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    • 专利摘要:
    Assist device (100) for a turbine engine (TAG1) with free turbine of an aircraft comprising at least two turbomachines (TAG1, TAG2) with free turbine, the device comprising an electric starter machine (D1) for prolonged assistance of the gas generator of a first turbine engine (TAG1) with energy produced by an electric generator machine (G2) driven by the second turbine engine (TAG2), the device further comprising at least one electrical storage device (S1) connected electrically to said electric starter machine (Dl) to provide a timely assistance to said gas generator, characterized in that the electric starter machine (D1) is powered by a first power converter (CVS1) which allows it to exchange the energy with the storage member (S1) for the punctual assistance, and which transmits energy supplied by a second power converter (CVS2) for the assi extended stance.
    公开号:FR3019215A1
    申请号:FR1400753
    申请日:2014-03-27
    公开日:2015-10-02
    发明作者:Vincent Poumarede；Thomas Klonowski；Calvairac Fabien Mercier；Camel Serghine
    申请人:Turbomeca SA；
    IPC主号:
    专利说明:

    [0001] TECHNICAL BACKGROUND The invention is in the field of assemblies of several free turbine turbomachines, as commonly found on helicopters. 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. subsequently by BTP), and also a gas generator consisting mainly of a compressor, a combustion chamber and a high pressure turbine (HP). A mechanical gearbox or accessory box makes it possible to connect the shaft of the gas generator to an electric machine consisting of a stator and a rotor, which can operate indifferently as a motor (starter) or as a 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 the startup, by performing 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. 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. by increasing the speed of the other turbomachine, which reduces the overall fuel consumption of the system. 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. 301 9 2 1 5 2 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 a motor torque assistance is applied to the gas generator via the electric machine and the accessory box. In a third variant, the combustion chamber of the turbomachine can be completely extinguished, and it is then proposed to keep the gas generator in rotation at a speed to facilitate reignition 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. 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 reactivate the turbomachine désynchronisée quickly, especially in an emergency situation, for example in case of failure of another turbine engine, if there is three or more turbomachines in total, or the other turbomachine if there are two turbomachines. This is particularly the reason for keeping the gas generator rotating at a speed facilitating reignition in the system 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 25 regulated at idle (mode "super assisted idle") require for their part a rather weak power 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 FR2967132 and FR2967133, among other solutions, to use an electric starter powered by a starter / generator connected to the gas generator of the other turbine engine, or a generator driven directly or indirectly by the free turbine of the engine. other turbomachine. 301 9 2 1 5 3 As for the emergency restart from a low-speed situation or a burned-out combustion chamber, it requires applying a high power to the generator shaft because of the inertia important 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 FR2967133 to use, among other solutions, electrical energy, in particular a supercapacitor, which provides punctual assistance to the gas generator. In EP2602458, it is proposed to use the power taken from the power turbine of the first turbomachine to assist the rotation of the gas generator of the second turbomachine. The power transfer is performed using two electrical machines. It reduces fuel consumption. The second turbomachine is kept in idle mode ("idle").
    [0002] In 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.
    [0003] 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. . The system also works in deceleration assistance.
    [0004] The present invention aims, in this context, to provide a structure for both the continuous supply of energy of the gas generator of a first turbomachine by the other turbomachine, including, but not only, in the context of prolonged assistance to the rotation of the gas generator of said first turbomachine in its preferred ignition window, but also the use of an electrical storage member charged by a turbomachine and serving for the point supply of energy to the generator of gas of the second turbomachine in the context of restarting or assisting the acceleration of said second turbomachine. The structure may preferably, but not necessarily, be independent of the on-board electrical network (particularly autonomous in terms of power supply, but also galvanically isolated) and easy to implement in practice in an aircraft.
    [0005] DESCRIPTION OF THE INVENTION AND ASSOCIATED ADVANTAGES For this there is provided an assistance device for a turbine engine free turbine of an aircraft comprising at least two turbomachines free turbine, the device comprising an electric starter machine to perform extended assistance, characterized in general by a low power, the gas generator of a first turbomachine with energy produced by a generating electric machine powered by the second turbomachine (generally by the gas generator of said second turbomachine, the connection being performed by an accessory box), the device further comprising at least one electrical energy storage device electrically connected to said starter electric machine to provide a point assistance, generally characterized by high power, to said gas generator, characterized in that the electric machine starts r is powered by a first power converter that allows it to exchange energy with the storage device for punctual assistance, and which transmits energy supplied by a second power converter for assistance extended. The evoked electrical machines can, in some implementations, operate in both motor mode and generator mode, and in this case the architecture can be symmetrical, each of the two turbomachines can be assisted in turn. But nevertheless an asymmetrical architecture is also possible, with assistance provided to only one of the two turbomachines. Thanks to this structure, it is possible with a limited weight and a limited number of components, to set up the various functions of one-off assistance in flight, one-off assistance at start-up, prolonged assistance to the rotation of the gas generator. , such as for example the prolonged holding in rotation of the latter in the absence of combustion in the combustion chamber. It is also possible to carry out a conventional start-up of the turbomachine, or to ensure the dry ventilation thereof. It is recalled that the dry ventilation consists in rotating the gas generator at a reduced speed for about ten seconds, the fuel flow being cut, so as to use the air flow generated by the compressor to cool some subsets internal turbomachine, and to evacuate from the combustion chamber a possible accumulation of unburned fuel resulting from a fault ignition during startup. The system of two power converters makes it possible to manage the exchanges of electrical energy between the electric machine driven by the gas generator of the first turbomachine, which generally supplies an alternating voltage, the electric machine responsible for providing assistance to the generator the gas turbine of the second turbomachine, which in general is also an AC machine, and with the storage member, which can in particular provide a DC voltage. Thus, these two converters allow the use of two energy sources that are not of the same nature (direct or alternating current) or the same characteristics (low or high voltage, or different frequencies). The device may comprise a bus, for example DC and high voltage between the electrical storage member and the first converter, the bus being independent (galvanically isolated) from the electrical network of the aircraft. Thus, the regulatory requirements for the on-board system do not apply to the bus, and the bus voltage is distinct from the on-board system voltage, and is suitable for storing energy in the storage device as well than for the optimization of the mass of electrical machines and power converters. Advantageously, the first converter is controlled. Thus, the first converter makes it possible to control the speed (frequency) and the torque applied to the starter rotating machine (AC machine). Advantageously, a breaking device (static, electromechanical or other) makes it possible to galvanically isolate the two converters from one another, the storage member remaining connected to the first power converter. Thus, the storage member can transmit energy only to the gas generator of the first turbomachine, without applying it to the second power converter. 301 9 2 1 5 6 Advantageously, the first electric machine is also a generator. This recharges the electrical storage device by the energy supplied by the first electrical machine, through the first power converter. Advantageously, a switching member makes it possible to connect the second power converter to the electrical storage member. This recharges the electrical storage device by the energy supplied by the second turbomachine, through the second power converter. Advantageously, the device can be controlled, via the first power converter, to assist punctually with the aid of the electrical storage member 10 possible controlled acceleration or deceleration of said gas generator of the first turbomachine in twin-engine flight condition. As stated in the document FR2914697, this method makes it possible to improve the transient performance of the turbomachine, and therefore to reduce the amplitude of the fall or increase in the speed of the rotors of the aircraft resulting from a rapid variation. 15 of the requested power to said turbomachine. It is specified that in the case of a deceleration of the gas generator, the punctual assistance is a subtraction of energy, whereas in the context of an acceleration of the power generator, the punctual assistance is a contribution of energy without taking energy from the aircraft's on-board network. Advantageously, the second power converter is powered by an electric machine operating as a generator actuated by the gas generator of a second turbine engine of the aircraft. Thanks to this technical choice, an assistance device is obtained which can be autonomous from the on-board network, which substantially reduces the problems of electromagnetic disturbances, in particular those caused by the electric cables, simplifies the installation and avoids oversizing the system. network, the electrical generation system or the battery of the aircraft. Furthermore, the assistance device can be provided by the engine manufacturer as part of a design and certification process distinct from that of the aircraft. For example, the second generating electric machine also has a starter function of the second turbomachine. Thus, weight is saved and the number of necessary devices is reduced, and it is possible to implement a conventional start of the first turbomachine, or else the dry ventilation of the turbomachine, using the assistance device. Advantageously, the device comprises a turbomachine storage element for participating in the point accelerations of the gas generators of one or other of the turbomachines. Apart from the fact that each of the two turbomachines is thus provided with a specific punctual assistance function, the fact of having a turbomachine storage element makes it possible to electrically segregate the assistance devices of the two turbomachines when they participate. simultaneously with the propulsion of the aircraft (flight in twin engine condition). In some embodiments, the extended assistance may be performed during periods during which said gas generator is not fueled, the mechanical energy being adapted to maintain said gas generator at a reduced speed facilitating reignition said gas generator.
    [0006] In some embodiments, the extended assistance may be performed during periods during which said gas generator is maintained in operation, the mechanical energy being adapted to maintain said gas generator at a reduced speed minimizing fuel consumption. Finally, the electrical storage device may comprise at least one supercapacitor, a hybrid capacitor, a lithium-ion battery or a flywheel with or without an integrated DC / AC power converter. Advantageously, it is proposed that the electrical storage member be recharged by taking energy from the gas generator of the first or second turbomachine during periods during which said gas generator is supplied with fuel. It should be pointed out that, advantageously, the storage device is more particularly designed to accept, without damage, discharge sequences characterized by a high power and a short duration, of the order of a few seconds, and that in this respect it is dedicated solely to the occasional assistance function to the gas generator of the turbomachine. In this context, it is used in particular for the functions of normal start, emergency start and dry ventilation, and the assistance in flight. The invention also relates to an aircraft with at least two free turbine turbomachines, comprising an assistance device as evoked. The aircraft may be a helicopter. The invention will now be described in relation to the appended figures. List of Figures Figure 1 shows an overall diagram of a system according to the invention, integrated into the propulsion and electrical systems of the aircraft. Figure 2 shows a more specific diagram of an embodiment of the invention. Figures 3 to 9 each show a phase or a mode of use of the embodiment of Figure 2. Figure 10 shows an alternative embodiment of the invention. Figure 11 shows another alternative embodiment of the invention. Figures 12 and 13 show two alternative embodiments of the invention. DETAILED DESCRIPTION Referring to FIG. 1, the general electrical architecture of one embodiment of the proposed system is as follows. The electrical generation of the aircraft is provided by at least two alternators ALTI. and ALT2 driven by the transmission gearbox (BTP), typically 115VAC / 400Hz machines of the type "3 stages", 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 turbine engines, thus making it possible to maintain a sufficient level of availability and redundancy for electrical generation. economic cruise flight, when one of the two turbomachines is kept in a standby mode incompatible with any power draw on the gas generator. 301 9 2 1 5 9 Moreover, this architecture is less penalizing for the operation of the turbine engines than a sampling at the gas turbine engine generators, in particular in terms of impact on the acceleration and specific fuel consumption performances, as the mechanical sampling 5 corresponding to the electrical power consumed by the aircraft's on-board system is effected on the side of the free turbine and not on the level of the gas generator. 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. 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 BTP via a free wheel 15, and a gas generator. Each turbine engine TAG1 and TAG2, is equipped with a rotating machine (G / D1 and G / D2, respectively) able to function as a starter as a generator, and, in the embodiment shown, mechanically connected to the gas generator of the turbomachine through a box of accessories. In order to optimize the compactness and the mass of the device, it is preferred for G / D1 and G / D2 a machine architecture compatible with a high-speed drive by the gas generator, therefore without rotor winding, such as for example and not exhaustive a synchronous machine "brushless" (brushless motor) with permanent magnets, a variable reluctance machine or an asynchronous machine. Both machines G / D1 and G / D2 are included in an autonomous electrical assembly 100, operating independently of the electrical network of the aircraft. With reference to FIG. 2, the autonomous electrical assembly 100 comprises the following subsets. It comprises first of all two buses, Bus No. 1 and Bus No. 2, DC (DC) and high voltage (of the order of a few hundred volts), independent of each other and independent of the transmission network. edge. The autonomous electrical assembly further comprises two CVS1 and CVS2 reversible DC / AC static power converters (for example of two-level or other inverter type) loaded in particular with power supply and torque control and in speed of rotating machines G / D1 and G / D2. When the electric machine is driven by the gas generator, these converters are able to operate as a controlled rectifier and to regulate the corresponding bus voltage. The autonomous electrical assembly 100 further comprises electrical storage members S1 and S2, optimized for brief and intense power discharges. It may be, for example, supercapacitors or hybrid capacitors 10 (possibly equipped with their control system), Li-ion batteries (equipped with their control and monitoring system usually called "BMS" for Battery Management System in English) or a flywheel (and its AC / DC converter charging / discharging). The self-contained electrical assembly 100 further comprises an electrical switching member 120 of the electromechanical contactor or SSPC type for interconnecting (in parallel) the two DC buses, and conversely galvanically isolating the S1 assembly on one side. , Bus 1, CVS1, G / D1, TAG1 and on the other side the set S2, Bus 2, CVS2, G / D2, TAG2. With reference to FIG. 3, a two-engine flight phase will be described. Once the two turbine engines TAG1 and TAG2 have been started, the two electrical machines G / D1 and G / D2 driven by the gas generators of the turbine engines TAG1 and TAG2 operate as a generator and the DC / AC converters are driven in a rectifier according to a current law. / voltage adapted to recharge and / or maintain the load of the storage members S1 and S2. The cutoff member 120 is open. The storage members having possibly been unloaded during the start-up of the turbine engines, it may be necessary to wait for the storage members S1 and S2 to be loaded again at their nominal level before allowing take-off.
    [0007] Charging or maintaining the charge of the storage members S1 and S2 (to compensate for the internal losses due for example to the balancing of the cells of a pack of supercapacities or a battery, or the friction of a steering wheel of inertia) is provided independently of the on-board network by taking energy from the gas generator of the turbine engines TAG1 and TAG2 respectively. According to their technology, the compensation of the losses of each storage organ S1 and S2 does not represent more than a few tens of watts in steady state. In this mode of operation, the DC buses are galvanically isolated from one another and operate independently of each other. On the other hand, in a variant, a sequential management of the charging of the storage members according to a hysteresis-type law is used: charging of the body until a threshold of energy E1 is reached, then inhibition of the recharge (thus total stop of the sampling on the gas generator) until the stored energy passes - by the set of the internal losses - below a threshold E2 <El. With technologies battery type or hybrid capacity with balancing circuits active, one reaches the intervals between two phases of recharge rather spaced.
    [0008] With reference to FIG. 4, in twin-engine flight, the energy stored in the members S1 and S2 is used to optimize the operation of the turbomachines. The general idea is to achieve a transient supply of mechanical energy on the gas generator of a turbine engine. Two modes of operation are possible and are detailed below. They are presented for operation with the cutoff member 120 open. First of all we can perform a punctual assistance to accelerations of the gas generator. In the case of a rapid step setting from a low speed, a mechanical power supply on the gas generator improves its acceleration, thus increasing the speed with which the turbine engine delivers power to the free turbine, and consequently substantially reduce the transient drop in rotor speed of the helicopter obtained at the end of the maneuver, thus increasing the margin of safety of the crew. This function provides a significant improvement in performance when the initial regime of the gas generator is low. This operating mode can be activated automatically on request of the turbine computer when several criteria are met, for example and in a nonlimiting manner: the system is available (no fault detected), the energy level stored in the organs S1 and S2 is sufficient, the turbomachine operates, the initial speed of the gas generator is within a given range, a rapid increase in the power demand is detected via the approximation of the operating line of the turbine engine of its limit of protection against pumping. 5 One-off assistance is disabled when the operating line of the turbine engine is moving away from its pumping protection limit, the stored energy level falls below a certain threshold, or the speed is above the pumping limit. a certain threshold. Then, one can perform a punctual assistance to the decelerations of the gas generator 10. In the case of a rapid step decrease during which the deceleration of the gas generator is limited by the anti-extinction law, it is proposed to increase for a few moments the setpoint of generation of the converters so as to take a power important on gas generators. As a result, it is possible to decelerate the gas generator more quickly, thus increasing the speed with which the regulation of the turbine engine decreases the fuel flow injected into the combustion chamber and consequently decreases the amplitude of the engine. transient increase in rotor speed. This operating mode is activated automatically on request of the turbine computer when several criteria are fulfilled, for example and in a nonlimiting manner: the operating line approaches the anti-extinction flow stop, and provided that it is possible storing the energy taken from the gas generator during its deceleration. In one variant, the capacity of the storage member is therefore slightly oversized in order to provide a storable energy margin in all circumstances. Alternatively, a device is provided on the DC bus to dissipate the deceleration energy of the gas generator, such as, for example, a combination of a resistor and a braking chopper arm. One can also perform a punctual assistance type power injection. Pmec mechanical power is injected onto the gas generator so as to obtain a multiplied effect on the free turbine. In certain areas of the flight range, it is possible to recover a K.Pmec power on the free turbine, and thus on the BTP of the helicopter, with a gain K greater than 1. It will be noted that when the conditions 3 0 1 9 If adequate support is provided, assistance with the gas generator can therefore offer a better return than equivalent assistance, but it is injected directly into the free turbine or the BTP. This operating mode can be activated when the level of energy stored in the members S1 and S2 is sufficient, either preventively at the request of the crew, for example in a high mass point-off take-off situation and / or in a condition of altitude and high temperature, either automatically on request of the engine of the turbine engine to provide a short-term power supplement to the emergency regime OEI ("One Engine Inoperative"), for example in case of a drop in speed free turbine below a certain threshold or loss of power detection on another turbine engine. Referring to Figure 5, there is shown a single-engine economic cruise flight phase. When the conditions permitting this mode are met, which implies, among other things, a sufficient level of energy stored in the members S1 and / or S2, the avionics transmits to the turbine computer (TAG2 in the figure) a set-up instruction. Standby. In a first variant shown in FIG. 5, described as a "super slowed-down" variant, the TAG2 calculator reduces the fuel flow and regulates the speed of the gas generator to a low set point, making it possible to desynchronize the power turbine. the BTP (the power supplied to the helicopter is therefore zero) and offering low consumption. Simultaneously the electric machine G / D2 and the associated converter CVS2 are inhibited so as not to draw power on the gas generator of the TAG2. The electric machine G / D1 and its converter CVS1 switch to "generator" mode (if it was not already the case); the two DC buses are electrically connected via the reconfiguration of the cut-off device 120. The energy taken from the gas generator TAG1 is used to maintain the charge of the storage members S1 and S2: this charge-maintaining function can be carried out continuously or on the contrary discontinuous and sequential on each of the two bodies. 301 9 2 1 5 14 In a second variant, shown in Figure 6, the computer of the turbine engine TAG2 cut the fuel flow. The combustion chamber of TAG2 being extinguished, the fuel consumption is zero and the free turbine is out of synchronization with the BTP. Simultaneously, the electric machine G / D2 and the associated converter CVS2 switch to motor mode with a speed setpoint corresponding to the ideal ignition window of the combustion chamber. The gas generator switches to autorotation and, after a few seconds, its speed stabilizes at this setpoint, the combustion chamber being extinguished. The electric machine G / D1 and its converter CVS1 switch to "generator" mode, if it was not already the case. The two DC buses are electrically connected via the reconfiguration of the cut-off device 120. The energy taken from the gas generator of the turbine engine TAG1 is used to maintain the charge of the storage members S1 and S2 and to supply the electric machine. G / D2 via the CVS2 power converter. This last aspect is a prolonged assistance to the gas generator of the turbine engine TAG2, called "turning" mode. In a variant shown in FIG. 7, the supply of fuel to the turbine engine TAG2 is maintained, and a prolonged assistance to the rotation of the gas generator thereof is provided, on the same principle as that presented in FIG. in order to optimize the operation of the turbine and to minimize fuel consumption. In such a mode of operation, called "super assisted idle", CVS2 and G / D2 operate in motor mode. During these operating phases the electrical assembly 100 remains autonomous vis-à-vis the onboard network. The output of the single-engine economy cruise flight can be done in two different ways. First of all, with reference to FIG. 8, when the restart of the TAG2 is not of an emergency character, it is restarted on request from the avionics via the normal procedure: in a first step, the two buses DC are galvanically isolated via the reconfiguration of the electrical switchgear 120. If the turbine engine TAG2 was initially kept in standby combustion chamber on ("super idle" or "super idle assisted" mode), the electric machine G / D2 is controlled so as to provide a driving torque so as to assist punctually, using the energy stored in the storage member S2, the acceleration of the gas generator. Simultaneously, the computer of the TAG2 turbine engine increases the fuel flow according to a predefined law. If the turbine engine TAG2 was initially kept in standby combustion chamber 5 extinguished ("turning" mode), the computer initiates a start sequence similar to that described above, except that the gas generator of the turbine engine TAG2 is already driven into the ideal ignition window. When ignition of the combustion chamber is detected, the torque delivered by the electric machine G / D2 is increased and the computer of the turbine engine TAG2 increases the fuel flow rate 10 according to a predefined law. In both cases, when the NG regime exceeds a threshold of autonomy, the power assistance is cut off and the turbine engine TAG2 accelerates on its own until the flight regime. It should be noted that an analogous sequence makes it possible to start the turbomachines when the helicopter is on the ground, before take-off, the difference being that the gas generator of the turbomachines is initially at a complete stop. Turbomachines are usually started sequentially, one after the other. Once the two turbomachines have started, and before takeoff, the storage members S1 and S2 are reloaded according to the procedure described above (see Figure 3). With reference to FIG. 9, under certain conditions of single-engine economy flight, the crew may need the power of the turbine engine TAG2 quickly: this may be the case for example in the event of loss of power on the turbine engine TAG1, or well in case of need of unexpected power requiring the power of the two turbomachines and thus justifying a fast exit of the single-engine mode (obstacle avoidance etc). In this case, a restart is made via the emergency procedure, the objective being that the TAG2 turbine engine reaches its flight regime or even its OEI regime (One Engine Operative regime, for emergency regime with a single engine running) in a short time. Initially, the two DC buses are galvanically isolated via the reconfiguration of the electrical switchgear 120. If the turbine engine TAG2 was initially kept in standby combustion chamber on (super idle or super assisted idle mode) ), the electric machine G / D2 is controlled to provide a motor torque to assist punctually the acceleration of the gas generator, this assistance being a significantly higher level than for the normal restart procedure. At the same time, the TAG2 turbomachine computer increases the fuel flow rate according to a predefined law, which is also optimized for a rapid restart of the turbine.
    [0009] If the turbine engine TAG2 was initially kept in standby combustion chamber off ("turning" mode), the computer triggers the ignition of the combustion chamber, this operation being facilitated by the fact that the gas generator is already rotated in the ideal ignition window. Then, as before, the computer makes a request for electrical assistance to accelerate the gas generator and increases the fuel flow according to a predefined law, also optimized for rapid restart of the turbine. In both cases, the punctual power assistance on the gas generator is likely to be extended beyond the starter cut-off threshold used for the normal start procedure, in order to minimize the acceleration time of the generator. turbomachine towards the flight regime or the OEI regime. Once the helicopter is on the ground, before cutting the turbines, it may be wise to recharge the storage devices of the electrical hybridization device so that they are ready for subsequent start-up. This procedure can be performed during the mandatory passage to the "idle ground" regime used for the homogenization of the turbomachine temperatures before shutdown. With reference to FIG. 10, a variant is presented. The autonomous electrical assembly 101 is similar to the self-contained electrical assembly 100 presented above, but a single storage unit S replaces the storage members S1 and S2. It is for example dimensioned to ensure the emergency start of a single turbomachine. The advantage is then a gain of almost 2 in terms of mass and compactness. In charging mode (twin-engine operation), one of the two CVS1 or CVS2 power converters is designated as "master" by the supervision computer and is responsible for charging the storage device S. The reconfiguration device 121 allows the storage member S to be connected to the CVS2 converter and to electrically isolate the S-CVS2-G / D2 assembly from the CVS1-G / D1 assembly or, on the contrary, to connect the unit 3 0 1 9 2 1 5 to the CVS1 converter and to electrically isolate the S-CVS1-G / D1 assembly from the CVS2-G / D2 assembly, for the charging phases of the S-element by one or the other. other turbomachines or punctual assistance to a turbomachine. The reconfiguration member 121 is also able to keep the CVS2 (G / D2) -CVS1 (G / D1) assembly electrically connected for the single-engine flight phases involving the feeding of one of the electrical machines driven by engine driven by the other generator ("turnaround" mode and "super assisted idle" mode). With reference to FIG. 11, another variant is presented. The electrical assembly 102 this time is not autonomous vis-à-vis the onboard network. The electrical connection between the electric machine G / D1 and the converter CVS1 indeed borrows the on-board network. The electrical storage unit S is unique and is dedicated to the occasional assistance of the TAG2 turbine engine via the CVS2 converter and the electric machine G / D2. It can be loaded by the converter and the electric machine G / D1 or by the CVS2 converter and the electric machine G / D2, depending in particular on the position of the reconfiguration member 122. The turbine engine TAG1 is not brought to a standby mode during the economic cruise flight. On the other hand, the turbine engine TAG2 can be brought to the standby mode with the combustion chamber on (super assisted idle mode) or the combustion chamber switched off ("turning" mode), the electrical energy required for prolonged assistance to the generator. of gas then from the turbine engine TAG1, via G / D1, CVS1, CVS2 and G / D2, or via ALTI, CVS1, CVS2 and G / D2 (see ALTI in connection with FIG. In this second case, G / D1 can be replaced by a simple, uncontrolled starter. The reconfiguration device 122 makes it possible to connect the storage unit S to the CVS2 converter and to electrically isolate the set S-CVS2-G / D2 from the CVS1-on-board network assembly or, on the contrary, to connect it. storage member S to the CVS1 converter and galvanically isolating the S-CVS1-G / D1 assembly from the CVS2-G / D2 assembly, for the load phases of the S-unit or the point-to-point support at the turbomachine TAG2. With reference to FIG. 12, another variant is presented. The turbine engine TAG1 has an accessories table which comprises power take-offs for two electric machines, here an electric starter machine D1 and a generator electric machine G1. The machine D1, used for the normal start of the turbine engine TAG1, is powered by the on-board network, while the machine G1 is connected to the converter CVS1. The remainder of the circuit diagram is similar to that of FIG. 9. The storage unit S, which is unique, is dedicated to the punctual assistance of the TAG2 turbine engine. The reconfiguration member 123 makes it possible to connect the storage member S to the CVS2 converter and to electrically isolate the set S-CVS2-G / D2 from the assembly CVS1-G1 or, on the contrary, to connect the storage member S to the converter 10 CVS1 and galvanically isolate the assembly S-CVS1-G1 of the assembly CVS2-G / D2-TAG2, for the phases of charge of the organ S by one or other of the turbomachines or occasional assistance to the TAG2 turbomachine. The reconfiguration member 123 is also able to keep connected the CVS2 (G / D2) -CVS1 (G1) assembly for the flight phases involving the supply of the electric machine G / D2 by the electric machine G1. The assembly consisting of elements G1, CVS1, 123, S, CVS2 and G / D2 is an independent electrical assembly, reference 103. It is autonomous vis-à-vis the on-board network. With reference to FIG. 13, another variant is presented. The electrical assembly 104 comprises a CVS1 converter connected to the on-board network. It further comprises a CVS2 converter connected to switching members 130 for connecting either to the electric machine G / D1 connected to the turbine engine TAG1, or to the electric machine G / D2 connected to the turbine engine TAG2. It is excluded that the two electrical machines G / D1 and G / D2 are connected at the same time to the CVS2 converter. A reconfiguration device 124 furthermore makes it possible to connect the single storage device S to the converter CSV1 for its load by the on-board network, or to the converter CVS2 for punctual assistance to one of the turbine engines TAG1 and TAG2, in depending on the position of the switching member 130. The storage member S can also be connected to both CVS1 and CVS2 converters. The reconfiguration device 124 makes it possible to connect the converter CVS1 to the converter CVS2 to enable prolonged assistance to the gas generator of the turbomachine connected to the converter CVS2 by the switching member 130 (especially the standby mode with combustion chamber switching off and holding the gas generator in the preferred ignition window, ie the "super slowed" mode and the mode with the room switched on, ie the "super assisted idling" mode) .
    [0010] It is recalled that the onboard network is powered by one or more generators actuated indirectly or directly by at least one of the turbomachines TAG1 or TAG2, and that when one of them is extinguished, it is necessarily the other which provides long-term power to the on-board network. 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 (13)
    [0001]
    REVENDICATIONS1. Assistance device (100; 101; 102; 103; 104) for a turbine engine (TAG1) with free turbine of an aircraft comprising at least two turbomachines (TAG1, TAG2) with a free turbine, the device comprising an electric starter machine ( Dl) for prolonged assistance of the gas generator of a first turbine engine (TAG1) with energy produced by an electric generating machine (G2) driven by the second turbine engine (TAG2), the device further comprising at least an electrical storage unit (S1; S) electrically connected to said starter electric machine (D1) for providing one-off assistance to said gas generator, characterized in that the starter electric machine (D1) is powered by a first power converter (CVS1) which allows it to exchange energy with the storage device (S1; S) for the occasional assistance, and which transmits to it energy supplied by a second converter. power transmitter (CVS2) for extended assistance.
    [0002]
    2. Assist device according to claim 1, wherein a cut-off device makes it possible to galvanically isolate the two converters (CVS1, CVS2) from one another, the storage member (S1; S) remaining connected to the first converter (CVS1).
    [0003]
    3. Assist device according to one of claims 1 to 2, wherein the first electrical machine (G1 / D1) is also a generator. 25
    [0004]
    4. Assist device according to one of claims 1 to 3, wherein the second electric machine (G2) is driven by the gas generator of the second turbine engine (TAG2).
    [0005]
    5. Assist device according to one of claims 1 to 4, wherein a switching member (120; 121; 122; 123; 124) is used to connect the second converter (CVS2) to the electrical storage member. (51; S).
    [0006]
    6. Assist device according to one of claims 1 to 5, wherein the second converter (CVS2) is powered by a generatorGenerator (G2) powered by the gas generator of a second turbine engine (TAG2) of the aircraft.
    [0007]
    7. Assist device according to one of claims 1 to 6, wherein the electrical storage member (S1; S) can be used to assist any controlled acceleration or deceleration of said gas generator in twin-engine flight condition.
    [0008]
    8. Assist device according to one of claims 1 to 7, comprising a storage element (Si, S2) by a turbomachine (TAG1, TAG2) to participate in point accelerations gas generators of one or the other turbomachines (TAG1, TAG2).
    [0009]
    9. Assist device according to one of claims 1 to 8, wherein the extended assistance can be performed during periods during which said gas generator is not supplied with fuel, the mechanical energy being adapted to maintaining said gas generator at a reduced speed facilitating reignition of said gas generator.
    [0010]
    10. Assist device according to one of claims 1 to 9, wherein the extended assistance can be performed during periods during which said gas generator is kept in operation, the mechanical energy being adapted to maintain said generator of gas at a reduced speed minimizing fuel consumption.
    [0011]
    11.Assist device according to one of claims 1 to 10, wherein the electrical storage member (S1; S) comprises a supercapacitor, a hybrid capacitor, a lithium-ion battery or a flywheel comprising a integrated DC / AC converter.
    [0012]
    12.Dispositif assistance according to one of claims 1 to 11, wherein the electrical storage member (S1; S) is recharged by energy sampling on the gas generator of the first or second turbomachine ( TAG1; TAG2) during periods during which said gas generator is supplied with fuel.
    [0013]
    13.Aironef to at least two free turbine turbomachines, comprising an assistance device according to one of claims 1 to 12.
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    同族专利:
    公开号 | 公开日
    RU2016141965A3|2018-09-11|
    JP2017512940A|2017-05-25|
    RU2686236C2|2019-04-24|
    US10151246B2|2018-12-11|
    EP3123016B1|2018-03-07|
    JP6557321B2|2019-08-07|
    PL3123016T3|2018-07-31|
    US20180187604A1|2018-07-05|
    EP3123016A1|2017-02-01|
    KR20160140833A|2016-12-07|
    KR102285093B1|2021-08-03|
    ES2664446T3|2018-04-19|
    CA2943486C|2021-08-31|
    CA2943486A1|2015-10-01|
    WO2015145077A1|2015-10-01|
    CN106536895A|2017-03-22|
    FR3019215B1|2019-05-31|
    RU2016141965A|2018-04-27|
    CN106536895B|2018-08-07|
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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
    FR1400753|2014-03-27|
    FR1400753A|FR3019215B1|2014-03-27|2014-03-27|ASSISTANCE DEVICE FOR AN AIRCRAFT FREE TURBINE TURBOMACHINE COMPRISING AT LEAST TWO FREE TURBINE TURBINES|FR1400753A| FR3019215B1|2014-03-27|2014-03-27|ASSISTANCE DEVICE FOR AN AIRCRAFT FREE TURBINE TURBOMACHINE COMPRISING AT LEAST TWO FREE TURBINE TURBINES|
    JP2017501506A| JP6557321B2|2014-03-27|2015-03-26|Assistance device for an aircraft free turbine engine having at least two free turbine engines|
    US15/129,240| US10151246B2|2014-03-27|2015-03-26|Assistance device for a free-turbine engine of an aircraft having at least two free-turbine engines|
    PCT/FR2015/050767| WO2015145077A1|2014-03-27|2015-03-26|Assistance device for a free turbine turbomachine of an aircraft comprising at least two free turbine turbomachines|
    CN201580016709.3A| CN106536895B|2014-03-27|2015-03-26|The auxiliary device of freedom turbine for the aircraft including at least two freedom turbines|
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    KR1020167030206A| KR102285093B1|2014-03-27|2015-03-26|An assistance device for a free-turbine engine of an aircraft having at least two free-turbine engines|
    CA2943486A| CA2943486C|2014-03-27|2015-03-26|Assistance device for a free turbine turbomachine of an aircraft comprising at least two free turbine turbomachines|
    ES15725706.4T| ES2664446T3|2014-03-27|2015-03-26|Aircraft comprising at least two turbines with free turbines with assistive devices|
    EP15725706.4A| EP3123016B1|2014-03-27|2015-03-26|Dual turboshaft aircraft with power assistance device|
    PL15725706T| PL3123016T3|2014-03-27|2015-03-26|Dual turboshaft aircraft with power assistance device|
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