• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
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    • 专利摘要:
    The rapid assistance device applies to a turbine engine (11) free turbine of an aircraft comprising at least a first turbine engine (11) free turbine equipped with a gas generator, associated with an electric machine (12) operable as a starter and a generator, the first turbomachine (11) being able to be put in standby mode or in the unwanted extinction mode, the electric machine being powered from an onboard power supply network (17). electric energy. The device furthermore comprises at least one electrical energy storage device (14) adapted to be electrically connected to the electric machine (12) associated with the first turbomachine (11) to provide punctual assistance to the gas generator of this turbomachine (11). The electrical energy storage member (14) is a so-called "primary" non-rechargeable energy storage device that can be used once. The device comprises an activation system of the electrical energy storage member (14) and a device (15) for coupling the electrical energy storage member with a power supply system (13, 16). ) of the electric machine (12).
    公开号:FR3024707A1
    申请号:FR1457671
    申请日:2014-08-07
    公开日:2016-02-12
    发明作者:Thomas Klonowski；Michel Nollet；Frederic Pailhoux
    申请人:Sagem Defense Securite SA；Turbomeca SA；Labinal Power Systems SAS；
    IPC主号:
    专利说明:

    [0001] Technical Field The invention is in the field of free turbine turbomachines, as commonly found on helicopters. For the record, a turbomachine (sometimes designated by the acronym TAG) free turbine comprises a power turbine or free turbine which, in a helicopter, drives the rotors thereof via a free wheel and a main transmission box (hereinafter referred to as MGB), and also a gas generator consisting mainly of a compressor, a combustion chamber and a high pressure turbine. A mechanical gearbox or accessory box makes it possible to connect the shaft of the gas generator to an electric machine (abbreviated to MEL) consisting of a stator and a rotor, which can operate indifferently in motor (starter) or in generator. In the motor mode, the electric machine is powered by a source of electrical energy and develops a motor torque so as to rotate the gas generator of the turbomachine, in particular for the purpose of ensuring startup, thereby performing start-up assistance. In the generator mode, the electric machine is rotated by the gas generator so as to take on the latter a mechanical power which is then converted into electrical power. State of the art When an aircraft equipped with two turbomachines is in a cruising flight situation, it has been proposed in documents FR2967132 and FR2967133 to put one of the two turbomachines in a standby mode so as to desynchronize its free turbine from the transmission gearbox while increasing the speed of the other turbomachine, which reduces the overall fuel consumption of the system. The invention is thus particularly in the context of a reduction of the consumption of a helicopter at least twin engine, in which in economic flight 3024707 2, that is to say in a flight phase characterized by a the power demanded for each relatively small motor resulting in a very high specific consumption (abbreviated to CS), one of the turbines is put in a standby mode so that the other engine operates at a high speed and thus benefits from a consumption specific much lower. Several variants of this watch regime have been proposed. In a first variant, called "super idle", the gas generator of the desynchronized gas turbine can be regulated at a low idle speed. In a second variant, called "assisted super idle", the gas generator of the BTP desynchronized gas turbine can also be regulated at a low idle speed, and simultaneously an assist engine torque is applied to the generator. gas through the electric machine and the accessory box. In a third variant, the combustion chamber of the turbomachine 15 can be completely extinguished, and it is then proposed to keep the gas generator rotating at a speed to facilitate re-ignition at the end of the cruise flight phase. . The range of adapted speeds can be qualified as a preferential ignition window. This operating mode, called "turning" mode, is a prolonged assistance of the gas generator.
    [0002] In these three modes of operation, which are likely to be maintained throughout the cruising flight time, the power transmitted to the BTP by the turbomachine in standby is generally zero, and it is generally not possible to collect power on its gas generator. In the three variants that have just been mentioned, it is necessary to be able to quickly reactivate the desynchronized turbomachine, especially in an emergency situation, for example in case of failure of another turbomachine, if there is has three or more turbomachines in total, - or the other turbomachine if the turbomachines are two in number. This is particularly the reason for keeping the gas generator rotating at a speed facilitating reignition in the system 30 where the combustion chamber is extinguished. The maintenance of the gas generator in rotation in the preferential ignition window ("turning" mode) and the prolonged assistance to the gas generator 3024707 3 regulated at idle (mode "super assisted idle") require for their part a power enough low but in the end a significant energy, the interest of the system residing in its use during a long period of flight. It has been proposed in documents FR2967132 and FR2967133, among other solutions, to use an electric starter powered by a starter / generator connected to the gas generator of the other turbomachine, or a generator driven directly or indirectly by the free turbine of the other turbomachine. As for the emergency restart from a low-speed situation or a burned-out combustion chamber, it requires the application of high power to the generator shaft because of the high inertia of the rotating assemblies and the Resistant torque of the compressor of the turbomachine. This power must be delivered for a short time, of the order of a few seconds, in order to guarantee a fast start of the turbomachine. It has been suggested in document FR2967133 to use, among other solutions, an electrical energy, in particular a supercapacitor, which provides punctual assistance to the gas generator. In the document EP2581586, it has also been proposed to use two supercapacitors (which are electrical storage devices), each of which is respectively charged by an electric generator driven by the gas generator of one of the two turbomachines, and which serve each, punctually, to start the other turbomachine from an off state thereof. The object of the present invention is, in this context, to provide a practical technical means of producing, on an aircraft which is at least twin-engine, the function of "quick reactivation" from an economic mode of the turbine, by using in place and place of the conventional electric starter an electrotechnical system powered by the on-board network or by a specific electrical power supply network and making it possible to ensure different modes of operation which are: - The ground start of the gas turbine, - The economic mode, - The reactivation in flight of the turbine, which was previously in economic mode, and 3024707 4 - The rapid reactivation in flight of the turbine, which was previously in economic mode. Another object of the present invention is to make it possible to efficiently perform, on a single-engine aircraft, a function of rapid reactivation of a turbomachine, in the event of the occurrence of an undesired extinction mode, by using instead of the conventional electric starter an electrotechnical system powered by the on-board network or by a specific power supply network. The invention is particularly in the context of the French patent application No. 1400753 filed March 27, 2014 and is more particularly intended to provide an electrical system architecture giving a way to ensure improved so-called rapid reactivation mode. in flight of the gas turbine. The architectures of the electrical systems proposed hitherto for the hybridization of a gas turbine still use a so-called "secondary" storage element on the HVDC bus (so-called "High Voltage Direct Current") which has the power reserve function necessary for the fast reactivation mode. "Secondary" means that these storage elements are rechargeable. Most require an electrical management body called BMS (Battery 20 Management System). The existing solutions thus have several drawbacks, the main ones of which are as follows: 1 / The BMS, independently of the technology of the secondary storer (Li-Ion battery, NiMH, supercapacity, hybrid capacities, etc.), is a so-called equipment 25 complex since it includes power switching devices and uses electronics to control the state of charge, operating parameters and health status of the storage organ, and therefore governed by avionics certification standards. , such as RTCA DO-178 and DO-254 ("Radio Technical Commission for Aeronautics").
    [0003] 3024707 5 The BMS increases the weight of the system and its probability of failure. 2 / The known secondary pairs have a significant self-discharge rate, which requires periodic recharging of the battery and therefore requires the presence of a charger, either in the aircraft or in the ground infrastructure. 3 / Secondary pairs deteriorate little by little even when they are only rarely used (so-called calendar aging). This requires testing and replacing them periodically. 4 / These so-called secondary storage members have the further disadvantage of being always active, that is to say that the system can provide electrical energy at any time in undesired cases such as the short ones. -circuits, or be discharged prematurely by a phenomenon of leakage current. 5 / These secondary storage members have another general disadvantage which is the resistance to harsh environments, such as cold and hot temperatures, as well as mechanical stress (vibrations, shocks). To cope with these environmental constraints, these secondary organs must be dimensioned accordingly, which results in an unfortunate increase in the mass of the system to board an aircraft and more particularly a helicopter. Another disadvantage of certain secondary storage organ technologies is the dangerous nature of these elements in the event of thermal runaway, which thermal runaway may be caused in particular by external or internal short circuits to the secondary storage devices, by overload, or other environmental causes. 7 / The coupling to the onboard network of a secondary storer is problematic considering the interactions between a network whose voltage can vary at any time, and a secondary battery whose voltage is a function of the state of charge. Precautions must therefore be taken (which leads to a complexification of the system) to avoid any electrical risk, or even any risk of operational unavailability of the storer.
    [0004] SUMMARY OF THE INVENTION In order to overcome the aforementioned drawbacks, in accordance with the invention, there is provided a rapid assistance device for a free turbine turbine engine of an aircraft comprising at least one first turbine engine equipped with a free turbine. a gas generator, associated with an electric machine operable as a starter and a generator, the first turbine engine can be put in standby mode or in the unwanted extinguishing mode, the electric machine being connected to a specific network of supply of electrical energy, such as an on-board network, the device further comprising at least one electrical energy storage member adapted to be electrically connected to said electrical machine associated with said first turbomachine to provide one-off assistance to the generator of this turbomachine, characterized in that said energy storage member is The trunk is a so-called "primary" energy storage device which is non-rechargeable and can be used only once, and in that the device comprises means for activating the electrical energy storage device and means for coupling the electrical energy. electrical energy storage member with a power supply system of said electric machine. According to a first possible embodiment, the electrical energy storage member comprises a low-self-discharge ready-to-use device incorporating an anode and a cathode in contact with an electrolyte. According to a second possible embodiment, the electrical energy storage member comprises an inert device before its activation, integrating an anode, a cathode and an electrolyte which does not wet the anode and the cathode.
    [0005] In this case, the electrical energy storage member may comprise a separate electrolyte cell, with a separate electrolyte storage tank, and electrolyte release means out of the separate reservoir to enable it to come in contact with the anode and the cathode during the activation of the electrical energy storage member.
    [0006] Alternatively, the electrical energy storage member may comprise a thermal battery adapted to maintain the solid electrolyte at room temperature during storage and to liquefy the electrolyte by heating upon activation of the electrolyte. the electrical energy storage member. The activation means of the electrical energy storage member may comprise pyrotechnic activation means.
    [0007] According to another possible embodiment, the activation means of the electrical energy storage member comprise electrical activation means. According to a particular embodiment, the electrical energy storage member is connected in parallel with said specific power supply network 10 which can be a continuous electrical energy supply on-board network. A non-return diode may be interposed if necessary between the electrical energy storage member and the continuous edge network. This continuous edge network is itself normally powered by the alternating electrical power supply mains network, via a rectifier or an AC-DC converter. According to another particular embodiment, the electrical energy storage device is connected in series with the rectifier or the AC-DC converter which produces the DC network voltage from the specific power supply network as shown in FIG. as an alternating edge network and in parallel with a diode. The diodes may be semiconductors or electromechanical or static type controlled switches. In general, the electrical energy storage member may comprise one or more elements or batteries of elements connected in series, in parallel or in series-parallel. According to a particular embodiment, the rapid assistance device is applied to an aircraft free turbine engine comprising a plurality of free turbine turbomachines each equipped with a gas generator, each associated with an electric machine that can operate. in a starter and generator, at least one of the plurality of turbomachines can be put in standby mode, while at least one other of the plurality of turbomachines is in normal operating mode.
    [0008] In this case, according to a particular embodiment, the rapid assist device according to the invention comprises a single electrical energy storage member adapted to be electrically connected by a switching or switching device to the machine. electrical associated with that of the plurality of turbomachines requiring punctual assistance to the gas generator of the turbomachine previously put into standby mode. The invention also relates to an aircraft with at least one free turbine turbine engine, comprising an assistance device as evoked. The aircraft can be a helicopter.
    [0009] BRIEF DESCRIPTION OF THE FIGURES Other features and advantages of the invention will become apparent from the detailed description of particular embodiments of the invention, with reference to the accompanying drawings, in which: Figure 1 shows a schematic of a device device according to a first embodiment of the invention, with a primary energy element connected in parallel with an aircraft on-board network. FIG. 2 shows a diagram of a fast assistance device according to a first embodiment of the invention. a second embodiment of the invention, with a primary energy element 20 connected in series with an aircraft on-board network, FIG. 3 presents a diagram showing the integration of a system according to the invention in a propellant and electrical systems of an aircraft, FIG. 4 shows a diagram of a rapid assistance device according to a third embodiment of the invention, with a single primary energy element FIG. 5 is a schematic diagram of a rapid assist device according to a fourth embodiment of the invention, with a single primary energy element connected in series. with an aircraft onboard network.
    [0010] DETAILED DESCRIPTION With reference to FIG. 3, the general electrical architecture of an exemplary system to which the invention is applicable is as follows. The electrical generation of an aircraft is provided by at least two alternators (abbreviated as ALTI_ and ALT2) 18, 19 driven by a power transmission gearbox (abbreviated to BTP) 20, and 5 typically constituted by 115VAC / 400Hz machines. type "3 floors", other rotating machines are conceivable. This architecture is advantageous in the context of economic single-engine cruising flight, because it guarantees a functional and organic independence between electrical generation and operation of the turboshaft engines 11, 21, 10 thus making it possible to maintain a sufficient level of availability and redundancy for the electrical generation in economic cruising flight, when one of the two turbomachines 11, 21 is maintained in a standby mode incompatible with any power draw on the gas generator of the turbomachine in standby mode.
    [0011] Moreover, this architecture is less penalizing for the operation of the turbine engines 11, 21 than a sampling at the gas generators of the turboshaft engines 11, 21, in particular in terms of impact on the acceleration and specific consumption performance, in the extent to which the mechanical sampling corresponding to the electrical power consumed by the aircraft 17 edge network is effected on the free turbine side and not on the gas generator. Alternators 18, 19 (ALTI_ and ALT2) feed the electrical network 17 of the aircraft. Thus, the onboard network 17 is powered by one or more alternators 18, 19 actuated, directly or indirectly by at least one of the turbomachines 25, 11, 21. When one of the turbomachines 11, 21 is extinguished, it is necessarily necessary to other which supplies power to the on-board network 17 in a prolonged manner. However, other sources of energy available for supplying this network 17, which, in particular, serves to supply the entire associated electrical system 100 the turbomachines 11, 21 may be constituted by an auxiliary power unit 30 of embedded power 53 (abbreviated as APU corresponding to the acronym of the English expression "Auxiliary Power Unit"), one or more storage batteries 51, or, at ground, a park catch 52.
    [0012] The power transmission gearbox 20 (BTP) is driven by the turbomachines 11, 21. These are free turbine turboshaft engines. They each comprise a power turbine (free turbine) driving the BTP 20 via a free wheel, and a gas generator.
    [0013] Each turbine engine 11, 21 is associated with a rotating machine 12, 22 respectively capable of operating as a starter as a generator, and which can be powered from the aircraft's on-board network 17 via a system 50 of electrical control including the device according to the invention. Reference will be made to FIGS. 1 and 2 of first and second embodiments of the invention. FIGS. 1 and 2 show, in addition to the turbomachines 11 and 21 and the alternating edge network 17, examples of the electrical assembly 100 of FIG. 3 which constitutes an electric starting system that can be applied to the turbine engine 11 or to the turbine engine 21 In the embodiment of FIG. 1, there is shown, for the turbine engine 11, an electrical starting system comprising an AC / DC converter 16, also called an AC / DC converter, fed from the alternating edge network. and a DC / AC converter 13, also called DC / AC converter, connected to the AC / DC converter 16 and providing power to the electric machine 12, also called MEL. Alternate edge network 17 and AC / DC converter 16 define a continuous electrical power supply network (output voltage Vcc), but other embodiments of continuous network are possible. According to the invention, a diode 15 may be connected between the DC / AC converter 13 and the AC / DC converter 16. This diode is useful when the DC network is used by other equipment than the MEL 12. It allows to reserve the MEL 12 all the power produced by the storer 14 (which will be described later) when the voltage produced by the storer 14 is greater than the voltage Vcc of the DC network. It allows the continuous network to contribute to the supply of the MEL 12 when the voltage produced by the storage 14 is lower than the voltage Vcc of the continuous network. The anode of the diode 15 is connected to the positive pole of the output of the AC / DC converter 16 and the cathode of the diode 15 is connected to the positive pole of the DC / DC converter 13. Naturally, in an equivalent manner, the cathode of the diode 15 may be connected to the negative pole of the output of the AC / DC converter 16, while the anode of the diode 15 is connected to the negative pole of the DC / AC converter 13. The diode 15 may be a semiconductor , or a controlled switch 5, static or electromechanical. Furthermore, a primary storage unit 14, that is to say a non-rechargeable electrical energy storage member that can only be used once, is connected in parallel with the converters 13 and 16, the positive pole of the primary storage unit 14 being connected to the cathode of the diode 15 and the negative pole of the primary storage being connected to the negative poles of the converters 13 and 16. The primary storage 14 is optimized for brief and intense power discharges. It may be, for example, a low-self-discharge ready-to-use device incorporating an anode and a cathode in contact with an electrolyte. The primary storer 14 may, however, be an inert device prior to activation, incorporating an anode, a cathode, and an electrolyte which does not wet the anode and the cathode. In this case, the electrical energy storage member 14 may comprise a separate electrolyte cell, with a separate electrolyte storage tank, and electrolyte release means out of the separate reservoir to allow it to be electrolytically separated. come into contact with the anode and the cathode during activation of the electric energy storage member 14. Alternatively, in the case of an inert device before its activation, the storage member The electrical energy supply 14 may comprise a thermal battery adapted to maintain the solid electrolyte at ambient temperature during storage and to liquefy the electrolyte by heating upon activation of the electrical energy storage member 14. primary electric energy store 14 is activated when the turbine engine 11 must be restarted urgently. The activation means of the electrical energy storage member 14 may comprise, for example, pyrotechnic activation means or else mechanical activation means or electric activation means.
    [0014] In the embodiment of FIG. 1, the electrical energy storage device 14 is connected in parallel with the continuous electric power supply supply network Vcc, but because a diode 15 is interposed between the electrical energy storage member 14 and the AC-DC converter 16 supplied by the reciprocating edge network 17, when the electrical energy storage member 14 is activated by an activation means, not shown in the drawings, to provide the energy necessary for the rapid reactivation of the turbomachine 11 previously idle, the electrical voltage across the storage member 14 may be greater than the level of the voltage Vcc of the continuous network delivered by the network The diode 15 then has a negative potential difference between its anode and its cathode and is in a locked state. The electrical energy required for the rapid reactivation of the gas turbine of the turbomachine 11 is thus entirely delivered by the primary energy store 14, which has the advantages of sending to the MEL 12 all the power supplied. by the storer 14 and not to raise the voltage Vcc of the continuous onboard network of the aircraft. In the case where the voltage delivered by the storage unit 14 loaded by the DC / AC converter 13 and the MEL 12 is less than the voltage Vcc of the continuous network, the diode 15 conducts, allowing the continuous network to participate in the power supply. the MEL 12. Finally, if it is not desired that the continuous network participates in the supply of the MEL 12 when the voltage of the storage unit 14 is lower than that of the continuous network, and since, as stated above, the diode 15 can be a controlled switch, it can be controlled switch 15 so that it does not lead in this case.
    [0015] FIG. 1 shows, in cooperation with the second turbomachine 21 and the second electric machine 22, elements 23 to 26 corresponding respectively to the elements 13 to 16 cooperating with the first turbomachine 11 and the first electric machine 12. Items 23 to 26 will not be described again. The elements 23 to 26 play a role similar to that of the elements 13 to 16 previously described, if the turbine engine 11 is in high-speed operation while the turbomachine 21 is in standby mode and is likely to be subject to 'rapid reactivation.
    [0016] Since it is never necessary to restart turbomachines 11 and 21 at the same time, it is in fact possible to only board a storer 14 to restart one or other of the two turbomachines 11 and 21. An electronic or electromechanical switching member 38, 48 connects the single storer 14 to either the DC / AC converter 13 (as shown in FIG. 4 with the switch 38 in the closed position and the switch 48 in the open position), or on the DC / AC 23 converter as needed. As shown in FIG. 4, it is possible to use not only a single storer 14, but also a single diode 15 and a single AC / DC converter 16, when organs are available. turnout 38, 48 for the storage 14 sends its energy to the MEL 12 or the MEL 22. The embodiment of Figure 4 and differs from that of Figure 1 by removing the elements 24 to 26. Furthermore the switching function is very simple to achieve using the contactors 38, 48 which are simple on-off commands 15 ("on / off") DC / AC converters 13 and 23. Alternatively, the DC / AC converter 23 of Figure 4 could also be deleted. In this case, the on-off switches 38, 48 could be suppressed and on-off switches would be arranged not on the DC input side of the DC / AC converters 13 and 23, but on the interface between the MEL 12, 22 and the AC output of the DC / AC converter 13. Thus, all or part of the element chains 13 to 16 and 23 to 26 can be made with single elements, the switching being done where the chain doubles. It is also possible to provide that only a turbomachine, for example the turbomachine 11, will be able to be put in standby, while the other turbomachine 21 will still be operating at high speed, in which case the elements 24 and 25 could be omitted without a switching function is necessary, since no rapid reactivation would be implemented for this second turbine engine 21.
    [0017] FIG. 2 shows another embodiment, which is similar to that of FIG. 1, and comprises similar elements which bear the same reference numerals and will not be described again, but in which the primary storer respectively 124 is associated with a diode 115 respectively 125. In FIG. 2, thus, according to the second embodiment of the invention, a primary storage unit 114, that is to say an energy storage member, is thus seen. 5, which is connected in parallel with a diode 115, between the converters 13 and 16, the negative pole of the primary storage unit 114 being connected to the anode of the diode 115 and to the positive pole of the converter AC / DC 16, and the positive pole of the primary storage 114 being connected to the cathode of the diode 115 and to the positive pole of the DC / AC converter 13.
    [0018] When the primary storer 114 is not in use, the MEL 12 can be fed by the continuous on-board network via the diode 115. If the turbomachine 11 previously idle must be reactivated quickly, the diode 115 is blocked and the primary storage 114 is connected in series with the converters 13 and 16.
    [0019] The primary energy store, when activated, is thus in series with the onboard network 17 associated with the AC / DC converter 16. The electrical energy required for the rapid reactivation of the gas turbine of the turbomachine 11 will be delivered by the primary energy storage 114 and the onboard network 17, which compared to the solution of the embodiment of Figure 1 allows to undersize the energy store 114 in terms of power and energy to deliver. Nevertheless, the DC / AC converter 13 must be dimensioned so as to admit the voltage that results and allow to pass all the electrical power necessary for rapid reactivation. This solution of the embodiment of FIG. 2 optimally sizing the supply voltage during the fast reactivation which will be the sum of the voltages delivered by the primary storage unit 114 and the voltage Vcc at the output of the rectifier 16. this will minimize the intensity of the current flowing in the overall electrical circuit. The storer 114 meanwhile can be sized to provide a voltage lower than the voltage level generated in the solution of Figure 1, which will have the advantage of reducing the mass and bulk of this body.
    [0020] As compared with the solution of the embodiment of FIG. 1, the solution of the embodiment of FIG. 2 presents a lack of autonomy with respect to the on-board network 17, so that, depending on the applications it may be necessary to add filter elements upstream of the converter 16, in order to meet the requirements of network stability. In the embodiment of FIG. 2, the elements 23, 124, 125 and 26 associated with the second turbomachine 21 and the second electric machine 22 play the same role as the elements 13, 114, 115 and 16 associated with the first turbomachine 11 and the first electric machine 12, but 10 intervene in the case where it is the second turbine engine 21 which is put on standby and is likely to be subject to rapid reactivation, while the first turbomachine 11 is in high speed operation. As in the first embodiment, it is however possible to direct a single storer 114 to the turbomachine 11 or to the turbine engine 21 or 15 to assign for example to the only first turbomachine 11 the role of being in standby mode , in which case it would be possible to omit the elements 124 and 125. FIG. 5 shows a particular embodiment in which a single storer 114, a single diode 115 and a single AC / DC converter 16 are used. In this case it is possible to , as in FIG. 4, use two on-off switches 38, 48 or simply turn the DC / AC converters 13, 23 on or off, or use a switching element 39, shown in FIG. FIG. 5, which may be a simple switch, for connecting the single storer 114 in series with the DC / AC converter 13 (position shown in FIG. 5) or in series with the DC / AC converter 23. As in the case of the embodiment 25 of FIG. alternatively, one could delete the DC / AC converter 23 and implement a single converter DC / AC 13. In this case, the switch would be made not on the DC input side of the DC / AC converter 13, but on the AC output side. The nature of the storage member 24, 114 or 124 may be quite similar to what has been described above with reference to the storage member 14. According to the present invention, the storage member 14 or 114, respectively 24 or 124 integrated in the electrical system of a turbomachine 11, respectively 3024707 16 21 may be put in standby mode, is necessary so that the corresponding gas turbine, which is initially in standby mode , is reactivated quickly, for example because of a problem on the gas turbine that was in operation. The situation described above is supposed to be extremely rare and thereafter necessitates a maintenance operation of the gas turbine. It therefore appears without significant inconvenience that the storage member 14 or 114, respectively 24 or 124, is a storer used once and replaced during engine maintenance. In this concept where the storage member 14 or 114, respectively 24 or 124 is a single shot ("one shot" in English), it is then possible to use a so-called "primary" storage technology, it is to say that these storages are not rechargeable. As already indicated, the primary pairs are divided into two families: 1 / Family of primary couples ready for use In this case, their electrolyte wets the anode and the cathode. There are high performance primary couples, with very low self-discharge, which do not exhibit temporal degradation and, since they do not require periodic recharging, make it possible to avoid implementing a control and monitoring system. (BMS) which is complex equipment and which, in addition, increases the weight of the system and its probability of failure. Mention may be made of Li-502, Li-MnO2, LiSOCl2, Zn-MnO2 (saline or alkaline), Zn-Ag2O by way of examples, this list being non-exhaustive. 2 / Family of inert primary couples Their electrolyte does not wet the anode and the cathode. This family comprises two sub-families: 2.1 / Separated electrolyte battery: the electrolyte is withdrawn into an auxiliary reservoir, and will be released upon activation. We can mention the Argent-Zinc couple (Zn-Ag2O) as an example (non-exhaustive list). 2.2 / Thermal battery: the electrolyte is solid at ambient temperature and is reheated and therefore liquefied very rapidly during activation 3024707 17 The Ca / CaCrO4 and Li / FeS2 pairs can be cited as examples, this list being non comprehensive. These couples have the advantage of being inert electrically and chemically when they are not activated.
    [0021] They provide a solution to all the disadvantages of the prior art using so-called "secondary" electrical energy storage members. a / There is no need for BMS. b / No self-discharge occurs. There is no need for a charger. c / No temporal degradation occurs and a warranty of for example 15 or 20 years can be available. d / There is no electrical hazard or risk of unexpected discharge, since the energy storage members 14, 114, 24, 124 are electrically inert. e / There is a very good resistance to severe environmental conditions since the energy storage members 14, 114, 24, 124 are chemically inert. f / There is no risk of thermal runaway in the inert state. g / The energy storage members 14, 114, 24, 124, when in an inactive state, have the property that the insulation resistance between the polarities + and - of the storage member is very high , which makes it possible to install it on an electrical architecture without precautionary precaution, and the coupling to the on-board network 17 of an electrically inert battery, is thus done very simply by putting in parallel (the storer 14 is at the insulating state) or in series (the storer supports the zero voltage state). It should be noted that the storer 14 or 114, 24 or 124, although sometimes qualified as unique as a functional unit in the present description, may not consist of a single organ, but may be made of one or more pairs or pairs of couples, connected in parallel or in series or in series-parallel. Moreover, the case of two turbomachines 11, 21 has been described above, but the invention applies in the same way to a smaller or larger number of turbomachines that can be used on the same aircraft, one or more devices. or a device with switch according to the invention can be applied to one or more of these turbomachines.
    [0022] In the case of a single-engine aircraft comprising a single turbomachine 11, which corresponds to the case of the embodiments of FIGS. 1 and 2 in which there exists only the upper element chain cooperating with the turbomachine 11, the storer 14 or 114 makes it possible to perform rapid assistance in order to provide rapid one-off assistance to the gas generator of the turbomachine 11, in the event that this turbomachine 11 is put, during flight, in an undesired extinction mode. In general, the invention is not limited to the embodiments presented, but extends to all variants within the scope of the appended claims.
    权利要求:
    Claims (16)
    [0001]
    REVENDICATIONS1. Rapid assistance device for a turbine engine (11) free turbine of an aircraft comprising at least a first turbine engine (11) with a free turbine equipped with a gas generator, associated with an electric machine (12) capable of operating as a starter and as a generator, the first turbomachine (11) can be put in standby mode or in the unwanted extinction mode, the electric machine being connected to a specific electrical energy supply network (17), such as a network the device further comprising at least one electrical energy storage member (14; 114) adapted to be electrically connected to said electrical machine (12) associated with said first turbomachine (11) to provide one-off assistance to the generator of said turbomachine (11), characterized in that said electrical energy storage member (14; 114) constitutes a non-primary energy storage member rechargeable and usable once and in that the device comprises means for activating the electrical energy storage member (14; 114) and means (15; 115) for coupling the electrical energy storage member with a power supply system (13, 16) of said electrical machine (12).
    [0002]
    A rapid assist device according to claim 1, wherein the electrical energy storage member (14; 114) comprises a low self-discharge ready-to-use device incorporating an anode and a cathode contact with an electrolyte.
    [0003]
    A rapid assist device according to claim 1, wherein the electrical energy storage member (14; 114) comprises an inert device prior to its activation, integrating an anode, a cathode and an electrolyte which does not wet the electrolyte. anode and the cathode.
    [0004]
    The rapid assist device according to claim 3, wherein the electrical energy storage member (14; 114) comprises a separate electrolyte battery with a separate electrolyte storage tank and release means. electrolyte out of the separate reservoir to enable it to come into contact with the anode and the cathode upon activation of the electrical energy storage member (14; 114).
    [0005]
    A rapid assist device according to claim 3, wherein the electrical energy storage member (14; 114) comprises a thermal battery adapted to maintain the solid electrolyte at ambient temperature during storage and to liquefy the electrolyte. electrolyte by heating upon activation of the electrical energy storage member (14; 114).
    [0006]
    6. Rapid assistance device according to one of claims 1 to 5, wherein said activation means of the electrical energy storage member (14; 114) comprise pyrotechnic activation means.
    [0007]
    The rapid assist device according to one of claims 1 to 5, wherein said means for activating the electrical energy storage member (14; 114) comprises electrical activation means.
    [0008]
    8. rapid assistance device according to one of claims 1 to 7, wherein the electrical energy storage member (14) is connected in parallel with said specific network (17) for supplying electrical energy.
    [0009]
    The rapid assist device according to claim 8, wherein a diode (15) is interposed between the electrical energy storage member (14) and a rectifier or an AC-DC converter (16) powered by said specific network (17) for supplying electrical energy.
    [0010]
    10. rapid assistance device according to one of claims 1 to 7, wherein the electrical energy storage member (114) is connected in series with a rectifier or an AC-DC converter (16) powered by said specific power supply network (17), and in parallel with a diode (115).
    [0011]
    11. rapid assistance device according to claim 10, wherein said diode (115) is constituted by a controlled electromechanical type switch or controlled static type.
    [0012]
    The rapid assist device of claim 10, wherein said diode (115) is a semiconductor element.
    [0013]
    13. The rapid assist device according to one of claims 1 to 12, wherein the electrical energy storage member (14; 114) comprises one or more elements or batteries of elements connected in series, in parallel or in series-parallel.
    [0014]
    14. Rapid assistance device according to one of claims 1 to 12, for a turbine engine (11) free turbine of an aircraft comprising a plurality of turbomachines (11, 21) free turbine each equipped with a generator of gas, each associated with an electric machine (12, 22) operable as a starter and generator, at least one of the plurality of turbomachines (11, 21) can be put in standby mode, while at least one another of the plurality of turbomachines (11, 21) is in normal operating mode.
    [0015]
    15. Rapid assistance device according to claim 14, characterized in that the device comprises a single electrical energy storage device (14; 114) adapted to be electrically connected by a switching or switching device (38, 48; 39) to said electric machine (12 or 22) associated with that of the plurality of turbomachines (11, 21) requiring punctual assistance to the gas generator of the turbomachine (11 or 21) previously put in standby mode.
    [0016]
    16.Aironef to at least one free turbine turbine engine, comprising a rapid assistance device according to any one of claims 1 to 15.
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    同族专利:
    公开号 | 公开日
    ES2676278T3|2018-07-18|
    RU2684691C2|2019-04-11|
    KR20170075709A|2017-07-03|
    JP2017525617A|2017-09-07|
    CA2956697A1|2016-02-11|
    CA2956697C|2022-01-04|
    US20170226933A1|2017-08-10|
    FR3024707B1|2018-03-23|
    EP3177817B1|2018-05-02|
    CN106661956B|2018-11-09|
    PL3177817T3|2018-10-31|
    CN106661956A|2017-05-10|
    RU2017107171A|2018-09-07|
    KR101809110B1|2017-12-14|
    JP6224869B2|2017-11-01|
    WO2016020607A1|2016-02-11|
    EP3177817A1|2017-06-14|
    US9828917B2|2017-11-28|
    RU2017107171A3|2019-01-14|
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    法律状态:
    2015-07-27| PLFP| Fee payment|Year of fee payment: 2 |
    2016-02-12| PLSC| Publication of the preliminary search report|Effective date: 20160212 |
    2016-06-20| PLFP| Fee payment|Year of fee payment: 3 |
    2017-05-04| PLFP| Fee payment|Year of fee payment: 4 |
    2017-09-01| CD| Change of name or company name|Owner name: LABINAL POWER SYSTEMS, FR Effective date: 20170727 Owner name: SAGEM DEFENSE SECURITE, FR Effective date: 20170727 Owner name: SAFRAN HELICOPTER ENGINES, FR Effective date: 20170727 |
    2017-11-03| CA| Change of address|Effective date: 20171002 |
    2018-01-19| CA| Change of address|Effective date: 20171218 |
    2018-01-19| CD| Change of name or company name|Owner name: SAGEM DEFENSE SECURITE, FR Effective date: 20171218 Owner name: SAFRAN HELICOPTER ENGINES, FR Effective date: 20171218 Owner name: SAFRAN ELECTRICAL & POWER, FR Effective date: 20171218 |
    2018-07-20| PLFP| Fee payment|Year of fee payment: 5 |
    2019-07-22| PLFP| Fee payment|Year of fee payment: 6 |
    2020-07-21| PLFP| Fee payment|Year of fee payment: 7 |
    2021-07-22| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1457671A|FR3024707B1|2014-08-07|2014-08-07|FAST ASSISTANCE DEVICE FOR AN AIRCRAFT FREE TURBINE TURBINE|FR1457671A| FR3024707B1|2014-08-07|2014-08-07|FAST ASSISTANCE DEVICE FOR AN AIRCRAFT FREE TURBINE TURBINE|
    JP2017512840A| JP6224869B2|2014-08-07|2015-07-31|A quick support device for aircraft free turbine engines.|
    PCT/FR2015/052119| WO2016020607A1|2014-08-07|2015-07-31|Quick-assist device for a free-turbine turbomachine of an aircraft|
    US15/502,017| US9828917B2|2014-08-07|2015-07-31|Rapid assistance device for a free turbine engine of an aircraft|
    KR1020177006397A| KR101809110B1|2014-08-07|2015-07-31|A rapid assistance device for a free turbine engine of an aircraft|
    RU2017107171A| RU2684691C2|2014-08-07|2015-07-31|Quick-relief device for engine with free aircraft turbine|
    EP15759878.0A| EP3177817B1|2014-08-07|2015-07-31|Aircraft|
    CA2956697A| CA2956697C|2014-08-07|2015-07-31|Quick-assist device for a free-turbine turbomachine of an aircraft|
    PL15759878T| PL3177817T3|2014-08-07|2015-07-31|Aircraft|
    ES15759878.0T| ES2676278T3|2014-08-07|2015-07-31|Aircraft|
    CN201580042459.0A| CN106661956B|2014-08-07|2015-07-31|The quick auxiliary device of the free turbine engine of aircraft|
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