Actuator power supply and control system

Abstract

The invention is specific to a power supply and control system (1) comprising - an actuator (2) comprising an actuator housing (4) and at least one electric motor (3) belonging to the actuator (2) and housed in a housing (4) of the actuator (2), the operation of the electric motor (3) being capable of causing the movement of a movable member (5) of the actuator (2), - at least one first alternator (6) and / or a second alternator (7), capable of generating an electrical power supply, - an electronic power module (9) powering the motor (3) of the actuator (2) and powered by the first alternator (6) and / or the second alternator (7), and - a control module (11) capable of controlling the electronic power module (9). More particularly, the electronic power module (9), the first alternator (6) and / or the second alternator (7) are housed in the actuator housing (4).The present invention is also specific to an aircraft turbomachine, comprising such a power supply and control system and to an aircraft comprising such a turbomachine. Figure to be published with the abstract: [Fig. 1].

Description

Title of the invention: Actuator power supply and control system Technical field of the invention

[0001] The invention relates to a system for supplying and controlling an actuator, in particular intended to equip a turbomachine, such as a turbojet, a turboprop of an aircraft or a helicopter turboshaft engine. The invention also relates to a turbomachine equipped with such a supply and control system and an aircraft comprising such a turbomachine. State of the prior art

[0002] Turbomachines intended for the aeronautical field generally comprise moving elements, for example air intake flaps (Inlet Guide Vanes or IGV in English) or variable pitch blades. These moving elements are moved by means of actuators which are currently mainly hydraulic, such as jacks. The fluid used for actuating these actuators is conventionally fuel taken from the fuel circuit of the turbomachine. The useful power is then provided by a hydraulic pump and modulated by a low-power electric actuator, of the controlled valve type.

[0003] The current trend is to replace hydraulic actuators with fully electric actuators. In such a case, the useful power is provided by an electrical power supply and modulated by an electronic power module controlled by a power control module.

[0004] The advantages of using an electric actuator include independence from the fuel system, greater ease of use and lower maintenance costs.

[0005] One of the difficulties is then to determine the architecture of the actuator power supply and control system. Such a power supply and control system notably comprises a power electronic module and a power control module. Furthermore, it is often required to have an autonomous power supply, separate from the power supply intended for the aircraft's on-board network, to power the power electronic module and the power control module.

[0006] In an aircraft, the power supply to the equipment is generally provided by a turbomachine regulation computer (Full Authority Digital Engine Control or FADEC in English), itself powered by an autonomous alternator driven by a turbine of the turbomachine. In the event of failure of the alternator, the regulation computer The turbomachine control system has an auxiliary power supply provided by the aircraft. The auxiliary power supply is also used in the event of a shutdown or during startup of the turbomachine, as long as the rotational speed of the alternator is not sufficient to provide the necessary electrical power.

[0007] Furthermore, when the same computer is designed for several applications, the computer must then be developed and sized to ensure the power supply in the case of the application requiring the most power. The computer is then correctly sized for a particular application but is oversized for other applications. The cost and mass of such a computer are therefore not optimized. Presentation of the invention

[0008] The invention aims to remedy the aforementioned drawbacks in a simple, reliable and inexpensive manner. To this end, the invention relates to a power supply and control system comprising - an actuator, comprising an actuator housing and at least one electric motor housed in the actuator housing and capable of driving a movement of a movable member of the actuator, - at least one first alternator and / or one second alternator, capable of generating an electrical power supply, - an electronic power module powering the actuator motor and powered by the first alternator and / or the second alternator, and - a power control module, capable of controlling the operation of the electronic power module.

[0009] Furthermore, according to the invention, the electronic power module, the first alternator and / or the second alternator are housed in the actuator housing.

[0010] The integration of the electronic power module into the actuator makes it possible to make the architecture of the power supply and control system more modular and thus to be able to be adapted to a large number of applications.

[0011] Furthermore, the definition of an assembly comprising both the electronic power module and the first alternator and / or the second alternator in the actuator makes it possible to ensure a reduction in the mass, size and overall cost of the power supply and control system. This is made possible by a commonality of the actuator housing and by the elimination of numerous electrical interfaces (connectors, electrical harnesses, shielding, etc.).

[0012] The power supply and control system may comprise the first alternator supplying the electronic power module and the second alternator supplying the power control module.

[0013] The power supply and control system also comprises first voltage rectification means arranged between the first alternator and the power electronic module and / or second voltage rectification means located between the second alternator and the power control module.

[0014] The first voltage rectification means and / or the second voltage rectification means supply the electronic power module and / or the power control module.

[0015] The first alternator, respectively the second alternator, comprises a rotor driven by a first input shaft, respectively by a second input shaft. Alternatively, the first alternator and the second alternator respectively comprise a rotor driven by the same first input shaft.

[0016] Advantageously, the first input shaft, respectively the second input shaft is arranged so as to be coaxial with the movable member of the actuator.

[0017] The first input shaft, respectively by the second input shaft, can be driven by a shaft of the gas generator or a shaft of the free turbine of a turbomachine, possibly via a reduction gear.

[0018] The power supply and control system may comprise electrical power supply selection means supplied by the first alternator, by the second alternator and / or by a separate electrical distribution network, for example an aircraft distribution network.

[0019] The power supply selection means are capable of supplying power to the power control module and / or the electronic power module.

[0020] The system may comprise a position control module, in particular located outside the actuator housing, capable of controlling the motor of the actuator as a function of a signal indicative of a position to be reached by the movable member of the actuator supplied by the position control module to the power control module.

[0021] The power control module can then be powered by the first alternator also powering the electronic power module, by the rectification means and / or by the aforementioned selection means.

[0022] The position control module may be housed in a computer housing. The power control module may then be housed in the computer housing. The computer may then be a control computer for the turbomachine of an aircraft.

[0023] Furthermore, the power control module may also be housed in the actuator housing.

[0024] At least the first alternator and / or at least the second alternator is arranged in a first subassembly and / or a second subassembly mounted in a manner modular on a main subassembly comprising at least the actuator.

[0025] The invention also relates to a turbomachine, for example a turbojet or a turboprop of an aircraft or a helicopter turboshaft engine, comprising at least one power supply and control system of the aforementioned type. The number of power supply systems can be at least doubled so as to ensure a redundancy function for safety reasons. The power supply system is then said to be multi-channel.

[0026] The invention also relates to an aircraft comprising at least one turbomachine of the aforementioned type. The aircraft may be rotary wing. Brief description of the figures

[0027] The invention will be better understood and other characteristics and advantages will become apparent upon reading the detailed description which follows, comprising embodiments given for illustrative purposes with reference to the appended figures, presented as non-limiting examples, which may serve to supplement the understanding of the present invention and the description of its embodiment and, where appropriate, contribute to its definition, in which:

[0028] [fig. 1] is a schematic view of a power supply and control system for an actuator according to a first embodiment of the invention,

[0029] [fig.2] is a schematic view of a power supply and control system of a actuator according to a second embodiment of the invention,

[0030] [fig.3] is a schematic view of a power supply and control system of a actuator according to a third embodiment of the invention,

[0031] [fig.4] is a schematic view of a power supply and control system of a actuator according to a fourth embodiment of the invention,

[0032] [fig.5] is a schematic view of a power supply and control system of a actuator according to a fifth embodiment of the invention,

[0033] [fig.6] is a schematic view of a power supply and control system of a actuator according to a sixth embodiment of the invention,

[0034] [fig.7] is a schematic view of a power supply and control system of a actuator according to a seventh embodiment of the invention,

[0035] [fig.8] is a schematic view of a power supply and control system of a actuator according to an eighth embodiment of the invention,

[0036] [fig.9] is a schematic view of a subassembly of a power supply system and control according to the invention intended for another type of application,

[0037] [fig.10] is a schematic sectional view of the actuator and at least one alternator of the power supply and control system according to the invention. Detailed description of the invention

[0038] [fig.l] is a schematic representation, according to a first embodiment of the invention, of a power supply and control system 1 of an actuator 2, in particular intended to equip an aircraft.

[0039] The actuator 2 is, for example, intended for the actuation of air intake flaps or variable-pitch blades of a turbomachine, such as for example a turbojet, a turboprop of an aircraft or a turboshaft of a helicopter.

[0040] The power supply and control system 1 comprises an electric motor 3 housed in an actuator housing 4. The electric motor 3 is capable of driving a movement of a movable member 5 of the actuator 2.

[0041] The electric motor 3 of the actuator 2 may be a direct current motor, a synchronous motor, an asynchronous motor, a stepper motor or any other type of electric motor.

[0042] According to the first embodiment, the power supply and control system 1 may further comprise a first alternator 6 and a second alternator 7, respectively capable of generating an electrical power supply.

[0043] The first alternator 6, respectively the second alternator 7, comprises a rotor driven in rotation by a first input shaft 8, respectively a second input shaft 8'. The first alternator 6, respectively the second alternator 7, advantageously provides an alternating voltage at the output.

[0044] The first input shaft 8, respectively the second input shaft 8', can be driven by a turbine, in particular via a reduction and drive box, for example accessories, by a gas generator or by a shaft of a turbine, in particular via a reduction gear, of the turbomachine.

[0045] The first alternator 6 supplies an electronic power module 9. According to the particular embodiment presented, the power supply of the electronic power module 9 by the first alternator 6 is done via first voltage rectification means 10, in particular capable of transforming the alternating voltage supplied at the output of the first alternator 6 into a direct voltage.

[0046] The electronic power module 9 makes it possible to power the electric motor 3 of the actuator 2. The electronic power module 9 may comprise electronic power components, such as in particular diodes, MOSFETs, transistors, in particular bipolar power transistors, IGBTs, thyristors.

[0047] The electronic power module 9 is capable of being controlled by a power control module 11.

[0048] The electronic power module 9 can receive, as input, a control signal from the power control module 11 and provide, as output, a voltage and a supply current for the electric motor 3 of the actuator 2.

[0049] Advantageously, the first alternator 6, the first rectification means of the voltage 10, the power electronic module 9 and / or the electric motor 3 are housed in at least one actuator housing 4.

[0050] According to the first embodiment, the second alternator 7 supplies the power control module 11. According to the particular embodiment presented, the power control module 11 is supplied by the second alternator 7 via second rectifier means 12.

[0051] In addition, the power supply and control system 1 may comprise first selection means 13. In particular, the power supply of the power control module 11 by the second alternator 7 may also be done via the first selection means 13.

[0052] As a particular example of embodiment, the first voltage rectification means 10, respectively the second voltage rectification means 12, may comprise, for example, a diode bridge, an active rectification, in particular based on transistors, IGBTs or MOSFETs etc.

[0053] According to an alternative embodiment of the invention, the first selection means 13 are powered by the second alternator 7 and by a separate electrical distribution network 14. The separate electrical distribution network 14 may, for example, be a distribution network of an aircraft.

[0054] Thus configured, the first selection means 13 are capable of powering the power control module 11 using the electrical power supplied by the second alternator 7 and / or the separate electrical distribution network 14.

[0055] The electrical distribution network 14 can then be used to supply the power control module 11, for example in the event of a breakdown of the second alternator 7, during the shutdown or startup phase of the turbomachine when the rotor of the second alternator 7 is stopped, or even during the startup phase of the turbomachine when the rotational speed of the rotor of the second alternator 7 is too low to provide sufficient electrical power to the other elements of the power supply and control system 1.

[0056] The power supply and control system 1 may also comprise a computer 15 comprising a computer housing 16. According to a particular embodiment, the power control module 11, the second voltage rectification means 12 and / or the first selection means 13 are housed in the computer housing 16.

[0057] The computer 15 may be a computer for regulating the turbomachine of an aircraft.

[0058] [Fig. 2] illustrates a second embodiment of the invention. The second embodiment of the invention differs from that illustrated in [Fig. 1] in that the first alternator 6 is used to power the electronic power module 9. and the power control module 11.

[0059] The power supply of the electronic power module 9 and of the power control module 11 by the first alternator 6 is done via the first rectification means 10 and the second voltage rectification means 12 respectively. In a complementary manner, the power supply of the power control module 11 by the first alternator 6 can also be done via the first selection means 13.

[0060] In this second embodiment of the invention, the first alternator 6 supplies, in particular in parallel, on the one hand, the first voltage rectification means 10 and, on the other hand, the second voltage rectification means 12.

[0061] [Fig. 3] illustrates a third embodiment of the invention. The third embodiment of the invention differs from that illustrated in [Fig. 2] in that the first voltage rectification means 10 are used at the output of the first alternator 6 to power, on the one hand, the electronic power module 9 and, on the other hand, the power control module 11, in particular via the first selection means 13.

[0062] In this third embodiment of the invention, the first voltage rectification means 10 supply, in particular in parallel, on the one hand, the electronic power module 9 and, on the other hand, the power control module 11.

[0063] [Fig. 4] illustrates a fourth embodiment of the invention. The fourth embodiment of the invention differs from that illustrated in [Fig. 1] in that the first input shaft 8 is used to actuate the first alternator 6 and the second alternator 7. Advantageously, the first alternator 6 and the second alternator 7 are then housed in the actuator housing 4.

[0064] In this fourth embodiment of the invention, the first alternator 6 supplies the first voltage rectification means 10 and the second alternator 7 supplies the second voltage rectification means 12.

[0065] In addition, the second alternator 7 supplies the power control module 11. According to this particular embodiment presented, the power control module 11 is supplied by the second alternator 7 via the second rectifier means 12.

[0066] In addition, the power supply and control system 1 may comprise the first selection means 13. In particular, the power supply of the power control module 11 by the second alternator 7 may also be done via the first selection means 13.

[0067] [Fig. 5] illustrates a fifth embodiment of the invention. The fifth embodiment of the invention differs from that illustrated in [Fig. 4] in that the first input shaft 8 actuating the first alternator 6 and the second alternator 7 is arranged so as to be coaxial with the movable member 5 of the actuator 2.

[0068] In the case where the movable member 5 of the actuator 2 is a rotary shaft, the directions of rotation of the movable member 5 of the actuator 2 and of the first input shaft 8 are chosen so that, in the event of breakage of the first input shaft 8, any friction between the movable member 5 and the first input shaft 8 drives the movable member 5 of the actuator 2 in a preferred direction of rotation, for example causing the air inlet flaps (IGV) of the turbomachine to open.

[0069] The movable member 5 of the actuator 2 may be a shaft capable of being driven in rotation or a rod capable of being moved in translation. In such a case, the conversion of movement between the motor 3 of the actuator 2 and the rod may be carried out by a conversion mechanism of the worm screw, roller screw, ball screw, or any other type of mechanism.

[0070] [Fig. 6] illustrates a sixth embodiment of the invention. The sixth embodiment of the invention differs from that illustrated in [Fig. 5] in that second selection means 17 are interposed between the first rectifier means 10 and the electronic power module 9. Preferably, the second selection means 17 are powered by the first alternator 6, in particular via the first rectifier means 10, and by the separate electrical distribution network 14. The second selection means 17 are capable of powering the electronic power module 9 using the electrical power supply from the alternator 6 and / or the separate electrical distribution network 14. Advantageously, the operation of the second selection means 17 is similar to that of the first selection means 13 described previously.

[0071] Generally, the first selection means 13 and the second selection means 17 constitute electrical power supply selection means 13, 17 making it possible to electrically power the power control module 11 and / or the electronic power module 9 via the electrical power supplied by the alternator 6, by the second alternator 7 and / or by the separate electrical distribution network 14.

[0072] [Fig. 7] illustrates a seventh embodiment of the invention. The seventh embodiment of the invention differs from that set out with reference to [Fig. 6] in that the power control module 11 is housed in the housing 4 of the actuator 2. According to this alternative embodiment of the invention, the power control module 11 is no longer arranged in the computer housing 16 but is advantageously arranged in the actuator housing 4. The second selection means 17 then supply the electronic power module 9 and the power control module 11.

[0073] In a complementary manner, the power supply and control system 1 can comprise a position control module 18, for example located outside the actuator housing 4. The position control module 18 is capable of providing, to the power control module 11, a signal indicative of a position to be reached by the movable member 5 of the actuator 2. The power control module 11 is then capable of controlling the electric motor 3 of the actuator 2 as a function of the signal from the position control module 18.

[0074] According to the particular embodiment presented, the position control module 18 is housed in the computer housing 16. Preferably, the position control module 18 is powered by the second voltage rectification means 12, in particular via the first selection means 13.

[0075] The power control module 11, in particular when it is housed in the actuator housing 4, may comprise control means capable of positioning the movable member 5 of the actuator 2 in a safety or collection position, in the event, for example, of loss of the position signal from the position control module 18.

[0076] [Fig. 8] illustrates an eighth embodiment of the invention. The eighth embodiment of the invention differs from that set out with reference to [Fig. 7] in that the first alternator 6 and the second alternator 7 are respectively arranged in a first subassembly E1 and a second subassembly E2. Advantageously, the first subassembly E1, respectively the second subassembly E2, is mounted in a modular manner on a main subassembly E3. According to a particular arrangement, the main subassembly E3 may comprise the actuator 2, the power control module 11, the power electronic module 9, the second selection means 17 and / or the first voltage rectification means 10.

[0077] In the various embodiments described above, the first alternator 6 and the second alternator 7 can provide identical or different voltage levels.

[0078] [Fig. 9] is a schematic view of a subassembly of a power supply and control system 1. [Fig. 9] illustrates the case where such a subassembly comprising the first alternator 6 is used for another type of application in which the first alternator 6 supplies the first selection means 13 of the aforementioned type, via the second voltage rectification means 12. According to this alternative embodiment of the invention, the first selection means 13 and the second voltage rectification means 12 are housed in the computer housing 16.

[0079] [Fig. 10] is a schematic sectional view of the actuator 2 and at least one first coaxial alternator 6 and one second coaxial alternator 7, suitable for use in the power supply and control system 1 according to the invention.

[0080] According to the exemplary embodiment presented, the actuator 2 comprises, as previously described, the electric motor 3, located in a cold or upstream zone AM of a turbomachine. The electric motor 3 drives a rotor coupled in rotation to the mobile member 5, in particular a rotary shaft, extending into a hot downstream zone AV of the turbomachine. The terms upstream and downstream are defined relative to the direction of circulation of the gases within the turbomachine.

[0081] The first alternator 6, respectively the second alternator 7, comprises coils 6a, respectively coils 7a, and at least one rotor coupled to the first input shaft 8, coaxial with the movable member 5 of the actuator 2.

[0082] In this configuration, the first input shaft 8 surrounds the movable member 5 of the actuator 2. More specifically, the first input shaft 8 is crossed by the movable member 5 of the actuator 2. The coils 6a, respectively the coils 7a, are arranged in the actuator housing 4, with the electric motor 3.

[0083] The first input shaft 8 of the first alternator 6 and of the second alternator 7 is driven through transmission means, in particular gears, belonging to a reduction and drive box 20, in particular accessories, of the turbomachine, such as the turbojet, the turboprop of an aircraft or the helicopter turbomotor.

[0084] The electronic power module 9 may be located in the actuator housing 4, as previously described, and / or in the reduction and drive housing 20. In addition, the actuator housing 4 and / or the reduction and drive housing 20 also comprises electrical connectors 21.

[0085] Obviously, the invention is not limited to the embodiments described above and provided solely by way of example. It encompasses various modifications, alternative forms and other variants that may be envisaged by those skilled in the art within the framework of the invention and in particular all combinations of the different operating modes described above, which may be taken separately or in association.

Claims

Claims

1. Power supply and control system (1), comprising: - an actuator (2) comprising - an actuator housing (4), and - at least one motor (3) housed in the actuator housing (4) and capable of driving a movement of a movable member (5) of the actuator (2), - at least one first alternator (6) and / or a second alternator (7), capable of generating an electrical power supply, - an electronic power module (9) powering the motor (3) of the actuator (2) and powered by the first alternator (6) and / or the second alternator (7), and - a power control module (11), capable of controlling the electronic power module (9), characterized in that the electronic power module (9), the first alternator (6) and / or the second alternator (7) are housed in the actuator housing (4).

2. Power supply and control system (1) according to the preceding claim, characterized in that it comprises first voltage rectification means (10) arranged between the first alternator (6) and the electronic power module (9) and / or second voltage rectification means (12) located between the second alternator (6) and the power control module (11).

3. Power supply and control system (1) according to claim 2, characterized in that the first voltage rectification means (10) and / or the second voltage rectification means (12) supply the power electronic module (9) and / or the power control module (11).

4. Power supply and control system (1) according to one of the preceding claims, characterized in that the first alternator (6), respectively the second alternator (7), comprises a rotor driven by a first input shaft (8), respectively by a second input shaft (8'), or in that the first alternator (6) and the second alternator (7) respectively comprise a rotor driven by the same first input shaft (8), and in that the first input shaft (8), respectively the second input shaft (8'), is arranged so as to be coaxial with the movable member (5) of the actuator (2).

5. Power supply and control system (1) according to one of the claims- preceding indications, characterized in that it comprises electrical power supply selection means (13, 17) supplied by the first alternator (6), by the second alternator (7) and / or by a separate electrical distribution network (14) and capable of supplying the power control module (11) and / or the electronic power module (9).

6. Power supply and control system (1) according to one of the preceding claims, characterized in that it comprises a position control module (18), in particular located outside the actuator housing (4), capable of controlling the motor (3) of the actuator (2) as a function of a signal indicative of a position to be reached by the movable member (5) of the actuator (2) supplied by the position control module (18) to the power control module (11).

7. Power supply and control system (1) according to claim 6, characterized in that the position control module (18) is housed in a housing of a computer (16) and / or in that the control module (11) is housed in the actuator housing (4) or in the computer housing (15).

8. Power supply and control system (1) according to one of the preceding claims, characterized in that at least the first alternator (6) and / or at least the second alternator (2) is arranged in a first subassembly (El) and / or a second subassembly (E2) mounted modularly on a main subassembly (E3) comprising at least the actuator (2).

9. Aircraft turbomachine, comprising at least one power supply and control system (1) according to any one of the preceding claims.

10. Aircraft comprising at least one turbomachine according to the preceding claim.

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