• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    Assist device (100) for a turbine engine (TAG1) with an aircraft free turbine, the device comprising means (K11, CVS1) for supplying electrical energy to a winding (S11) of a starter rotating machine (GD1), said first winding, to provide a first assistance to the acceleration to the gas generator of the turbomachine (TAG1). The device further comprises means for monitoring (110) the first assistance and means (K12, CVS2) for supplying electrical energy to a second winding (S12) of a rotating machine, to allow a second assistance to the acceleration of said generator of gas if the monitoring means (110) observe a deficiency of the first assistance.
    公开号:FR3019214A1
    申请号:FR1400752
    申请日:2014-03-27
    公开日:2015-10-02
    发明作者:Vincent Poumarede；Jean-Michel Bazet；Thomas Klonowski
    申请人:Turbomeca SA；
    IPC主号:
    专利说明:

    [0001] Technical Background The invention is in the field of free turbine turbomachines for aircraft comprising several turbomachines. The aircraft can notably be a helicopter. For the record, a free-turbine turbine engine comprises a power turbine or free turbine which, in a helicopter, drives the rotors thereof via a freewheel and a main gearbox (designated in FIG. continued by BTP). The turbomachine further comprises a gas generator including a compressor, a combustion chamber and a high pressure turbine (HP).
    [0002] A mechanical gearbox or accessory box makes it possible to connect the shaft of the gas generator to an electric machine constituted by a stator and a rotor, which can operate indifferently as a motor (starter) or as a generator. In the motor mode, this 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 with the aim of starting it, by carrying out thus 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. It has been proposed in documents FR2967132 and FR2967133, for an aircraft equipped with two turbomachines in a cruising flight situation, to put one of the two turbomachines in a standby mode. Because of the freewheel, the free turbine and the gearbox are desynchronized. In parallel, the speed of the other turbomachine (or other turbomachines) is increased, which makes it possible to maintain normal flight conditions. The overall fuel consumption of the system is reduced because the specific consumption of the turbomachine maintained in operation is then lower.
    [0003] Several variants of this watch regime have been proposed. In a first variant, the gas generator of the desynchronized gas turbine can be regulated, by supply of fuel, at a low idling speed. This can be done with or without the additional application of extended assist motor torque (constant speed rotation assistance) on the gas generator via the electrical machine and the accessory box. In a second variant, it is proposed to totally extinguish the combustion chamber of the turbomachine while maintaining, using the rotating machine, the gas generator rotating at a speed to facilitate relighting at the end of the cruise flight phase. This is also a prolonged assistance (assistance to rotation at constant speed). These modes of operation are likely to be maintained throughout the cruise flight duration. A normal restart of the desynchronized turbomachine is then similar in terms of the performance required of the rotating machine operating the gas generator, the usual ground start function. Such a normal restart usually requires a few tens of seconds between the start of the start and the moment when the turbine engine has reached a speed sufficient to generate useful power on the free turbine. It is implemented for example to carry out a planned maneuver a certain time in advance and whose execution requires the simultaneous operation of the two turbomachines, such as a landing. This restart requires an acceleration in rotation of the gas generator of the turbomachine. Such acceleration is obtained by increasing the fuel flow.
    [0004] But it is sometimes necessary to be able to reactivate the turbomachine desynchronized quickly, especially in an emergency situation, for example in case of failure of another turbomachine, if there are three or more turbomachines in total, or the other turbomachine if the turbomachines are two in number. The maximum time allowed, to satisfy the safety requirements, between the emergency start request and the moment when the turbine engine thus restarted is able to deliver the useful power is typically less than 10 seconds.
    [0005] This need to be able to quickly restart the turbomachine off is notably the reason for keeping the gas generator rotating at a speed that facilitates reignition in the operating modes in which the combustion chamber is extinguished.
    [0006] But that the gas generator is in a low-speed situation or combustion chamber off, it is preferable, for the emergency restart in particular, to apply to the shaft of the gas generator a high power because of the important 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. It is estimated that the power developed by the emergency starting system must, during this short period of time, be of the order of 5 to 10 times higher than that required for a normal start. It has been suggested in FR2967133 to use, among other solutions, electrical energy, in particular a supercapacitor, which provides punctual assistance to the rotational acceleration of the gas generator. In general, since a large power is required, it is advantageous to have an electrical energy storage member capable of mobilizing a large power for a short period of time. Electric power is applied through a rotating starter machine. In the document EP2581586, it has also been proposed to use two supercapacitors, each of which is respectively charged by an electric generator driven by the gas generator of one of the turbomachines, and which each serve, on an ad hoc basis, to start another turbomachine to from an off state of it. In the document FR2914697, a one-off acceleration assistance is provided to the gas generator of a turbine engine, in particular by supplying mechanical power to the gas generator by means of an electric machine driven in rotation by the free turbine. .
    [0007] Thus, solutions have been proposed to provide the high power required for the emergency restart of a turbomachine.
    [0008] But in this context, given the security challenges, we understand that emergency start systems must ensure a high level of availability. Indeed, in case of loss of power on the turbine engine alone ensuring the propulsion of the helicopter, the impossibility of restarting emergency turbine engine initially in standby mode can result in the total loss of power. Such a requirement of high level of availability can also be applied to the normal starting function of a standby turbomachine. Indeed, when the second turbine engine is operating in a nominal manner, the impossibility of restarting the turbomachine initially initially in standby mode when returning to the twin engine, in particular to prepare the landing, will result in the use of the engine speeds. OEI emergency (for One Engine Inoperative, or a non-running engine) on the operating turbine engine.
    [0009] This situation should be avoided as it increases the workload of the crew and the use of the OEI emergency regimes is very damaging for the turbine engine. Definition of the invention and associated advantages To solve these problems, there is provided an assistance device for a turbine engine free turbine of an aircraft, the device comprising means for supplying electrical energy to a winding of a rotating machine starter , said first winding, for providing a first assistance with the acceleration to the gas generator of the turbomachine, characterized in that the device further comprises means for monitoring the first assistance and means for supplying electrical energy to a second winding rotating machine, to allow a second assistance to the acceleration of said gas generator, if the monitoring means observe a deficiency of the first assistance. It is specified that, in accordance with what has been presented above, the first assistance is an assistance to the rotational movement, by mechanical drive of the gas generator by the rotor of the rotating starter machine, and the second assistance is also an assistance to the rotational movement, by mechanical drive of the gas generator by a rotating machine rotor starter, which can be the rotating starter machine already mentioned or another rotating machine starter. Thanks to these characteristics, if the circuit comprising the first winding and the power supply thereof fails (or more generally is insufficient), which causes a total or partial loss (or insufficiency) of the assistance capacity of the gas generator using the first winding, then it is possible to overcome with the second winding and its supply circuit. The starter motor or machines may be AC or DC. The windings can be rotor or stator, depending on the structure of the rotating machine used. The supply of the second winding can be done using elements also used to power the first winding, but the power circuits can also be completely separate and segregated, which is advantageous. This point is developed later.
    [0010] In order to detect the insufficiency of the first assistance, monitoring means are used which monitor one or more elements of the power supply chain supplying the starter rotating machine with electricity, the turbomachine supervision system, and / or the turbomachine. -even. According to an advantageous embodiment, the assistance device comprises the starter rotating machine and moreover a third-party starter rotating machine for providing assistance with the acceleration of the gas generator of a second turbine engine of the aircraft, the second winding being electrically connected bypassing said third-party rotating machine to the same power supply path.
    [0011] This makes it possible to pool the energy sources and the energy supply means and thus reduce the mass of the necessary elements. In particular, the energy source in question may be the source used in priority for the restart of the second turbomachine, and which is therefore used as a backup for the restart of the first turbomachine, if its restart circuit using the first winding lack. The source can be an element of energy storage, useful especially for the emergency restart.
    [0012] The assistance device may comprise a power converter and is preferably configured so that a power converter transmits electrical energy to the second winding of the starter rotating machine or, exclusively, to the third-party starter rotating machine. This configuration can be made using a pair of contactors included in the assistance device and can not be in the closed position simultaneously, so as to obtain the transmission of electrical energy exclusive to the second winding or to the rotating machine third starter. In one embodiment, said rotating starter machine, included in the assistance device, is a fault tolerant alternating-current rotating machine known as a double-coil machine or a double-star machine, the second winding being his second winding. In a known manner, these synchronous or asynchronous alternating-current rotating machines are characterized by two independent sets of three-phase stator windings, wound on the same magnetic circuit, each winding being powered by its own DC / AC power converter. . Although having many architectural variants, the design of these machines is based on the general principle of ensuring a high level of electrical insulation and physical, thermal and magnetic segregation between each of these two windings. This separation makes it possible to ensure that an electrical fault such as, for example, a short circuit or an open circuit, occurring at the level of the first winding or its DC / AC power converter, will have no impact. functional on the second winding and thus on the ability of the starter to deliver a torque of assistance to the gas generator. By pooling the stator magnetic circuit as well as mechanical elements such as the rotor, the bearings and the structure (housing), a rotating machine of this type is substantially more compact and lighter than a set of two completely independent machines of total performance. equivalent, while offering a high level of tolerance for internal power failures or power converter failures.
    [0013] The use of a double-coil machine also allows to set up a single rotating machine, which simplifies the mounting on the accessory box of the turbomachine.
    [0014] In one embodiment, the first coil is sized to allow acceleration assistance with higher performance than that provided by the second coil. Thus, the starter rotating machine can be sized to allow an emergency start (rapid start) of the turbomachine with the only power supply of said first coil, while keeping a reasonable dimensioning of the assembly, and always allowing a redundancy of non-emergency start-up capabilities (normal start). In one embodiment, the second winding is sized to assist acceleration with similar performance to that provided by the first winding. Thus there is a complete redundancy of the restart capabilities, including, if the coils and the magnetic circuit are sized for this, emergency restart capabilities.
    [0015] In one embodiment, the assistance device comprises two power converters for transmitting each electrical energy in a controlled manner respectively to said first and second coils. This allows a fine transition between the two audiences in case of detection of impairment in the first circuit. This also allows the piloting of an acceleration assistance using the two coils, which is particularly useful in an emergency situation since it can then benefit simultaneously for this acceleration of the power developed in each of the two coils. In one embodiment, the assistance device comprises a first source of electrical energy for supplying the first or second winding, and the assistance device is further configured so that the second or the first winding can be powered by a second power source distinct from the first power source, which provides greater security in case of failure of one of the power sources or its electrical connection.
    [0016] In one embodiment, the device further comprises a third-party starter rotating machine for providing assistance with the acceleration to the gas generator of a second turbomachine of the aircraft, said third-party rotating machine comprising a winding said third winding, the assistance device further comprising a source of electrical energy configured to supply, as needed, the first or third coils. Thus, on a twin-engine apparatus, an acceleration assistance is obtained for each of the turbomachines, while not multiplying the energy sources, since the energy source for the first turbomachine is also used for the second one. turbine engine. In one embodiment, the starter rotating machine, included in the assistance device, is also a generator powered by the turbine engine 10 when it is active, the second winding is that of a second rotating machine included in the invention. assistance device and that is only a starter. The generator can be used to recharge an energy storage element included in the assistance device or external to it. The energy storage element may be operable to provide electrical power for assisting the acceleration of the gas generator. This is particularly useful, as mentioned in the introduction, during a flight phase of the aircraft during which a second turbomachine provides power to the rotary wing of the aircraft for its flight, and that it is appropriate to operate an emergency restart (reactivation) of the first turbomachine. The fact of having two separate rotating machines, only one being responsible for the current generation, can make it possible to better size the two windings and the cylinder heads of the rotating machines while setting up a storage of energy for the restart of urgency of a turbomachine in flight and ensuring physical and functional segregation, favorable to the availability of the normal start function or emergency turbine engine, between the two rotating machines and their power converters, in the modes of embodiment in which they are connected to such converters. In one embodiment, the second winding is that of a second rotating machine included in the assistance device, the second rotating machine being DC, and the first rotating machine, also included in the assistance device, alternating current.
    [0017] This makes it possible to implement a torque / speed control of the first rotating machine operating in alternating current, used in priority, and to have a spare rotating machine directly powered by the aircraft's dc network, which is currently the starting device for the majority of helicopters equipped with small or medium power turboshaft engines and an electric starter. In one mode of use, the first winding is powered by an electrical storage member and the second winding is powered by the aircraft's onboard network. An aircraft is therefore proposed here, for example a twin-engine helicopter, comprising an assistance device according to the invention, the second winding being fed by the aircraft's on-board network. This makes it possible to have a power storage, for emergency starting or restarting, while being able to overcome a failure of the electrical storage unit without nevertheless doubling it, which can be considered as penalizing in terms of size and mass. In one embodiment, the means for supplying the second winding comprise a contactor which is closed if it is noted, by the monitoring means, a difficulty or an impossibility to accelerate said gas generator, for example to start said turbine engine, using the first winding. The contactor is a simple electromechanical device with a low risk of failure. There is also provided a method of assisting an aircraft free turbine turbine engine, comprising a step of supplying a winding said first winding of a starter rotating machine, with electrical energy to provide assistance to the aircraft. acceleration to the gas generator of the turbomachine, characterized in that the method further comprises a step of monitoring said assistance and a step of feeding a second rotating machine winding into electrical energy to allow a second assistance to the acceleration of said gas generator, if it is found during the monitoring step a difficulty 30 to start said turbomachine using the first winding. List of Figures Figure 1 shows the context of the embodiments of the invention. Figure 2 shows a first embodiment of the invention. Figure 3 shows a second embodiment of the invention. Figure 4 shows a third embodiment of the invention. DETAILED DESCRIPTION OF EMBODIMENTS With reference to FIG. 1, the general electrical architecture of one embodiment of the proposed system is as follows. It is given as part of a helicopter with two turbomachines. The BTP power transmission gearbox is driven by the turbine engines TAG1 and TAG2. These are free turbine turboshaft engines. They each comprise a power turbine (free turbine) driving the power transmission gearbox (BTP) via a free wheel, and a gas generator. The electrical generation of the aircraft is provided by at least two alternators ALTI. and ALT2 driven by the BTP. Although this architecture rather reserved for heavy helicopters is not essential for the implementation of the present invention and is not an essential feature, it is technically preferable to the conventional solution on smaller tonnage aircraft to train the generators by the gas generator of the turboshaft engines. Indeed, fuel economy in cruise flight is obtained, as mentioned in the introduction, by the standby of a turbine engine, which is a mode of operation incompatible with the removal of any power level on the gas generator, it appears to be particularly relevant in terms of safety to functionally decouple the electrical generation of the aircraft from the operating speed of the turboshaft engines. ALTI. and ALT2 feed the aircraft electrical network, other sources of energy available to supply this network may be constituted by an auxiliary power unit on board (APU), one or more batteries (s) of accumulators, or again, on the ground, a park catch. Each turbine engine TAG1 and TAG2, is equipped with a rotary machine (G / D1 and G / D2, respectively) able to operate as a starter as a generator, and mechanically connected to the gas generator of the corresponding turbomachine via a box of accessories. In order to optimize the compactness and the mass of the device, it is preferred for GD1 and GD2 a machine architecture compatible with a high-speed drive by the gas generator, therefore without rotor winding, such as Non-exhaustive example is a brushless synchronous machine (brushless motor) with permanent magnets, a variable reluctance machine or an asynchronous cage machine (without brushes). The two machines G / D1 and G / D2 are included in an assistance device 100, operating independently of the electrical network of the aircraft. With reference to FIG. 2, a first embodiment of the assistance device 100 has been presented. The electrical machines GD1 and GD2 are double-coil electrical machines, or alternating current fault-tolerant rotating machines. These machines consist of a single magnetic circuit or cylinder head and two separate polyphase windings or stator windings, denoted S11 and S12 for GD1 and S21 and S22 for GD2. GD1 and GD2 are for example synchronous or asynchronous type machines. The windings S11 and S22 are respectively connected to reversible DC / AC power converters CVS1 and CVS2. These each constitute an interface between the polyphase AC circuit of the winding and a DC circuit consisting of a DC bus connecting the converter to an electrical storage member. The electrical storage members are denoted respectively S1 and S2, and the continuous buses connecting them Bus No. 1 and Bus No. 2. The electrical storage members are here direct current, and are for example supercapacitors, hybrid capacitors, storage batteries or flywheels equipped with an integrated DC / AC converter. The windings S12 and S21 are connected to the opposite power converters, that is to say respectively CVS2 and CVS1. The windings S12 and S22 are thus connected bypass, or in parallel, with respect to one another at the output of the CVS2 converter, whereas the windings S11 and S21 are connected in a bypass connection to a screw to each other at the output of the CVS1 converter.
    [0018] Contactors K11, K21, K12 and K22 are present to electrically isolate or connect the windings S11, S21, S12 and S22, respectively, and operate or are operated in a coordinated manner so that the CVS1 and CVS2 converters can be used to drive each at most a single rotating machine at a given moment. Thus, the closing of the contactor K11, respectively K21 causes the opening of the contactor K21, respectively K11, and that of the contactor K12, respectively K22 causes the opening of the contactor K22, respectively K12. Knowing that in all cases it is necessary to start only one turbine engine at a time, this contactor device and the associated control logic advantageously allow the mutualization of the power converters between the two rotating machines and to reduce the necessary number of four to two, while maintaining the level of redundancy required by the availability of normal and emergency start functions, which provides a distinctive gain in terms of weight and bulk.
    [0019] A contactor KC makes it possible to connect, or on the contrary isolate electrically the two buses DC, n ° 1 and n ° 2. The rotating machines GD1 and GD2 are here both generators and starters. In generating operation, they are rotated by the gas generator of the corresponding turbomachine, and they are able, by one or other of their stator windings, to transfer electrical energy to the storage elements S1 and / or S2, or to the single storage element if only one storage element is provided. Once the electrical energy storage elements are loaded, a single-engine flight phase can be conducted. In the scenario presented here, the turbine engine TAG1 provides the driving power and the turbine engine TAG2 is kept in a standby mode among those presented in the introduction. To restart the TAG2 turbine engine, for example before landing, or in the event of loss of power on the TAG1 turbine engine, it is proposed to first electrically isolate the buses No. 1 and No. 2 from one of the using the KC contactor, to ensure that no part of the system fails to propagate to another. Then the contactor K21 is closed, K11 being open and the converter CVS1 being inhibited, ready for operation but not actually feeding the winding S21.
    [0020] Simultaneously, the contactor K22 is closed, K12 being open, and the converter CVS2 being controlled inverter to control the rotating machine GD2 operating in motor mode and regulate the torque provided by it in a law optimized for normal starting or emergency of the turbomachine depending on the circumstances. The gas generator of the turbomachine TAG2 is thus actuated so as to allow the start of the turbomachine. If a failure occurs on the power train S2-CVS2-K22-S22 and threatens the possibility of leading the acceleration of the gas generator of the TAG2 turbine engine to good, it is identified by monitoring means 120. These means The monitoring system 120 then controls the actuation of the CVS1 converter. In a first variant, the CVS2 converter is disconnected from the winding S22 by means of the contactor K22 or put in want, and the power converter CVS1 feeds, alone, the winding S21 according to a torque control law identical to that implemented. implemented by the converter CSV1. Thus, the start sequence is continued. While initially the energy was taken on the storage member S2, it is then on the storage member Si. In a second variant, and in case of partial or progressive failure of the power chain S2- CVS2-K22-S22, it is implemented a strategy of sequential control of the converters, transferring the torque from one branch to the other continuously, in whole or in part. Thus the audience by the two windings can be exclusive or, on the contrary, simultaneous. It is specified that a failure of the power chain S2-CVS2-K22-S22 can be detected, by the monitoring means 120, at each element of the power chain S2-CVS2-K22-S22 (including the DC bus), or at the level of the supervision system of the TAG1 turbomachine, for example by comparing the acceleration of the gas generator to a predetermined template. The power chain S1-CVS1-K11-S11 and the acceleration assistance of the gas generator of the turbine engine TAG1 are similarly monitored by monitoring means 110 which ensure a symmetrical role for the monitoring means 120. .
    [0021] In a variant, each of the windings S11, S12, S21 and S22 is sized to be able, in engine operation, to provide on its own the necessary performance for an emergency start, and a fortiori for a normal start of the corresponding turbomachine. Thus, in case of failure on one of the power chains, normal start and emergency start can be carried out with a replacement power chain. In another variant, only the windings S11 and S21 are sized to be able to provide, individually, the performance required for an emergency start. Nevertheless, the four windings S11, S21, S12 and S22 are dimensioned to be able to provide the necessary performances for a normal start. Thus, in case of failure on one of the power chains involving S11 or S21, the normal start can be completed with a replacement power chain, and the emergency start is performed with similar performances to those of normal start, using one of the S12 or S22 windings.
    [0022] Finally, in another variant, the windings 511 and S12 (respectively S22 and S21) are dimensioned to jointly deliver, while being powered simultaneously, the torque and power performance for the emergency start of the turbine engine TAG1 (respectively TAG2). . The two converters CVS1 and CVS2 are, for such an emergency start, activated simultaneously, one being master and the other slave, so as to feed in a coordinated manner the two coils. It is further proposed that the windings S11 and S12 (respectively S22 and S21) are dimensioned in this variant, to allow a normal start using a single winding, which ensures that in case of failure of one of the chains of power implying, a normal start of the turbomachine can be completed in any event. With reference to FIG. 3, another embodiment of an assistance device, here reference 101, is presented. The double-coil machines are replaced by sets of two single-coil rotating machines. Thus, replacing GD1, a rotating machine M1A AC with a single stator winding is present, with, on another socket of the accessory box of the turbine engine TAG1, another rotating machine M1B alternating current also to a only stator winding. In this embodiment, the winding S11 is that of the machine M1A and the winding S12 that of the machine M1B. It is polyphase windings. The machine M1A is both a generator and a starter, while the machine M1B is only a starter. M1B can optionally be mechanically connected to the gas generator 5 of the turbomachine via a freewheel, which allows to size the starter only for the maximum drive speed in starter mode is around 50 to 60% NG, instead of the maximum speed of the gas generator is 100% NG. Thus, during the flight phases during which the turbomachine is in operation, the electrical energy storage element S1 is recharged via the generator M1A and the converter CVS1, the rotary machine M1B being left at rest. It is further specified that one of the two machines M1A or M1B is sized to provide the required performance in the event of an emergency start, but the other machine may be dimensioned only to provide the performance required for a particular machine. normal start. Similar elements are set up in the accessory box of the TAG2 turbomachine, the electrical machines being marked M2A and M2B. Monitoring means 111 and 121 monitor assistance to the acceleration of the gas generators of the turbomachines, as in FIG. 2, to control the start-up of the CVS1 and CVS2 power converters. With reference to FIG. 4, another embodiment of an assistance device, here reference 102, is presented. The machines M1B and M2B are replaced by DC brush and commutator machines, D1 and D2. Their respective armature (rotor) coils, S12 and S21, are connected to the helicopter's dc board, which is a 28VDC network comprising in particular at least one battery B. KB2 (usually not coordinated to each other) can isolate these machines from the network or on the contrary to connect them. A single electrical energy storage unit S can additionally replace, in the variant shown, the storage members S1 and S2 of the previous embodiments. Contactors KS1 and KS2 make it possible to connect this member S either to the converter CVS1 or to the converter CVS2. It is nevertheless possible to use two storage members as in FIGS. 2 and 3. Monitoring means 112 and 122 monitor the assistance with the acceleration of the gas generators of the turbomachines, as in FIGS. 2 and 3, for controlling 5 this time the switchover of the switches KB1 and KB2. In the event of a fault preventing the startup of a turbomachine, for example the turbine engine TAG1, using the corresponding AC rotary machine, that is to say for TAG1 the machine M1A, the contactor KB1 is closed and the DC motor D1 takes the relay, allowing a normal start of the turbine engine TAG1 although the assistance torque can not be controlled. DC machines D1 and D2 can be generators, in addition to their function of starter. If this is not the case, they can be connected to the accessory box of the corresponding turbomachine by a freewheel.
    [0023] The invention is not limited to the embodiments presented, but extends to all variants within the scope of the claims.
    权利要求:
    Claims (17)
    [0001]
    REVENDICATIONS1. Assist device (100; 101; 102) for a turbine engine (TAG1) with an aircraft free turbine, the device comprising means (K11, CVS1) for supplying electrical energy to a winding (S11) of a rotating starter machine (GD1, M1A), said first winding, for providing a first assistance with the acceleration to the gas generator of the turbomachine (TAG1), characterized in that the device further comprises monitoring means (110; 111; 112 ) of the first assistance and means (K12, CVS2, KB1) for supplying electrical energy to a second winding (S12) of rotating machine, to allow a second assistance to the acceleration of said gas generator if the monitoring means (110 111, 112) observe a deficiency of the first assistance.
    [0002]
    2. Assist device according to claim 1, comprising the rotating machine starter (GD1, M1A) and moreover a rotating machine third starter (GD2; M2A) to provide assistance to the acceleration of the gas generator of a second turbine engine (TAG2) of the aircraft, the second winding (S12) being electrically connected, in derivation of said third rotating machine (GD2; M2A), to the same power supply path (CVS2).
    [0003]
    3. Assist device according to claim 2, comprising a power converter (CVS2) and configured so that said power converter (CVS2) transmits electrical energy to the second winding (S12) of the rotating starter machine (GD1) , M1A) or exclusively to the rotating starter machine (GD2, M2A).
    [0004]
    4. Assist device according to claim 3, comprising a pair of contactors (K12, K22) that can not be in the closed position simultaneously, so as to obtain the transmission of electrical energy exclusive to the second winding (S12). or the rotating starter motor (GD2, M2A).
    [0005]
    5. Assist device according to one of claims 1 to 4, wherein the monitoring means (110; 111; 112) monitors one or more elements (S1, CVS1, K11, S11) of the power chain supplying the power supply. rotating machine starter (GD1; M1A) in electricity
    [0006]
    6. Assist device according to one of claims 1 to 5, wherein the monitoring means (110; 111; 112) monitor the monitoring system of the turbine engine (TAG1).
    [0007]
    7. Assist device according to one of claims 1 to 6, comprising said rotating starter machine (GD1), the latter being a rotary machine with alternating current fault tolerant called double coil or double star machine, the second winding (S12) being its second winding.
    [0008]
    8. Assist device according to claim 7, wherein the second winding (S12) is sized to allow assistance with acceleration with similar performance to that provided by the first winding (S11).
    [0009]
    The assisting device of claim 7, wherein the second winding (S12) is sized to allow acceleration assistance with higher performance than the second assist.
    [0010]
    10. Assist device according to one of claims 1 to 9, comprising two power converters (CVS1, CVS2) for transmitting each of the electrical energy in a controlled manner respectively to said first and second windings (S11, S12).
    [0011]
    11. Assist device according to one of claims 1 to 10, comprising a first source of electrical energy (S1, S) for supplying the first or second winding (S11, S12), the assistance device being further configured so that the second or the first winding (S12, S11) can be powered by a second power source (S2; B) separate from the first power source.
    [0012]
    12. Assist device according to one of claims 1 to 11, further comprising a rotating machine third starter (M2A) for providing assistance to the acceleration gas generator of a second turbine engine (TAG2) of the aircraft, said third rotating machine (M2A) comprising a winding (S22) said third winding, the assistance device further comprising a source of electrical energy (S1, S2, KC; S, KS1, KS2) configured to supply, in according to the needs, the first or the third winding (S11, S22).
    [0013]
    13. Assist device according to one of claims 1 to 12, wherein the rotating machine starter (M1A) is included in the assistance device and is also a generator configured to be actuated by the turbine engine (TAG1), the second winding (S12) being that of a second rotating machine (M1B; D1) included in the assistance device and which is only a starter.
    [0014]
    14. Assist device according to one of claims 1 to 13, wherein the second winding (S12) is that of a second rotating machine (D1) included in the assistance device, the second rotating machine being current continuous, and the first rotating machine (M1A), included in the assistance device, being AC.
    [0015]
    15. Assist device according to one of claims 1 to 14, wherein the means for supplying the second winding comprises a contactor (KB1) which is closed if it is found an impossibility to accelerate said gas generator to the using the first winding.
    [0016]
    16.Aironef comprising an assistance device according to one of claims 1 to 15, and wherein the first winding (S11) is powered by an electrical storage member (S) and the second winding is supplied by the on-board network. of the aircraft.
    [0017]
    17. A method for assisting a turbine engine (TAG1) with an aircraft free turbine, comprising a step of feeding a winding (S11) said first winding of a starter rotating machine (GD1, M1A), into electrical energy for providing assistance with the acceleration to the gas generator of the turbomachine (TAG1), characterized in that the method further comprises a step of monitoring said assistance and a step of feeding a second winding (S12) of rotating machine in electrical energy to allow a second assistance to the acceleration of said degaz generator, if it is found during the monitoring step a difficulty in starting said turbomachine using the first winding.
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    同族专利:
    公开号 | 公开日
    US10294868B2|2019-05-21|
    JP2017519144A|2017-07-13|
    RU2683351C2|2019-03-28|
    RU2016142122A3|2018-10-09|
    WO2015145076A1|2015-10-01|
    KR20160135837A|2016-11-28|
    PL3123009T3|2019-03-29|
    CA2942962A1|2015-10-01|
    JP6470305B2|2019-02-13|
    FR3019214B1|2019-05-31|
    KR102285092B1|2021-08-03|
    CN106164442A|2016-11-23|
    CA2942962C|2021-09-07|
    EP3123009B1|2018-11-14|
    EP3123009A1|2017-02-01|
    RU2016142122A|2018-04-28|
    CN106164442B|2019-05-07|
    ES2703234T3|2019-03-07|
    US20170184032A1|2017-06-29|
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    法律状态:
    2016-03-02| PLFP| Fee payment|Year of fee payment: 3 |
    2017-02-10| PLFP| Fee payment|Year of fee payment: 4 |
    2017-09-01| CD| Change of name or company name|Owner name: SAFRAN HELICOPTER ENGINES, FR Effective date: 20170727 |
    2018-02-20| PLFP| Fee payment|Year of fee payment: 5 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-02-19| PLFP| Fee payment|Year of fee payment: 8 |
    2022-02-18| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1400752A|FR3019214B1|2014-03-27|2014-03-27|ASSISTANCE DEVICE FOR AN AIRCRAFT FREE TURBINE TURBINE|
    FR1400752|2014-03-27|FR1400752A| FR3019214B1|2014-03-27|2014-03-27|ASSISTANCE DEVICE FOR AN AIRCRAFT FREE TURBINE TURBINE|
    US15/128,845| US10294868B2|2014-03-27|2015-03-26|Assistance device for an aircraft turbine engine with a free turbine|
    KR1020167030205A| KR102285092B1|2014-03-27|2015-03-26|An assistance device for an aircraft turbine engine with a free turbine|
    ES15725705T| ES2703234T3|2014-03-27|2015-03-26|Assistance device for an aircraft-free turbine turbomachine|
    EP15725705.6A| EP3123009B1|2014-03-27|2015-03-26|Assistance device for an aircraft free turbine turbomachine|
    JP2016559229A| JP6470305B2|2014-03-27|2015-03-26|Helper for aircraft turbine engine with free turbine|
    PCT/FR2015/050766| WO2015145076A1|2014-03-27|2015-03-26|Assistance device for an aircraft free turbine turbomachine|
    CN201580016241.8A| CN106164442B|2014-03-27|2015-03-26|The auxiliary device of aircraft free turbine turbine|
    RU2016142122A| RU2683351C2|2014-03-27|2015-03-26|Auxiliary device for an aircraft gas turbine engine with a free turbine|
    CA2942962A| CA2942962C|2014-03-27|2015-03-26|Assistance device for an aircraft free turbine turbomachine|
    PL15725705T| PL3123009T3|2014-03-27|2015-03-26|Assistance device for an aircraft free turbine turbomachine|
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