• 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:
    The invention relates to a device for rapid reactivation of a turbine engine (6) of a helicopter, characterized in that it comprises a pneumatic turbine (7) mechanically connected to said turbine engine (6) so as to be able to drive it in rotation and ensure its reactivation; a pneumatic storer (9) connected to said pneumatic turbine (7) via a pneumatic circuit (10) supplying pressurized gas to said pneumatic turbine (7); a pneumatic valve (11) with controlled rapid opening arranged on the circuit (10) between said pneumatic storage (9) and said pneumatic turbine (7) and adapted to be placed on command at least in an open position in which the gas can feed said pneumatic turbine (7), or in a closed position in which said pneumatic turbine (7) is no longer supplied with gas under pressure.
    公开号:FR3024180A1
    申请号:FR1457282
    申请日:2014-07-28
    公开日:2016-01-29
    发明作者:Romain Thiriet；Frederic Moulon；Camel Serghine
    申请人:Turbomeca SA；
    IPC主号:
    专利说明:

    [0001] 1 PNEUMATIC DEVICE FOR RAPID REACTIVATION OF A TURBOMOTEUR, ARCHITECTURE OF A PROPULSIVE SYSTEM OF A MULTI-ENGINE HELICOPTER EQUIPPED WITH SUCH A DEVICE AND CORRESPONDING HELICOPTER 1. Technical Field of the Invention The invention relates to an autonomous pneumatic device for quick reactivation of a turbine engine. The invention also relates to an architecture of a propulsion system of a multi-engine helicopter - in particular twin-engine or three-engine - equipped with at least one such rapid reactivation device. The invention also relates to a helicopter comprising a propulsion system having such an architecture. 2. Technological background A twin-engine helicopter or three-engine helicopter presents in known manner a propulsion system comprising two or three turbine engines, each turbine engine comprising a gas generator and a free turbine driven in rotation by the gas generator, and secured to a shaft. Release. The output shaft of each free turbine is adapted to set in motion a power transmission box, which itself drives the rotor of the helicopter equipped with blades with variable pitch. It is known that the turbine engines of the helicopter operate at speeds that depend on the flight conditions of the helicopter. In all of the following text, a helicopter is said to be in a cruising flight situation when it operates under normal conditions, during all phases of flight, excluding transitional phases of take-off, climb, landing or flight. stationary. Throughout the following text, a helicopter is said to be in a critical flight situation when it is necessary for it to have the total installed power, that is to say in the transitional phases of take-off, climb, landing and engine in which one of the turboshaft engines failed, designated by the acronym OEI 3024180 2 (One Engine Inoperative). It is known that when the helicopter is in cruise flight, the turboshaft engines operate at low power levels, lower than their maximum continuous power. These low power levels result in a specific consumption (hereinafter Cs) defined as the ratio between the hourly fuel consumption by the turbine engine combustion chamber and the mechanical power supplied by this turbine engine, which is in the order of 30 % Cs of the maximum takeoff power, and therefore overconsumption of fuel in cruising flight.
    [0002] In addition, the turboshaft engines of a helicopter are designed oversize to be able to keep the helicopter in flight in the event of failure of one of the engines. This flight situation corresponds to the OEI regime described above. This flight situation arises following the loss of an engine and results in the fact that each running engine provides a power well beyond its nominal power to allow the helicopter to face a perilous situation, then to be able to continue his flight. On the other hand, the turboshaft engines are also oversized to ensure the flight in all the flight range specified by the aircraft manufacturer and in particular the flight at high altitudes and in hot weather. These flight points, which are very restrictive, especially when the helicopter has a mass close to its maximum take-off mass, are encountered only in certain cases of use. These oversized turboshaft engines are penalizing in terms of weight and fuel consumption. In order to reduce this consumption in cruising flight, it is envisaged to put one of the turbine engines on stand-by. The active engine (s) then operate at higher power levels to provide all the necessary power and therefore to more favorable Cs levels. The applicants have proposed in applications FR1151717 and FR1359766, methods for optimizing the specific consumption of turbine engines of a helicopter by the possibility of placing at least one turbine engine in a stabilized power regime, said continuous, and at least one 3024180 3 turbine engine in a particular standby mode from which it can exit urgently or normally, as needed. An output of the standby mode is said to be normal when a change of flight situation requires the activation of the turbine engine in standby, for example when the helicopter will go from a cruising flight situation to a landing phase. Such a normal standby output takes place over a period of 10 seconds to 1 minute. An exit from the standby mode is said to be fast when a breakdown or a deficit of power of the active engine intervenes or that the flight conditions suddenly become difficult. Such a fast wake-up output is performed for less than 10s.
    [0003] The output of a standby mode of a turbine engine is obtained for example by means of a turbine engine restart pack associated with an energy storage device such as an electrochemical storage of the Li-Ion battery type. an electrostatic storage of the overcapacity type, which makes it possible to supply the turbine engine with the energy necessary to reactivate and rapidly reach a nominal operating speed. Such a pack of quick reactivation of the turbine engine standby has the disadvantage of significantly increase the total weight of the turbine engine. The gain in fuel consumption obtained by the standby of the turbine engine is therefore partly lost by the overweight caused by the reactivation device and the associated energy storage device, in particular when each turbine engine is equipped with such a device. emergency reactivation device. In addition, these electrotechnical components may be dependent on the electrical architecture of the helicopter on which they are mounted. The inventors have therefore sought to reconcile a priori incompatible problems that are the possibility of placing the helicopter in economic flight phase, that is to say to put at least one turbine engine in standby, without generating excessive overweight of the entire propulsion system, but while allowing a quick exit from the standby mode. In other words, the inventors have sought to propose a new device for rapid reactivation of a turbine engine and a new architecture of the propulsion system of a twin-engine or three-engine helicopter. OBJECTS OF THE INVENTION The object of the invention is to provide a device for rapid reactivation of a turbine engine which overcomes the disadvantages of prior solutions. The invention also aims to provide a new architecture of the propulsion system 5 of a multi-engine helicopter. The invention also aims to provide an architecture of a propulsion system of a multi-engine helicopter that allows the standby of a turbine engine and its rapid reactivation. The invention also aims to provide, in at least one embodiment of the invention, an architecture that has a weight and volume not crippling to be embedded in a helicopter. The invention also aims to provide, in at least one embodiment of the invention, an architecture that has a lower cost than the architectures of the prior art with equal performance.
    [0004] The invention also aims to provide a method for rapid reactivation of a turbine engine. 4. DESCRIPTION OF THE INVENTION To this end, the invention relates to a device for rapid reactivation of a turbine engine of a helicopter, characterized in that it comprises: a pneumatic turbine mechanically connected to said turbine engine so as to be able to drive in rotation and ensure its reactivation, a pneumatic storage connected to said pneumatic turbine by means of a pneumatic circuit for supplying pressurized gas to said pneumatic turbine, a pneumatic valve with quick opening controlled arranged on the pneumatic circuit between said storer and said pneumatic turbine and adapted to be placed on command at least in an open position in which the gas can supply said pneumatic turbine, thus allowing a reactivation of said turbine engine, or in a closed position in which said pneumatic turbine no longer supplied with pressurized gas. A device for reactivating a turbine engine according to the invention thus provides a pneumatic device - preferably completely independent of the electrical network of the helicopter on which such a turbine engine is intended to be mounted - to ensure the reactivation of the turbine engine. A device for quickly reactivating a turbine engine is primarily intended to quickly reactivate a turbine engine standby so that it can quickly exit the idle mode in which it was placed to provide new mechanical power. According to another application, a fast reactivation device can also serve as a starting device for a turbine engine, that is to say, start-up of a turbine engine, without previous standby. However, throughout the following description, it is essentially discussed the use of the device according to the invention as a device for reactivating a turbine engine standby. A turbine engine comprises in a known manner a gas generator and a free turbine fed by the gas generator and connected to a power transmission box. Preferably, a reactivation device according to the invention provides for the gas generator of the turbine engine to be rotated by the pneumatic turbine adapted to transform the pneumatic power of the pressurized gas which supplies the turbine with a mechanical driving power of the turbine. gas generator. The gas supply of the pneumatic turbine is carried out by the cooperation of a pneumatic storer and a controlled fast opening valve. Such a reactivation device is therefore independent of the electric network of the helicopter and does not require bulky storage batteries. The proposed solution therefore ensures rapid reactivation of a turbine engine, in particular a turbine engine placed in a standby mode, without generating problems of size, weight and cost. In addition, a device according to the invention is easy to use and perhaps 3024180 6 tested on the bench before its integration on a helicopter. Advantageously, a device according to the invention further comprises an expander arranged on the pneumatic circuit between the pneumatic valve and the pneumatic turbine and configured to regulate the pressure of the gas supplying the pneumatic turbine. An expansion valve therefore makes it possible to adapt the pressure of the gas supplied to the pneumatic turbine to the type of pneumatic turbine used and to the type of pneumatic storage unit used. According to one variant, the pneumatic storer comprises a high-pressure gas, for example between 200 and 400 bar, and the pneumatic turbine 10 is supplied via the expander with a gas having a pressure between 5 and 50 bar. Advantageously and according to the invention, the pneumatic turbine is mechanically connected to the turbine engine by means of at least one freewheel. The presence of the freewheel makes it possible to avoid spontaneous entrainment of the pneumatic turbine by the gas generator when the latter supplies mechanical power. Advantageously, the freewheel is mounted on an accessory box of the turbine engine. Advantageously and according to the invention, the pneumatic storer contains a gas mixture comprising, by mass, at least 50% of a neutral gas, and a fire extinguishing agent. Such a mixture of gases not only enables the pneumatic turbine to be supplied with gas to ensure the reactivation of the turbine engine, but also to supply a fire extinguishing system arranged, for example, in the vicinity of the turbine engine to allow the extinction of all possible fire of this turbine engine. The neutral gas can be of any type, such as nitrogen, helium or argon. The fire extinguishing agent is, for example, halon. A device according to this variant, in combination with a fire extinguishing system, therefore makes it unnecessary to equip helicopters with dedicated fire-extinguishing bottles.
    [0005] Advantageously and according to the invention, the turbine comprises a low pressure supply plug configured to perform an integrity test 3024180 7 of the kinematic chain formed of the pneumatic turbine and the freewheel. Such a power supply makes it possible to test the kinematic chain formed of the pneumatic turbine and the freewheel and thus to ensure that the turbine engine can effectively be reactivated quickly in case of emergency. It's a way to put in place control and security measures. Such a test can for example be carried out on the ground by the use of an air compressor of the park group type. This test can also be performed in flight by an air intake at the compressor outlet on one or the other of the turboshaft engines. Advantageously and according to the invention, the pneumatic valve is controlled in position by an electronic equipment and controlled in opening by a pyrotechnic equipment. A pyrotechnic equipment allows a quick opening of the pneumatic valve and therefore a quick reactivation of the turbine engine. The invention also relates to an architecture of a propulsion system 15 of a multi-engine helicopter comprising turbine engines connected to a power transmission box, characterized in that it comprises: at least one turbine engine among said turboshaft engines, said turbine engine hybrid, capable of operating in at least one watch state during a stabilized flight of the helicopter, the other 20 turboshaft engines operating alone during this stabilized flight, at least one rapid reactivation device of a hybrid turbine engine according to the invention adapted to be able to output the hybrid turbine engine from said idle mode and reach a speed, said rated speed, wherein it provides a mechanical power to said 25 transmission box power. A device for reactivating a turbine engine according to the invention is particularly intended to be integrated into an architecture of a propulsion system of a multi-engine helicopter comprising at least one turbine engine capable of being put on standby. The pneumatic reactivation device makes it possible to ensure the rapid reactivation of the turbine engine in standby if necessary. Advantageously, an architecture according to the invention comprises at least 3024180 8 a fire extinguishing device arranged in the vicinity of a turbine engine and connected to said pneumatic valve of an emergency starting device through a pipe, called fire, so that said gas of said pneumatic storage of this reactivation device can be driven on command of said valve to said extinguishing device. An architecture according to this variant comprises at least one fire extinguishing device arranged in the vicinity of a turbine engine to be able to extinguish a fire within the turbine engine by using the pneumatic circuit of the fast reactivation device. To do this, the hydropneumatic storage unit 10 advantageously contains a mixture of gases comprising in bulk, at least 50% of a neutral gas, and a fire extinguishing agent. Advantageously, an architecture according to the invention comprises two hybrid turbine engines and two emergency starting devices according to the invention, each hybrid turbine engine being associated with a dedicated reactivation device. According to this variant, the architecture has a separate pneumatic supply for each pneumatic starter turbine of each hybrid turbine engine. Advantageously, an architecture according to the invention comprises two hybrid turbine engines and a single reactivation device according to the invention which comprises two pneumatic turbines connected respectively to each hybrid turbine engine, said pneumatic valve being a three-way valve controlled to direct the gas towards said pneumatic turbine of the hybrid turbine engine to reactivate.
    [0006] According to this variant, the valve is controlled to direct the gas of the pneumatic circuit to the hybrid turbine engine which must be reactivated. The invention also relates to a helicopter comprising a propulsion system characterized in that said propulsion system has an architecture according to the invention.
    [0007] The invention also relates to a method for rapid reactivation of a turbine engine of a helicopter, characterized in that it comprises: 3024180 9 a step of controlling the opening of a pneumatic valve arranged on a pneumatic circuit between a storer pneumatic turbine and a pneumatic turbine mechanically connected to said turbine engine, a step of routing the gas taken to said pneumatic turbine, a step of transformation by said pneumatic turbine of the pneumatic power of said pressurized gas in mechanical power to ensure the reactivation of the turbine engine.
    [0008] The invention also relates to a device for reactivating a turbine engine, an architecture of a propulsion system of a multi-engine helicopter, a helicopter equipped with a propulsion system having such an architecture, and a method for reactivating a turbine engine. characterized in combination by all or some of the features mentioned above or hereinafter. 5. BRIEF DESCRIPTION OF THE DRAWINGS Other objects, features and advantages of the invention will become apparent on reading the following description given solely by way of non-limiting example and which refers to the appended figures in which: FIG. 1 is a diagrammatic view of FIG. A device for reactivating a turbine engine according to one embodiment of the invention, FIG. 2 is a schematic view of an architecture of a propulsion system of a helicopter according to one embodiment of the invention. FIG. 3 is a schematic view of an architecture of a propulsion system of a helicopter according to another embodiment of the invention, FIG. 4 is a schematic view of an architecture of a propulsion system of a According to another embodiment of the invention, FIG. 5 is a schematic view of an architecture of a propulsion system of a helicopter according to another embodiment of the invention, the FIG. 6 is a schematic view of a helicopter comprising a propulsion system having an architecture according to the invention. 6. DETAILED DESCRIPTION OF AN EMBODIMENT OF THE INVENTION In the figures, the scales and the proportions are not respected for purposes of illustration and clarity. FIG. 1 is a schematic view of a device for reactivating a turbine engine 6 according to one embodiment of the invention. Such a device comprises a pneumatic turbine 7 mechanically connected to the turbine engine 6 by means of a freewheel 8. This pneumatic turbine 7 may be a radial or axial turbine, with one or more stages. Its function is to transform the pneumatic power it receives into a mechanical power enabling the turbine engine 6 to be reactivated. This pneumatic turbine 7 is preferably mounted on the turbine engine 6 by means of a box of accessories. , the device further comprises a pneumatic storage 9 connected to the pneumatic turbine 7 by means of a pneumatic circuit for supplying pressurized gas to this pneumatic turbine. The supply of the pneumatic turbine 7 is dependent on a pneumatic valve with fast opening, controlled, which is arranged on the pneumatic circuit between the storer 9 and the pneumatic turbine 7. This pneumatic valve 11 is, in the embodiment of FIG. 1, a two-way valve controlled by a control device 12, which is preferably the control computer of the turbine engine 6, which also makes it possible to define the engine speed. operation of the turbine engine. When the valve 11 is controlled in opening, the gas of the storer 9 is ejected towards the pneumatic turbine 7 so that it can transform the pneumatic power of the received gas into a mechanical power output. The pneumatic circuit further comprises an expander 14 arranged between the storer 9 and the pneumatic turbine 7 to regulate the pressure of the gas supplying the pneumatic turbine 7. The pneumatic storer 9 further comprises a pressure sensor 40 and a safety valve 41. The pneumatic storer 9 has, for example, a nitrogen capacity of 250 bar. The reactivation device of FIG. 1 advantageously equips an architecture of a propulsion system of a twin-engine helicopter as represented in FIG. 2. According to the embodiment of FIG. 2, the propulsion system comprises two turboshaft engines 6, 16 connected to a transmission box 22, which itself drives a rotor of the helicopter (not shown in the figures). Each turbine engine is a hybrid turbine engine, capable of being placed in at least one watch state during a stabilized flight of the helicopter, which can quickly emerge by means of a reactivation device according to the invention.
    [0009] A turbine engine comprises in known manner a gas generator, a combustion chamber and a free turbine. The standby mode is for example one of the following operating modes: a standby mode, called idle, in which the combustion chamber is lit and the shaft of the gas generator rotates at a speed between 60 and 80% of the nominal speed, a standby mode, said super-idle, in which the combustion chamber is lit and the shaft of the gas generator rotates at a speed between 20 and 60% of the nominal speed, a regime of standby, said assisted super-idle, in which the combustion chamber is lit and the shaft of the gas generator rotates, assisted mechanically, at a speed between 20 and 60% of the nominal speed, a standby mode, said turning gear, in which the combustion chamber is extinguished and the shaft of the gas generator rotates, mechanically assisted, at a speed of between 5 and 20% of the nominal speed, a standby mode, said stop, in which the room Re combustion is off and the gas generator shaft is shut down completely.
    [0010] The reactivation device comprises, in addition to the elements described in connection with FIG. 1, a pneumatic turbine 17 connected to the turbine engine 16 by means of a freewheel 18. In addition, the pneumatic circuit extends from the storer 9. pneumatic up to the pneumatic turbine 17 and the pneumatic turbine 7. The valve 11 controlled is, according to this embodiment, a three-way valve adapted to allow, on command, either the supply of the pneumatic turbine 17 connected to the turbine engine 16, or the supply of the turbine 7 pneumatic turbine engine 6 The control is a function of the engine in standby to emergency out of its standby mode. The operating principle of the reactivation device of this architecture is, for each turbine engine 6, 16, identical to that described with reference to FIG. 1. FIG. 3 is an architecture according to another embodiment of the invention. According to this embodiment, a separate reactivation device is provided for each turbine engine. In other words, a pneumatic storer 29, 39 is associated with each pneumatic turbine 7, 17 and a two-way valve 11, 21 is associated with each storer 29, 39 for supplying the turbines and restarting them. the corresponding turbine engine. The valves 11, 21 are controlled respectively by calculators 12, 13, a device calculator. Alternatively, a single computer can control both valves. In addition, each turbine is associated with a dedicated expander 14, 24 and intended to regulate the pressure of the gas supplying the corresponding turbine. The architecture of FIG. 4 is based on the architecture of FIG. 3 and additionally comprises elements described in connection with FIG. 3, a fire extinguishing system. This extinguishing system comprises a device 30 for fire extinguishing by turbine engine. The architecture of Figure 4 thus comprises two extinguishing devices. Each device comprises a pipe 25, 3024180 13 fire arranged between the corresponding valve 21, 31 and a fire nozzle 26, 36 arranged in the vicinity and towards the turbine engine 6, 16 corresponding so as to be able to project gas to the turbine engine in case of 'fire. According to this embodiment, the valves 11, 21 are three-way valves. In case of detection of a fire in the vicinity of a turbine engine, for example the turbine engine 6, by a fire sensor, the unit 12 controls the opening of the valve 11 corresponding to the turbine engine 6 so that the gas stored in the storer 29 (formed of a mixture of a neutral gas and a fire extinguishing agent of the halon type) is propelled towards the fire hose 26 to extinguish the fire of the turbine engine 6.
    [0011] The architecture of FIG. 5 is a variant of the architecture of FIG. 4 in which each fire lance 26, 36 can be fed by each pneumatic storer 29, 39 by control of the valve 11, 21 which are valves 4. tract. To do this, each fire hose is fed by two separate fire lines. Such an architecture makes it possible to use the gases of each reactivation device to treat a fire of one or the other of the turbine engines. Figure 6 is a schematic view of a twin-engine helicopter comprising a propulsion system having an architecture according to the invention. The propulsion system comprises in particular two turboshaft engines 6, 16 adapted to drive a rotor in rotation through the power transmission box 22. In this figure, the reactivation devices are not shown for the sake of clarity. Only the turbine engines 6, 16 are shown, it being understood that each turbine engine is equipped with a reactivation device according to the invention. The principle of using a device for reactivating a turbine engine 25 in a two-engine architecture as represented by FIG. 2 is as follows: when the flight conditions are favorable, an order is issued to place a turbine engine in standby to save fuel (idle mode selected from the idle modes mentioned above), 30 - the turbine engine computers then determine which turbine engine can be put on standby and order its standby 3024180 14 (in the following it is considered that the turbine engine 6 is put on standby and that only the turbine engine 16 provides power to the transmission box 22), the turbine engine 6 is in standby mode (this standby mode can be one standby modes mentioned above, with room on or off, mechanically assisted or not), - during the flight, the turbine engine 16 suddenly breaks down or the pilot decides to reactivate the turbom quickly 6 for a particular emergency maneuver, 10 the combustion chamber of the turbine engine 6 is then quickly re-lit (in the case of a room standby mode off), after a predetermined time, the control unit 12 orders the opening of the valve 11 to the turbine engine 6, the pneumatic turbine 7 then passes quickly (in a time less than the second) 0 rpm at the docking speed of the gas generator initially in standby mode by transforming the pneumatic power in a mechanical power for driving the gas generator of the turbine engine 6 through the freewheel 8, 20 the pneumatic turbine 7 continues driving the turbine engine 6 for a short time, for example less than 3s, during which the turbine engine has reached its emergency regime, rapid reactivation of the turbine engine 6 is obtained. The docking speed corresponds to the idle speed of the gas generator divided by the speed reduction ratio between the shaft of the gas generator and the inlet of the accessory box of the turbine engine on which the starter is mounted. pneumatic. A device according to the invention thus allows to quickly reactivate a turbine engine standby using only inexpensive organs, easy to use and installation, which can be tested on benches. The invention is not limited to the embodiments described. In particular, the architecture may comprise three turbine engines for the equipment of a three-engine helicopter and those skilled in the art will easily determine on the basis of the teachings of this text how to adapt the described embodiments to a multi-propulsion system. engine, including three-engine.
    [0012] Although dedicated to fast reactivation phases, the invention can also be used during a quick start on the ground or during a rapid restart in flight.
    权利要求:
    Claims (12)
    [0001]
    REVENDICATIONS1. Device for rapid reactivation of a turbine engine (6) of a helicopter, characterized in that it comprises: - a pneumatic turbine (7) mechanically connected to said turbine engine (6) so as to be able to drive it in rotation and ensure its reactivation, - a pneumatic storer (9) connected to said pneumatic turbine (7) via a pneumatic circuit (10) supplying pressurized gas to said pneumatic turbine (7), - a pneumatic valve (11) controlled quick-opening device arranged on the pneumatic circuit (10) between said storer (9) and said pneumatic turbine (7) and adapted to be placed on command at least in an open position in which the gas can supply said pneumatic turbine (7) , thus enabling reactivation of said turbine engine (6), or in a closed position in which said pneumatic turbine (7) is no longer supplied with gas under pressure.
    [0002]
    2. Device according to claim 1, characterized in that it further comprises an expander (14) arranged on said circuit (10) pneumatic between said valve (11) pneumatic and said turbine (7) pneumatic and configured to regulate the pressure said gas supplying said pneumatic turbine (7).
    [0003]
    3. Device according to one of claims 1 or 2, characterized in that said pneumatic turbine (7) is mechanically connected to said turbine engine (6) through at least one wheel (8) free.
    [0004]
    4. Device according to one of claims 1 to 3, characterized in that said pneumatic storage (9) contains a gas mixture comprising in bulk, at least 50% of a neutral gas, and a fire extinguishing agent.
    [0005]
    5. Device according to one of claims 1 to 4, characterized in that said pneumatic turbine (7) comprises a low pressure supply plug 3024180 17 configured to perform an integrity test of the kinematic chain formed of the turbine (7) pneumatic and free wheel (8).
    [0006]
    6. Device according to one of claims 1 to 5, characterized in that said pneumatic valve (11) is controlled in position by an electronic equipment and controlled in opening by a pyrotechnic equipment.
    [0007]
    7. Architecture of a propulsion system of a multi-engine helicopter comprising turbine engines (6, 16) connected to a transmission box (22), characterized in that it comprises: - at least one turbine engine ( 6, 16) among said turboshaft engines, said hybrid turbine engine, capable of operating in at least one watch state during a stabilized flight of the helicopter, the other turboshaft engines operating alone during this stabilized flight, - at least one device for rapid reactivation of a hybrid turbine engine according to one of claims 1 to 6 adapted to be able to output this hybrid turbine engine from said idle mode and reach a speed, said rated speed, in which it provides a mechanical power to said box of power transmission.
    [0008]
    8. Architecture according to claim 7, characterized in that it comprises at least one fire extinguishing device (26, 36) arranged in the vicinity of a turbine engine (6, 16) and connected to said valve (11, 21). pneumatic device of a device for rapid reactivation by means of a pipe, said pipe (25, 35) fire, so that said gas of said pneumatic storage (29, 39) of this starting device can be driven to order from said valve (11, 21) to said extinguishing device.
    [0009]
    9. Architecture according to one of claims 7 or 8, characterized in that it comprises two turboshaft engines (6, 16) hybrids and two rapid reactivation devices according to one of claims 1 to 6, each hybrid turbine engine being associated with a dedicated reactivation device. 30
    [0010]
    10. Architecture according to one of claims 7 or 8, characterized in that it comprises two turboshaft engines (6, 16) hybrids and a single device 3024180 18 reactivation according to one of claims 1 to 6 which comprises two turbines ( 7, 17) respectively connected to each hybrid turbine engine (6, 16), said pneumatic valve (11) being a three-way valve controlled to direct the gas towards said pneumatic turbine of the hybrid turbine engine to be reactivated. 5
    [0011]
    11. Helicopter comprising a propulsion system characterized in that said propulsion system has an architecture according to one of claims 7 to 10.
    [0012]
    12. A method for rapid reactivation of a turbine engine (6) of a helicopter, characterized in that it comprises: a step of opening control of a valve (11) pneumatic 10 arranged on a circuit (10) pneumatic between a pneumatic storage unit (9) and a pneumatic turbine (7) mechanically connected to said turbine engine (6), a step for routing the gas taken to said pneumatic turbine (7), a step of transformation by said pneumatic turbine (7) of the pneumatic power of said pressurized gas in mechanical power to ensure the reactivation of the turbine engine (6).
    类似技术:
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    同族专利:
    公开号 | 公开日
    US20170211483A1|2017-07-27|
    CN106574515B|2020-05-19|
    FR3024180B1|2016-07-22|
    EP3175090B1|2019-05-22|
    EP3175090A1|2017-06-07|
    PL3175090T3|2019-09-30|
    JP2017523342A|2017-08-17|
    CA2955637A1|2016-02-04|
    RU2017103313A|2018-08-28|
    CN106574515A|2017-04-19|
    RU2017103313A3|2019-01-29|
    KR20170031703A|2017-03-21|
    RU2703862C2|2019-10-22|
    BR112017001161A2|2018-01-30|
    WO2016016547A1|2016-02-04|
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    2021-04-09| ST| Notification of lapse|Effective date: 20210305 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1457282A|FR3024180B1|2014-07-28|2014-07-28|PNEUMATIC DEVICE FOR RAPID REACTIVATION OF A TURBOMOTEUR, ARCHITECTURE OF A PROPULSIVE SYSTEM OF A MULTI-ENGINE HELICOPTER EQUIPPED WITH SUCH A DEVICE AND CORRESPONDING HELICOPTER|FR1457282A| FR3024180B1|2014-07-28|2014-07-28|PNEUMATIC DEVICE FOR RAPID REACTIVATION OF A TURBOMOTEUR, ARCHITECTURE OF A PROPULSIVE SYSTEM OF A MULTI-ENGINE HELICOPTER EQUIPPED WITH SUCH A DEVICE AND CORRESPONDING HELICOPTER|
    US15/327,631| US20170211483A1|2014-07-28|2015-07-21|Pneumatic device for rapidly reactivating a turbine engine, architecture for a propulsion system of a multi-engine helicopter provided with such a device, and corresponding helicopter|
    CN201580040408.4A| CN106574515B|2014-07-28|2015-07-21|Pneumatic device, architecture of a propulsion system of a multi-engine helicopter, and helicopter|
    PL15753725T| PL3175090T3|2014-07-28|2015-07-21|Pneumatic device for rapidly reactivating a turbine engine, architecture for a propulsion system of a multi-engine helicopter provided with such a device, corresponding helicopter and method|
    JP2017503473A| JP2017523342A|2014-07-28|2015-07-21|Gas pressure device for rapid reactivation of turbine engines, architecture of a multi-engine helicopter propulsion system equipped with such a device, and corresponding helicopter|
    BR112017001161-1A| BR112017001161A2|2014-07-28|2015-07-21|turbocharger rapid reactivation pneumatic device, architecture of a multi-engine helicopter propulsion system equipped with such a device and corresponding helicopter|
    KR1020177002789A| KR20170031703A|2014-07-28|2015-07-21|Pneumatic device for rapidly reactivating a turbine engine, architecture for a propulsion system of a multi-engine helicopter provided with such a device, and corresponding helicopter|
    CA2955637A| CA2955637A1|2014-07-28|2015-07-21|Pneumatic device for rapidly reactivating a turbine engine, architecture for a propulsion system of a multi-engine helicopter provided with such a device, and corresponding helicopter|
    EP15753725.9A| EP3175090B1|2014-07-28|2015-07-21|Pneumatic device for rapidly reactivating a turbine engine, architecture for a propulsion system of a multi-engine helicopter provided with such a device, corresponding helicopter and method|
    PCT/FR2015/052009| WO2016016547A1|2014-07-28|2015-07-21|Pneumatic device for rapidly reactivating a turbine engine, architecture for a propulsion system of a multi-engine helicopter provided with such a device, and corresponding helicopter|
    RU2017103313A| RU2703862C2|2014-07-28|2015-07-21|Pneumatic device for fast reactivation of gas turbine engine, power plant structure of multi-engine helicopter equipped with such device and corresponding helicopter|
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