consumed by the high pressure system ...

[0077] According to a second step 102, implemented in a second calculation module, at least one operating point of the high-pressure system is determined from said measurement(s). It is recalled that the operating point corresponds to the ratio between the mass flow rate (of the air passing through the high-pressure system) and the compression ratio of the high-pressure system. The calculation of the operating point may be based on at least one tabulation, at least one simplified model, at least one inverse model, at least one integrated thermodynamic model, etc.

[0078] According to a third step 103, implemented in a third calculation module, it is determined whether the operating point is outside the safe operating zone of the high pressure system. It is therefore understood that the safe operating zone is thus delimited by a set of mass flow rate to compression ratio ratios, the operating point preferably remaining in this operating zone.

[0079] Thus, during a fourth step 104, implemented in a fourth calculation module, depending on the position of the operating point, a decision is taken according to the sequence of the following decisions.

[0080] First decision 105

[0081] If the operating point is in the secure zone, the operating law is not modified. It is therefore understood that the fourth calculation module thus communicates with the general controller 11 to indicate to it that the law is not modified. The general controller 11 transmits corresponding control orders to the controllers of the high pressure and low pressure systems 16, 17 during a first phase 106.

[0082] We then return to the first measurement step 101.

[0083] Second decision 107

[0084] If the operating point is outside the safe operating zone and the sampling law has not already been modified at least once to prioritize sampling at the low pressure system, the sampling law is modified to prioritize sampling at the low pressure system. It is therefore understood that the fourth calculation module communicates with the general controller 11 to ensure that this modification of the law is taken into account.

[0085] In this way, if the operating point is too high, modifying the sampling law allows the load demand to be shifted more to the low-pressure system. The high-pressure system is thus less stressed, which allows its operating point to be lowered. It is therefore understandable that in this second decision, the sampling law is modified in order to prioritize sampling from the low-pressure system. For example, the sampling law is modified so as to require that sampling be carried out only on the low-pressure system or so as to require that sampling be distributed between the low-pressure system and the high-pressure system, with the majority being carried out on the low-pressure system.In the latter case, the samples are, for example, distributed between the low pressure system and the high pressure system so that the amount of power taken from the high pressure system over the amount of power taken from the low pressure system is between 0 and 0.5.

[0086] The general controller 11 transmits corresponding control orders to the controllers of the high pressure and low pressure systems 16, 17 during a second phase 108.

[0087] We then return to the first measurement step 101.

[0088] Third decision

[0089] If the operating point is outside the safe operating zone and the sampling law has already been modified at least once to favor sampling at the low pressure system, the fourth calculation module orders a load shedding of the power supply of at least one of the devices which was supplied until now by the management system 10 via the bus bar 12. It is therefore understood that the fourth calculation module thus communicates with the general controller 11 to ensure that this load shedding order is taken into account.

[0090] Consequently, the general controller 11 controls, during a third phase 109, the component(s) connecting one or more devices to the bus bar 12 in order to temporarily stop the power supply to the device(s) concerned.

[0091] The high pressure system is thus less stressed, which allows its operating point to be lowered.

[0092] Preferably, the devices powered by the management system 10 are classified into at least two categories of different priority. This classification is predetermined and optionally modifiable during operation of the turbomachine 1.

[0093] The devices are, for example, classified into a high priority category, a medium priority category, and a low priority category. Devices classified as high priority are, for example, devices related to the propulsion of aircraft A (such as a de-icing device for turbomachine 1). Devices classified as medium priority are, for example, devices related to system functions other than propulsion functions of aircraft A (such as an avionics system). Devices classified as low priority are, for example, devices related to passenger entertainment (such as a game control device, a microwave oven, etc.).

[0094] Therefore, if the third decision is taken, the General Controller 11 imposes the load shedding of devices classified as low priority as a priority. Optionally, if this is not sufficient, the General Controller 11 imposes the load shedding of devices classified as medium priority. Optionally, if this is still not sufficient, the General Controller 11 imposes the load shedding of devices classified as high priority.

[0095] We then return to the first step of measurement 101.

[0096] We thus understand that whatever the decision taken, we return again to the first measurement step 101. The successive steps 101, 102, 103 and 104 described previously are therefore repeated at regular intervals, for example between 5 and 200 milliseconds, which allows the high pressure system to be properly controlled.

[0097] According to a second option, the management system 10 is configured to monitor the low pressure system as a priority.

[0098] Subsequently, the various modules described belong to the management system 10 and for example to the general controller 11 and / or to the low pressure system controller 17.

[0099] In an initial step 100, implemented in a determination module, a safe operating zone of the low pressure system is determined from at least one piece of data from a pumping line of said low pressure system.

[0100] The data linked to the pumping line is manufacturer data which is therefore known.

[0101] The safe operating zone is defined so as to be away from this pumping line. This defines an area in which the low pressure system can operate without any pumping phenomena degrading its performance.

[0102] According to a first step 101, implemented in a first measurement module, at least one characteristic data item linked to the low pressure system is measured.

[0103] The characteristic data is for example: a pressure prevailing in the low pressure system, a temperature prevailing in the low pressure system, a rotation speed of the low pressure system, a flow rate of the fuel consumed by the low pressure system, etc.

[0104] According to a second step 102, implemented in a second calculation module, at least one operating point of the low pressure system is determined from said measurement(s). The calculation of the operating point may be based on at least one tabulation, at least one simplified model, at least one inverse model, at least one integrated thermodynamic model, etc.

[0105] According to a third step 103, implemented in a third calculation module, it is determined whether the operating point is outside the safe operating zone of the low pressure system. It is therefore understood that the safe operating zone is thus delimited by a set of mass flow rate to compression ratio ratios, the operating point preferably remaining in this operating zone.

[0106] Thus, during a fourth step 104, implemented in a fourth calculation module, depending on the position of the operating point, a decision is taken according to the sequence of the following decisions.

[0107] First decision 105

[0108] If the operating point is in the secure zone, the operating law is not modified. It is therefore understood that the fourth calculation module thus communicates with the general controller 11 to indicate to it that the law is not modified. The general controller 11 transmits corresponding control orders to the controllers of the high pressure and low pressure systems 16, 17 during a first phase 106.

[0109] We then return to the first measurement step 101.

[0110] Second decision 107 If the operating point is outside the safe operating zone and the sampling law has not already been modified at least once to prioritize sampling at the high-pressure system, the sampling law is modified to prioritize sampling at the high-pressure system. It is therefore understood that the fourth calculation module communicates with the general controller 11 to ensure that this modification of the law is taken into account.

[0111] In this way, if the operating point is too high, modifying the sampling law allows the load demand to be shifted more to the high-pressure system. The low-pressure system is thus less stressed, which allows its operating point to be lowered.

[0112] It is therefore understood that in this second decision, the sampling law is modified in order to favor sampling from the high-pressure system. For example, the sampling law is modified so as to require that sampling be carried out only from the high-pressure system or so as to require that sampling be distributed between the high-pressure system and the low-pressure system, with the majority being carried out from the high-pressure system. In the latter case, the sampling is, for example, distributed between the low-pressure system and the high-pressure system so that the quantity of power taken from the low-pressure system over the quantity of power taken from the high-pressure system is between 0 and 0.5.

[0113] The general controller 11 transmits corresponding control orders to the controllers of the high pressure and low pressure systems 16, 17 during a second phase 108. We then return to the first measurement step 101.

[0114] Third decision

[0115] If the operating point is outside the safe operating zone and the sampling law has already been modified at least once to favor sampling at the high pressure system, the fourth calculation module orders a load shedding of the power supply of at least one of the devices which was supplied until now by the management system 10 via the bus bar 12. It is therefore understood that the fourth calculation module thus communicates with the general controller 11 to ensure that this load shedding order is taken into account.

[0116] Consequently, the general controller 11 controls, during a third phase 109, the component(s) connecting one or more devices to the bus bar 12 in order to temporarily stop the power supply to the device(s) concerned.

[0117] The low pressure system is thus less stressed, which allows its operating point to be lowered.

[0118] Preferably, if the third decision is taken, the general controller 11 imposes the load shedding of devices classified as low priority as a priority. Optionally, if this is not sufficient, the general controller 11 imposes the load shedding of devices classified as medium priority. Optionally, if this is still not sufficient, the general controller 11 imposes the load shedding of devices classified as high priority.

[0119] We then return to the first step of measurement 101.

[0120] We thus understand that whatever the decision taken, we return again to the first measurement step 101. The successive steps 101, 102, 103 and 104 described previously are therefore repeated at regular intervals, for example between 5 and 200 ms, which allows good control of the low pressure system.

[0121] In a third option, the management system is configured to monitor both the low pressure system and the high pressure system.

[0122] The first three steps 101, 102, 103 are identical to what has been indicated above and can be implemented independently for the high pressure system and the low pressure system.

[0123] On the other hand, the fourth steps 104 cannot be implemented independently. The management system 10 then preferably applies the following ordered rules:

[0124] - If both high pressure and low pressure systems are in their safe operating zone, the operating law is not modified. The general controller 11 transmits corresponding control orders to the controllers of the high pressure and low pressure systems 16, 17. We then return to the first measurement step 101.

[0125] - If one of the systems is in its safe operating zone but not the other system, then the operating law is modified to prioritize the withdrawals from the other system which is still in its safe operating zone. The general controller

[0126] 11 transmits corresponding control orders to the controllers of the high pressure and low pressure systems 16, 17. We then return to the first measurement step 101.

[0127] - If both systems are outside their safe operating zones, the management system 10 orders a load shedding of the power supply of at least one of the devices which was previously powered by the management system 10 via the bus bar 12 in order to relieve both the high pressure system and the low pressure system. We then return to the first measurement step 101.

[0128] We therefore understand that whatever the rule applied, we then return to the first measurement step 101. The four successive steps described previously are therefore repeated at regular intervals, for example between 5 ms and 200 milliseconds, which allows the low pressure system to be properly controlled as well as the high pressure system.

[0129] With reference to Figures 3 and 4, a second particular embodiment of the invention will be described. This second embodiment is identical to the first embodiment except that the aircraft A comprises at least one energy storage member 24 associated with the turbomachine 1. The energy storage member 24 is for example controlled by the general controller 11.

[0130] The storage member 24 is for example a fuel cell and / or a battery.

[0131] The storage member 24 makes it possible to temporarily assist the turbomachine 1, for example, during a particularly high load demand from the devices powered by the turbomachine 1. For this purpose, the storage member 24 is connected to the bus bar 12 either directly or via at least one electrical and / or electronic component, such as, for example, an electronic power converter. Said electronic power converter is, for example, a direct current / direct current converter. Said electronic power converter is preferably reversible so that the storage member 24 can be recharged via said bus bar 12. For example, the storage member 24 is charged by the bus bar 12 when the latter is capable of doing so in view of the load demand from the devices or is charged by the external electrical power source.

[0132] The storage member 24 is connected to the bus bar 12 by a channel (such as a direct current channel) connected in parallel with the other channels connected to the bus bar 12 (in particular the channels connecting the electrical interfaces 18 and 21 to the bus bar 12).

[0133] Indeed, it may happen that even if the sampling law is modified, at least one of the two low pressure and high pressure systems remains outside its safe operating zone.

[0134] Thus, during an additional decision 110 (regardless of whether the case is the first option, the second option or the third option), the general controller 11 uses the storage device 24 to supply the devices in addition to and / or as a replacement for the part of the power taken from the turbomachine 1.

[0135] The low pressure and / or high pressure systems are thus less stressed, which allows their operating point to be lowered.

[0136] According to a first possibility, the additional decision 110 can be implemented between the second decision 107 and the third decision. Thus, if at least the operating point of one of the low pressure and high pressure systems is outside the secure zone and the sampling law has already been modified at least once to favor sampling at the level of the other of said systems, and the storage member 24 is at least partially charged, during a fourth phase 111, the general controller 11 controls the storage member 24 so that it supplies the devices via the bus bar 12.The general controller 11 can optionally modify the sampling law again so that it further reduces the proportion of samplings on the system whose operating point is outside the secure zone (without increasing the proportion of samplings on the other system, the storage member 24 making it possible to absorb this reduction in samplings at the level of the turbomachine 1) and / or can optionally modify the sampling law again to ensure that the proportion of samplings on the low pressure system is the same as the proportion of samplings on the high pressure system. We then return to the first measurement step 101.

[0137] If, despite the intervention of the storage device 24, the low-pressure and / or high-pressure systems are outside their respective secure operating zones, then during the next step 104 the general controller 11 commands load shedding according to the third decision described above. According to a second possibility, the additional decision 110 can be implemented after the third decision or during the third decision. For example, the general controller 11 can command load shedding of at least one of the devices (such as a low-priority one) and if, despite the load shedding, the low-pressure and / or high-pressure systems are outside their secure operating zones, then the general controller 11 orders the intervention of the storage device 24 to attempt to bring the low-pressure and / or high-pressure systems back into their secure operating zones.If, despite the assistance of the storage device 24, the low pressure and / or high pressure systems are outside their safe operating zones, then the general controller 11 orders load shedding to continue.

[0138] The management system 10 is preferably configured to be able to switch between the two possibilities if necessary, for example depending on at least one characteristic of the storage device 24 such as for example its state of charge.

[0139] Of course, the invention is not limited to the embodiments described but encompasses any variant falling within the scope of the invention as defined by the claims.

[0140] The invention is applicable to any type of turbomachine, such as a double-flow turbojet, a single-flow turbojet, a turbojet with more than two spools, a hybrid turboprop, a hybrid turbojet, etc.

[0141] The turbomachine may therefore have a reducer or be without a reducer. The turbomachine may therefore be shrouded or unshrouded (the turbomachine may then be called an unshrouded fan, better known by the English term “open fan”).

[0142] The aircraft could be a drone, an airplane, a helicopter, etc.

[0143] In the case where the turbomachine is associated with an energy storage device, the sampling law can be modified to place less strain on the high pressure and / or low pressure system without consideration of the devices supplied by the management system as long as the storage device is at least partially charged.

[0144] The management system may differ from what has been indicated and may include, for example, at least one AC bus bar. The management system may therefore include at least one AC channel.

[0145] The first and / or second electrical interface may be different from what has been indicated. The electrical machine may, for example, be synchronous or asynchronous or with variable reluctance. If the electrical machine is synchronous, it may have wound rotors or permanent magnets instead.

[0146] Although here each safe operating zone is defined so as to be far from the associated pumping line, the safe operating zone may be closer to said pumping line and for example stop at the pumping line.

[0147] Although here at least one of the safe operating zones is defined from the pumping line, at least one of the safe operating zones may be defined from at least one other constraint such as for example a maximum authorized withdrawal capacity on the system associated with said safe operating zone (for example to avoid one or more thermal problems on the turbomachine).

[0148] Whatever the definition and situation of the high pressure and low pressure systems, the sampling law may include at least one maximum limit and / or one minimum limit for the samples taken from the high pressure system and / or the low pressure system.

[0149] Regardless of the definition and situation of the high-pressure and low-pressure systems, the offtake law will preferably be defined so that the sum of the power offtakes to be made from the high-pressure and low-pressure systems is greater than or equal to the sum of the power consumptions of the various devices at the bar. This will make it possible to maintain an acceptable voltage level in the management system, particularly at the bar. An external source and / or a storage device can help maintain the power level available at the bar, so that it is permanently greater than or equal to the sum of the power consumptions of the various devices if the offtakes made from the turbomachine were not sufficient.

Claims

CLAIMS 1. Method for controlling a turbomachine (1) of an aircraft (A), the turbomachine being equipped with a high pressure system and a low pressure system, the method comprising the step of taking a portion of a power generated by the turbomachine to supply one or more devices (13, 14, 15) of the aircraft according to a taking law governing whether the portion of the power generated by the turbomachine (1) must be taken at the high pressure system and / or the low pressure system, the method further comprising: • The following steps for monitoring the high pressure system: - Measure (101) at least one characteristic data linked to the high pressure system, - Determine (102) an operating point of the high pressure system from said measurement, And • The following steps for monitoring the low pressure system: - Measure (101) at least one characteristic data linked to the low pressure system, - Determine (102) an operating point of the low pressure system from said measurement, The method further comprising the following step: - If the operating point of the high pressure system is outside a safe operating zone of the high pressure system and the operating point of the low pressure system is itself in a safe operating zone of the low pressure system, modify (106) the sampling law to favor sampling at the level of the low pressure system, the safe operating zone of the high pressure system being defined from at least one pumping line data of said high pressure system, the safe operating zone of the low pressure system being defined from at least one pumping line data of said low pressure system, - And / or if the operating point of the low pressure system is outside the safe operating zone of the low pressure system, and the operating point of the high pressure system is itself in the safe operating zone of the high pressure system, modify (106) the sampling law to favor sampling at the level of the high pressure system, the safe operating zone of the low pressure system being defined from at least one pumping line data item of said low pressure system.

2. Method according to claim 1, in which if the operating point of the high pressure system is outside a safe operating zone of the high pressure system then the sampling law remains unchanged or if the operating point of the low pressure system is outside a safe operating zone of the high pressure system then the sampling law remains unchanged.

3. Method according to claim 1 or claim 2, in which if despite the modification of the sampling law the operating point remains outside the safe zone, at least one of the devices (13, 14, 15) supplied by the sampling of the part of the power generated by the turbomachine (1) is unloaded (109).

4. Method according to one of the preceding claims, in which the devices (13, 14, 15) are classified into at least two different priority categories, the devices belonging to the lower priority category being those offloaded first.

5. Method according to one of the preceding claims, comprising at least one energy storage member (24) associated with the turbomachine (1).

6. Method according to claim 5, in which if despite the modification of the sampling law the operating point remains outside the secure zone, the energy storage member (24) is used to participate in the power supply of at least one of the devices.

7. Method according to claim 6, in which if despite the use of the energy storage member (24), at least one of the operating points of the high pressure or low pressure system remains outside the safe operating zone, at least one of the devices (13, 14, 15) supplied by the withdrawal of the part of the power generated by the turbomachine (1) is discharged.

8. Method according to one of claims 5 to 7, in which the sampling law is modified in the event of recourse to the energy storage member (24) so ​​as to place less strain on at least one of the high pressure systems or low pressure without, however, placing more strain on the other system.

9. Management system (10) implementing the method according to one of the preceding claims.

10. Aircraft (A) comprising at least one management system according to claim 9.

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