• 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 twin-engine rotorcraft equipped with a fuel supply system for combustion engines (2,3,4) of an engine group (1) of the rotorcraft, including main engines (2,3 ) capable of driving alone in flight at least one rotor (5) of the rotorcraft and of which an auxiliary motor (4) mechanically connected to the rotor (5) is however unable to provide isolation flight training. The auxiliary engine (4) is supplied with fuel by auxiliary pumps (33,32) collecting the fuel from both main fuel tanks (11,12) from which the main tanks (11,12) ) the main engines (2, 3) are respectively supplied with fuel.
    公开号:FR3021629A1
    申请号:FR1401226
    申请日:2014-05-28
    公开日:2015-12-04
    发明作者:Sylvain Bornes
    申请人:Airbus Helicopters SAS；
    IPC主号:
    专利说明:

    [0001] 1 Twin-engined rotorcraft equipped with a fuel supply system for a power unit including an auxiliary power unit (APU). The present invention is in the field of rotorcraft and is more specifically the fuel supply of a group of engines fitted to a rotorcraft. The present invention relates to a fuel supply architecture of a multi-engine power unit of a rotorcraft, providing mechanical power for at least driving of at least one rotor of the rotorcraft. Rotorcraft are rotary wing aircraft having one or more rotors providing at least the lift of the rotorcraft, or even its propulsion and / or its flight guidance. The rotorcraft are also equipped with various auxiliary mechanical power consuming members, such as compressors, electric power generating machines and / or a ventilation, heating and / or air conditioning installation for example. In this context, the rotorcraft are equipped with a motorization unit comprising one or more combustion engines, in particular turbine engine (s), including one or more main engines and an auxiliary engine commonly designated by APU (according to the acronym English Auxiliary Power Unit). The main engines are typically sized to provide the mechanical power required to drive the various mechanical power consuming members of the rotorcraft in flight, including the rotor or rotors and said auxiliary members. For this purpose, at least the main motors are engaged on a mechanical power transmission chain from which the various members of the rotorcraft consuming mechanical power are driven. The auxiliary motor is typically sized to provide the mechanical power necessary to drive the auxiliary members when the rotorcraft is on the ground. For this purpose, the auxiliary motor is engaged on the power transmission mechanical chain being usually excluded from a mechanical engagement with the rotorcraft rotor or rotors, given its operation traditionally reserved for driving the organs. Auxiliaries out of flight situation of the rotorcraft. According to a particular category of rotorcraft, commonly referred to as category A, the engine group comprises several main engines simultaneously providing the mechanical power required for the rotorcraft in flight. Category A rotorcraft may fly over sensitive areas subject to the ability of at least one main engine to provide the mechanical power required by the rotorcraft in flight in the event of failure of one of the main engines of the power unit. . In this context, the authorization to fly over a sensitive territory by a category A rotorcraft is conditional on a separation of the means providing the main engines their individual operating autonomy. Indeed, in case of failure of one of the main engines whose operation is defective, at least one other main motor must be able to drive said at least one rotor without its operation is affected by the failure of the main engine defective .
    [0002] This is particularly so with regard to the fuel supply arrangements for the various main engines of the engine group. To this end, the category A rotorcraft are typically equipped with a fuel supply unit of the engine group comprising several fuel supply assemblies respectively allocated to the individual fuel supply of the various main engines.
    [0003] Conventionally, the different fuel supply assemblies are hydraulically insulated from each other. Each fuel supply assembly typically comprises a fuel tank, potentially consisting of one or more fuel reserves in fluid communication with each other, and a fluid circuit capable of conveying the fuel from the tank to the main engine which is affected. The individual fuel supply of the main engines is conventionally carried out via main pumps 10 driven by the main engines. More particularly considering a given fuel supply assembly, the fluid circuit comprises at least one or more pipes and a said main pump driven by the main engine. The main pump draws fuel from the tank to the main engine through a feed line of the fluid circuit. Alternatively, the fuel supply assemblies may also each include at least one booster pump dipped into the tank to discharge fuel to the main engine to initiate startup. There is the problem of a possible depletion of the fuel tanks, which may for example be caused by a leak of fuel out of a defective tank or as a result of the consumption by the main engine assigned to the fuel tank. all fuel initially contained in this tank. That is why it is common to equip each of the tanks of a nipple of predefined capacity. For a given fuel supply assembly, the nanny provides a reserve of fuel for operation of the main engine 30 for a specified time in case of exhaustion of the fuel tank.
    [0004] The nanny is conventionally disposed within the fuel tank and is supplied with fuel by at least one transfer pump. The transfer pump or pumps continuously feed the fuel from the tank to the nanny, the nanny 5 being provided with a weir restituting the overflow of fuel to the tank. These provisions are such that the nanny is kept full of fuel in the absence of a fuel fault inside the tank. In case of exhaustion of the fuel tank, the main engine has a predefined operating autonomy according to the capacity of the nanny. Where appropriate and in order to reduce the number of hydraulic members employed by the fuel supply installation, the transfer pump or pumps of the same fuel supply assembly can be further exploited to form said booster pumps. It is also common to provide an intercommunication circuit between the different tanks of the fuel supply system, to allow a fuel exchange between the tanks, in particular to balance the distribution of the onboard fuel mass with the fuel tanks. edge of the rotorcraft. Subject to the activation of a hydraulic unit integrated in the intercommunication circuit, the fuel of one tank may be used to maintain a quantity of fuel available in another tank or at least in the tank assigned to the other tank. tank. To find a technological environment similar to the present invention, reference may be made, for example, to document EP 2 567 896 (EUROCOPTER) which describes such a fuel supply installation fitted to a twin-engine rotorcraft.
    [0005] In general, a constant search lies in a simplification of the organization of equipment mounted on board rotorcraft, in particular to reduce the costs of design, installation on board and maintenance of said equipment, as well as for reduce the overall mass of rotorcraft. Such a search for simplification concerns, among other things, the fuel supply installations of the engine group of a rotorcraft, as mentioned in document EP 2 567 896. However, such a search for simplification must fall within the scope of the constraints. in-flight safety of category A multi-engine rotorcraft, especially in the event of fuel exhaustion of one of the tanks and / or in the event of failure of one of the main engines. With regard to the auxiliary engine, it may have an auxiliary fuel supply assembly whose architecture is simplified, given its function traditionally reserved for driving the auxiliary members when the rotorcraft is at ground. Such simplified architecture of the auxiliary fuel supply assembly makes it possible in particular to operate a single auxiliary fuel supply pump of the auxiliary engine that can draw fuel from a fuel tank specifically dedicated to the fuel supply of the engine. auxiliary engine, or even from one of the tanks assigned to supply fuel to a main engine.
    [0006] It may, however, be advantageous to further use the auxiliary engine in flight to participate in the training of the rotors of the rotorcraft, providing a mechanical power booster in cases of particular flights for which mechanical power is required. consequent, such as hovering, take-off or landing, or even in case of failure of one of the main engines for example.
    [0007] However, in this case, the auxiliary motor is kept mechanically engaged on the main power transmission chain to participate, even marginally, in driving the rotorcraft rotor or rotors. In such a context and in the context of the 5 constraints specific to category A rotorcraft, the auxiliary engine must be able to operate autonomously in the event of failure of one of the main engines, particularly with regard to the power supply modes. auxiliary engine fuel. In this context, it is desirable to seek a solution to allow implementation of a fuel supply assembly reserved for the auxiliary engine, forming part of the aforementioned research to simplify the fuel supply architecture of the group of motorization while respecting the constraints related to the fuel supply of motors 15 of a category A multi-engine rotorcraft in mechanical engagement with the rotorcraft rotor or rotors. The present invention is part of the search for such a solution, on the basis of the finding that has just been made and which concerns the approach of the present invention.
    [0008] Indeed, in the context of a possible participation of the auxiliary engine in the marginal drive of the rotorcraft rotor or rotors, the usual prejudices in the field of aeronautics must be overcome in order to propose viable and secure modes of power supply. auxiliary engine fuel by avoiding at best to complicate the architecture of the engine group fuel supply system. It emerges in practice that such prejudices hinder the operation of the auxiliary motor to participate marginally in the drive of the rotor or rotors of a category A multi-engine rotorcraft, because of the induced complexification of the engine. fuel supply architecture of the engine group.
    [0009] The difficulty of such an approach is particularly noted in the case where said multi-engine rotorcraft is a twin-engine rotorcraft, that is to say a rotorcraft equipped with a power unit comprising two so-called main combustion engines sized 5 each to be able to individually drive rotorcraft rotors or rotor in flight in case of failure of one of the main engines. Indeed in such a context in case of defection of one of the main engines, a single main engine is available to provide the mechanical power necessary for the rotorcraft to maintain its flight under secure flight conditions, the auxiliary engine being unable to provide only a drive of the rotors of the rotorcraft. The subject of the present invention is such a twin-engine category A rotorcraft of which the engine group comprises two so-called 15 main combustion engines and at least one said auxiliary engine as previously defined. The present invention more specifically aims to provide such a twin-engine class A rotorcraft equipped with a fuel supply system for the combustion engines of the engine group. The organization of said fuel supply installation of the present invention is sought viable under conditions of secure flight of the rotorcraft in the event of defection of one of the main engines, within the framework of a simplification of the feeding modalities. in auxiliary engine fuel. In particular, the constraints on category A rotorcraft must be taken into account, taking into account the involvement of the auxiliary engine in providing marginally and / or temporarily in specific flight phases of the rotorcraft a supplement of mechanical power 30 participating in the rotorcraft rotors.
    [0010] The rotorcraft of the present invention is a twin-engine rotorcraft equipped with a fuel supply system for the combustion engines of a rotorcraft power unit. The motorization unit provides mechanical power operated for driving rotorcraft mechanical power consuming members through a mechanical power transmission chain. Said mechanical power consuming members comprise at least one rotor, of which at least one main rotor 10 providing at least the lift of the rotorcraft. Said mechanical power consuming members also comprise auxiliary members excluding any rotor of the rotorcraft participating indifferently alone or in combination with the lift, the propulsion and / or the guiding of the rotorcraft.
    [0011] Furthermore, the motorization unit comprises two main combustion engines, the individual dimensions of which give the main engines an ability to individually drive the at least one rotor for a predefined period in the event of failure of one of the main engines.
    [0012] The motorization unit further comprises at least one auxiliary combustion engine, the size of which gives the auxiliary motor an ability to drive said auxiliary members and an inability to individually drive said at least one rotor in flight phase of the rotorcraft.
    [0013] Still further, the fuel supply system comprises main fuel supply assemblies distinct from one another. Such separate main fuel supply units are respectively assigned to the main engines for their individual fuel supply.
    [0014] Each main fuel supply assembly comprises a single main fuel tank and a main fluid circuit. The main fluidic circuit comprises at least one main pump and is a fuel delivery circuit from a main feeder equipping the main tank to the main engine to which the main fuel supply assembly concerned is assigned. According to a preferred embodiment, the main pump of a main fluidic circuit considered is in particular typically driven by the main engine fueled by the main fluidic circuit considered. Each main fuel supply assembly further comprises a main fuel transfer circuit comprising in particular at least one main transfer pump.
    [0015] The main transfer circuit is a fuel delivery circuit from the main tank to the main nanny. In this context as conventionally, the main nurse is provided with a spillway restoring too much fuel to the main tank.
    [0016] In addition, the fuel supply installation comprises an auxiliary fuel supply assembly comprising an auxiliary fuel tank and an auxiliary fluid circuit. The auxiliary fluid circuit comprises at least one auxiliary pump and is a fuel path from the auxiliary tank to the auxiliary engine. In this context, it is chosen according to the approach of the present invention to operate the auxiliary motor to participate in driving said at least one rotor, it being understood that the auxiliary motor is unable to provide only a drive of said motor. at least one rotor when the rotorcraft is in flight.
    [0017] As part of this approach, the present invention proposes to supply the auxiliary engine with fuel from both main tanks. In the event of fuel exhaustion of any of the main tanks, the auxiliary engine may be maintained fueled by the other of the main tanks. As a result, the mechanical engagement of the auxiliary motor on the drive train of the rotors of the rotorcraft is viable while meeting secure flight conditions in case of exhaustion of fuel of one of the main tanks and this avoiding an economically unacceptable complexification of the fuel supply installation of the engine group of the rotorcraft. More particularly according to the present invention, said auxiliary tank is composed of both respective main tanks of said main fuel supply assemblies. The main tanks each house a said auxiliary pump, the auxiliary fluid circuit being a fuel supply circuit to the auxiliary engine from the one and the other of the main tanks via an auxiliary conduit in fluid communication. together with both auxiliary pumps respectively housed in the main tanks. The main tanks are pooled to jointly form the de facto auxiliary tank composed of two separate fuel reserves capable of individually allowing a supply of the auxiliary engine fuel through the auxiliary fluid circuit. In the event of fuel exhaustion of any one of the main tanks causing the main engine fueled from the main depleted fuel tank to fail, the auxiliary engine is maintained fueled from the other main tank.
    [0018] The architecture of the auxiliary supply unit is simplified in the absence of a fuel tank specific to the auxiliary engine, while being able to maintain a supply of fuel to the auxiliary engine in case of exhaustion. fuel of one of the main tanks and while meeting the conditions of secure flight of the rotorcraft, or even optimizing such secure flight conditions in case of failure of one of the main engines by providing a mechanical power booster by the auxiliary motor to particularly drive the rotorcraft rotor or rotors. According to a preferred arrangement of the auxiliary duct, the latter comprises two upstream auxiliary channels in fluid communication respectively with one and the other of the auxiliary pumps. The upstream auxiliary channels are jointly in fluid communication with a downstream auxiliary channel itself in fluid communication with the auxiliary engine. Of course, according to such an architecture of the auxiliary duct, the concepts upstream and downstream are relative notions considered in the direction of flow of the fuel through the fluid circuit 20 from the auxiliary pumps to the auxiliary motor. Each of said two upstream auxiliary channels may advantageously be provided with a non-return valve preventing a passage of fluid from one to the other of the main tanks. Such arrangements and arrangement of the auxiliary duct make it possible, from simple structural arrangements, to obtain a strict prohibition of fluid passage from one to the other of the main tanks via the auxiliary fluid circuit. Such provisions are particularly useful in the event of fuel exhaustion of one of the main tanks, to prohibit an air passage 30 from a main fuel-depleted tank to the other main tank and / or to the auxiliary engine.
    [0019] In the alternative and according to the proper organization of the main fuel supply assemblies, the main fluid circuits may each comprise such non-return valves preventing such an air passage from the main tanks to the main engines which assigned to them respectively. According to a simple embodiment, the auxiliary pumps are placed at the bottom of the main tanks which are respectively assigned to them. Such placement of the auxiliary pumps in the bottom of the main tanks excluded, the composition of the auxiliary fuel supply assembly equipment, auxiliary auxiliary fuel supply of the auxiliary engine. However, it can not be ruled out the possibility of providing the auxiliary fuel supply unit for nannies in which the auxiliary pumps are respectively immersed. Such arrangements provide autonomous operation of the auxiliary engine for a predefined period of time in the event of fuel exhaustion of one and / or the other of the main tanks. Such a predefined duration is in particular of a value identical to the predefined duration of autonomy of the main engines in the event of exhaustion in fuel of the main tank which is affected to them. More particularly according to one embodiment, the auxiliary pumps are respectively placed at the bottom of the main nibs respectively equipping the main tanks The respective capacities of the main nannies are each able to provide for a predetermined duration a supply of water. fuel of both the auxiliary engine and the main engine fueled from the main nurse assigned to it.
    [0020] It may however be preferred to limit the individual capacity of the main nannies. In this case, it is proposed to provide the auxiliary fluid circuit auxiliary nurse respectively assigned to the auxiliary pumps.
    [0021] More particularly according to another embodiment, the auxiliary pumps are respectively housed at the bottom of auxiliary nipples equipping respectively one and the other of the main tanks. Auxiliary nannies are each supplied with fuel from the main tank housing them respectively. Auxiliary nannies are potentially supplied with fuel from the main tanks, respectively housing them via respective auxiliary transfer circuits separate from the main transfer circuits. Such auxiliary transfer circuits can conventionally use each at least one auxiliary transfer pump conveying the fuel, for a given auxiliary transfer circuit, between the main tank and the auxiliary nurse housed in this main tank. In the alternative, such an auxiliary transfer pump may advantageously be formed by the auxiliary pump of an auxiliary transfer circuit considered. However, it is proposed in the case where the auxiliary pumps are placed at the bottom of said auxiliary tanks and still in the context of a search for simplification of the architecture of the fuel supply system of the engine group, pooling the main transfer circuit and the auxiliary transfer circuit drawing the fuel in the same main tank to jointly feed the main and auxiliary nurse housed in the same main tank.
    [0022] More particularly in the case where the auxiliary pumps are placed at the bottom of said auxiliary tanks, it is advantageously proposed to supply the auxiliary tanks with fuel from the main tanks housing them respectively via the main transfer circuits with which the auxiliary pumps are in fluid communication. An exemplary embodiment of the present invention will be described in relation to the figures of the attached plates, in which fig.1 and fig.2 are diagrammatic representations of a fuel supply installation equipping a twin-engine rotorcraft according to a preferred embodiment of the invention. In FIG. 1 and FIG. 2, a twin-engine rotorcraft comprises a power unit 1 supplying the rotorcraft with the mechanical power required for its operation. The engine group 1 comprises main engines 2,3 and a combustion combustion auxiliary engine 4 fueled by means of a fuel supply system of the engine group 1. In the context of a twin-engine rotorcraft, the main motors 2, 3 are two in number and are typically each dimensioned to separately provide the mechanical power required for the flight training of at least one rotor 5 of the rotorcraft. Said rotor 5 is in particular a rotor commonly designated by main rotor typically providing at least the lift of the rotorcraft, or even its propulsion and / or its flight guidance in the specific case of a helicopter. Said rotor 5 is still potentially, in addition to the main rotor, at least one ancillary rotor providing yaw control of the rotorcraft or even its propulsion in translation in the case of a helicopter with high forward speeds.
    [0023] The auxiliary motor 4 is dimensioned more weakly than each of the main engines 2,3, with priority being given to the drive of auxiliary members 6 equipping the rotorcraft and mechanical power consumers. Such auxiliary members 5 typically comprise hydraulic power plants, compressors, one or more electric power generating machines and / or a ventilation, heating and / or air conditioning system, or even service equipment, for example.
    [0024] Unlike the main engines 2, 3, the design of the auxiliary motor 4 confers on it a faculty of producing mechanical power incapable of providing alone a drive of the at least one rotor 5 when the rotorcraft is in flight. However, the auxiliary motor 4 is advantageously used to participate in flight in the drive of the at least one rotor 5 by providing, in certain specific flight phases of the rotorcraft, a supplement of mechanical power in addition to the mechanical power essentially provided by the main engines 2,3. In this context, the main motors 2,3 and the auxiliary motor 4 are in mechanical connection with a main transmission box 7. The various members of the rotorcraft 5, 6 consumers of mechanical power are typically driven from the main gearbox 7 of mechanical transmission jointly driven by the main engines 2, 3 and by the auxiliary engine 4 in certain phases of flight for which it is necessary. required to provide the rotorcraft with optimized mechanical power. The fuel supply installation of the engine group 1 includes a plurality of fuel supply assemblies 8, 9, 10 including main fuel supply assemblies 8, 9 and an auxiliary fuel supply assembly.
    [0025] The main fuel supply assemblies 8, 9 are respectively assigned to the individual fuel supply of the main engines 2, 3. The auxiliary fuel supply assembly is assigned to the fuel supply of the auxiliary engine 4. Each main fuel supply assembly 8, 9 typically comprises: -) a main fuel tank 11, 12 potentially composed of a plurality of fuel stores placed in fluid communication with each other, -) a main nanny 13,14 housed in the main tank 11,12 and equipped with a fuel transfer circuit 15,16 from the main tank 11,12 to the main feeder 13,14; -) a main fluid circuit 27,28 comprising a main pump 29,30 drawing the fuel from the main feeder 13,14 to individually fuel a main engine 2,3. In the exemplary embodiment illustrated, the main pump 29,30 is typically driven by the main engine 2.3 fueled by the main pump 29,30.
    [0026] In the exemplary embodiment illustrated, said transfer circuits typically each comprise at least one transfer pump 17, 18; 19,20 and a transfer line 21,22 provided with at least one ejector 23,24 immersed in the main tanks 11,12. Transfer pumps 17,18; 19.20 are preferably two and are potentially used to form feed pumps. Conventionally, such booster pumps are used to supply fuel to the main engines 2,3 to start their startup, until an adequate drive of the main pumps 29,30.
    [0027] The main nannies 13, 14 are each provided with a weir 25,26 for discharging the overflow of fuel out of the main nannies 13,14 to the main tanks 11,12. An intercommunication circuit 31 is preferably arranged between the main nannies 13, 14 of the one and the other of the main fuel supply units 8, 9 to balance the quantities of fuel respectively contained in the main tanks. 11.12. Such an intercommunication circuit 31 is typically implemented selectively by activation of a hydraulic control member 32 of the fuel exchange between the main tanks 11, 12 or even more specifically between the main nannies 13, 14 such that illustrated in the figures. Such a hydraulic regulating device 32 can be controlled according to needs, for example consisting of an intercommunication valve or an intercommunication pump for example. In this context, there is the problem of a possible fuel depletion of one of the main tanks 11,12, or even one of the main nurses 13,14. Such exhaustion is potentially induced due to a fuel leak out of a main tank 11,12 become defective. Conventionally in case of failure and / or loss of the fuel supply of one of the main engines 2,3, the other main motor 2,3 then provides only the drive of the at least one rotor 5 for a period of time 25 predefined determining the individual capacity of the main nanners 13,14. However, since the auxiliary motor 4 is mechanically connected to the at least one rotor 5, the fuel supply of the auxiliary engine 4 must be maintained in the event of failure of any one of the main engines 2,3 and / or fuel exhaustion of any of the main tanks 11,12.
    [0028] In this context, it is proposed a solution allowing such maintenance of the fuel supply of the auxiliary engine 4, without greatly complicating the architecture of the fuel supply system of the engine group 1 ni affect the flight safety of the rotorcraft in the event of defection of one of the main engines 2.3. For this purpose on the preferred embodiment illustrated in the figures due to the optimization of its structural simplicity, it is proposed to supply fuel to the auxiliary motor 4 by means of an auxiliary fluid circuit 10 conveying the fuel from each of the main nannies 13,14 to the auxiliary motor 4. The auxiliary fluid circuit 10 comprises two auxiliary pumps 33,34 respectively immersed in the main nannies 13,14. The auxiliary pumps 33, 34 are jointly placed in fluid communication with an auxiliary conduit 35 conveying the fuel from one of the auxiliary pumps 33, 34 to the auxiliary engine 4. In case of fuel exhaustion at the In the interior of any one of the main tanks 11, 12, the fuel supply of the auxiliary engine 4 is maintained from the other 20 of the main tanks 11, 12. The auxiliary duct 35 comprises in particular upstream channels 36, 37 respectively assigned to the removal of fuel from the one and the other of the main tanks 11, 12. The upstream channels 36, 37 are each equipped with a 38.39 non-return valve 25 preventing an air passage from any main fuel tank 11, exhausted to the auxiliary engine 4 and / or to the other reservoir. principal 11.12. The upstream channels 36, 37 are jointly placed in fluid communication with a downstream channel 40 of the auxiliary duct 35, said downstream channel 40 conveying the fuel 30 from the upstream channels 36, 37 to the auxiliary motor 4.
    权利要求:
    Claims (8)
    [0001]
    REVENDICATIONS1. Twin-engined rotorcraft equipped with a fuel supply system for combustion engines (2,3,4) of a rotorcraft power unit (1), said engine group (1) providing mechanical power exploited for the driving rotorcraft mechanical power consuming members (5, 6) through a mechanical power transmission chain, said mechanical power consuming members (5, 6) comprising: -) at least one rotor ( 5) including at least one main rotor providing at least the lift of the rotorcraft, and -) auxiliary members (6), said auxiliary members (6) excluding any rotor (5) of the rotorcraft participating in the lift, the propulsion and / or guiding the rotorcraft, the engine group (1) comprising: -) two main combustion engines (2,3) whose individual dimensions give them an ability to drive said at least one rotor (5) individually during 20 u no predefined duration in the event of failure of one of the main engines (2, 3), and -) at least one auxiliary combustion engine (4) whose dimensioning gives it an ability to drive said auxiliary members (6) and a inability to individually drive said at least one rotor (5) in flight phase of the rotorcraft, the fuel supply system comprising main fuel supply assemblies (8,9) separate from one another by 3021629; being respectively assigned to the main engines (2,3) for their individual fuel supply, each at least one main fuel supply unit (8,9) comprising: -) a single main fuel tank (11,12) and a main fluidic circuit (27,28) comprising at least one main pump (29,30), the main fluid circuit (27,28) being a fuel delivery circuit from a main feeder (13,14) fitted to the tank principal (11 , 12) to the main engine (2,3) to which is assigned the main fuel supply assembly (8,9) considered, -) a main fuel transfer circuit (21,22) comprising at least one pump main transfer system (17,18; 19,20), the main transfer circuit (21,22) being a fuel delivery circuit from the main reservoir (11,12) to the main nanny (13,14) , the main nanny being provided with a weir (25,26) returning an excess of fuel to the main tank (11,12), the fuel supply installation comprising an auxiliary fuel supply assembly comprising a auxiliary fuel tank and auxiliary fluid circuit (10) comprising at least one auxiliary pump (33,34), the auxiliary fluid circuit (10) being a fuel supply circuit from the auxiliary tank to the auxiliary engine (4). ), characterized in that the auxiliary motor (4) is With respect to driving said at least one rotor (5), said auxiliary reservoir is composed of respective main reservoirs (11, 12) of said main fuel supply assemblies (8, 9). , The main tanks (11,12) each housing a said auxiliary pump (33,34), the auxiliary fluid circuit (10) being a fuel supply circuit to the auxiliary engine (4) since one and the other of the main tanks (11,12) via an auxiliary duct (35) in fluid communication with both auxiliary pumps (33,34) respectively housed in the main tanks (11,12).
    [0002]
    2. twin-engined rotorcraft according to claim 1, characterized in that the auxiliary duct (35) comprises two upstream auxiliary channels (36,37) in fluid communication respectively with one and the other of the auxiliary pumps (33,34), the upstream auxiliary channels (36,37) being jointly in fluid communication with a downstream auxiliary channel (40) itself in fluid communication with the auxiliary motor (4).
    [0003]
    3. A twin-engined rotorcraft according to claim 2, characterized in that each of said two upstream auxiliary channels (36, 37) is provided with a non-return valve (38, 39) preventing a passage of fluid from one to the other. other main tanks (11,12).
    [0004]
    4. Twin-engined rotorcraft according to any one of claims 1 to 3, characterized in that the auxiliary pumps (33,34) are placed at the bottom of the main tanks (11,12) which are assigned to them respectively excluding the composition auxiliary fuel supply equipment, auxiliary auxiliary engine fuel supply (4).
    [0005]
    5. twin-engined rotorcraft according to any one of claims 1 to 3, characterized in that the auxiliary pumps (33,34) are respectively placed at the bottom of the main nannies (13,14) respectively equipping the one and the other main tanks (11,12), the respective capacities of the main nannies (13,14) 5 being each able to provide for a predetermined duration a supply of fuel both the auxiliary engine (4) and the main engine (2 , 3) supplied with fuel from the main nanny (13,14) assigned to it.
    [0006]
    6. twin-engined rotorcraft according to any one of claims 1 to 3, characterized in that the auxiliary pumps (33,34) are respectively housed at the bottom of auxiliary nipples equipping respectively one and the other of the main tanks (11). , 12), the auxiliary nurses each being supplied with fuel 15 from the main tank (11,12) housing respectively.
    [0007]
    7. A twin-engined rotorcraft according to claim 6, characterized in that the auxiliary feeders are supplied with fuel from the main tanks (11,12) respectively housing them via respective auxiliary transfer circuits 20 distinct from the main transfer circuits.
    [0008]
    8. twin-engined rotorcraft according to claim 6, characterized in that the auxiliary tanks are supplied with fuel from the main tanks (11,12) housing them respectively via the main transfer circuits (21,22) with which the Auxiliary pumps (33,34) are in fluid communication.
    类似技术:
    公开号 | 公开日 | 专利标题
    EP2949578B1|2016-07-27|Twin-engined rotorcraft provided with a system for supplying fuel to a power unit comprising an auxiliary power unit |
    CN108027039B|2019-12-24|Oil supply device for epicyclic gear reducer
    US8870699B2|2014-10-28|Lubrication oil system for a reduction gearbox
    EP2524869B1|2016-02-10|Standalone system for electric power generation and conditioning for an aircraft, related aircraft and method.
    EP3075966B1|2019-05-08|Gas turbine engine having an air turbine starter system including an gearbox-integrated clutch module
    CA2968481A1|2016-06-02|Cooling device for a turbomachine supplied by a discharge circuit
    JP2007008461A|2007-01-18|Helicopter with an auxiliary lubricating circuit
    FR2491141A1|1982-04-02|OIL SUPPLY DEVICE FOR A GAS TURBINE AIRPLANE ENGINE
    RU2468227C1|2012-11-27|Oil system of aircraft gas turbine engine
    EP2567896B1|2014-06-04|Fuel supply architecture of a motor group of a rotary wing equipping a rotorcraft
    EP2657134B1|2016-08-31|A fuel supply of a motor of a rotorcraft, comprising means for initiating a suction pump for fuel from a distributor
    US11073041B2|2021-07-27|Jet engine
    CA2193167A1|1997-06-21|System for engine restart following complete inflight engine shutdown
    FR3019861A1|2015-10-16|BALANCING VALVE FOR THE FLUID SUPPLY OF THE CYLINDER BODIES OF A SERVO CONTROL MANUFACTURING THE BLADES OF A ROTOR OF GIRAVION
    EP3447267B1|2019-12-04|Supplemental lubrication pressurized by component or reservoir rotation
    WO2011107718A1|2011-09-09|Rotary- or fixed-wing aircraft provided with a distributed electric engine unit
    EP2524871B1|2017-08-23|Autonomous electric power generation system for aircraft and related control method
    FR3075875B1|2019-11-15|OIL CIRCUIT FOR AUXILIARY OIL RING TURBOMACHINE
    FR3005486A1|2014-11-14|LUBRICATION IN A TURBOMACHINE
    US20210131321A1|2021-05-06|Aircraft engine lubrication system and method
    US20140271151A1|2014-09-18|Oil transfer system on rotating shaft
    EP3087264B1|2018-09-26|Turbomachine air starter comprising first and second lubrication compartments
    FR3055936B1|2019-06-21|LUBRICATION DEVICE WITH MULTIPLE LUBRICATING LIQUID RECOVERY TANKS AND OPTIMIZED AND RELIABLE DELIVERY TO A MAIN TANK
    FR3024498B1|2019-07-12|TURBOMACHINE ASSEMBLY COMPRISING TWO BODIES AND INTERNAL GUIDING MEANS OF FLOW FLUID TO A FEEDING ELEMENT
    EP3857029A1|2021-08-04|Auxiliary oil tank for an aircraft turbine engine
    同族专利:
    公开号 | 公开日
    RU2600180C1|2016-10-20|
    US20160272338A1|2016-09-22|
    EP2949578A1|2015-12-02|
    EP2949578B1|2016-07-27|
    FR3021629B1|2016-06-10|
    PL2949578T3|2017-01-31|
    US9580184B2|2017-02-28|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP2524871A1|2011-05-18|2012-11-21|Dassault Aviation|Fuel storage device in an aircraft, related system and control method.|
    EP2567896A1|2011-09-09|2013-03-13|Eurocopter|Fuel supply architecture of a motor group of a rotary wing equipping a rotorcraft|
    CA2831706A1|2012-11-26|2014-05-26|Eurocopter|Method and rotary wing aircraft equipped with three engines|
    SU1108693A1|1983-03-31|1996-04-27|А.П. Белов|Aircraft fuel system|
    US5321945A|1990-04-02|1994-06-21|Honeywell Inc.|Apparatus for controlling fuel transfers in a distributed fuel tank system|
    EP0670264A1|1994-03-02|1995-09-06|Daimler-Benz Aerospace Aktiengesellschaft|Fuel delivery system|
    RU4733U1|1996-03-29|1997-08-16|Акционерное общество открытого типа "Московский вертолетный завод им.М.Л.Миля"|FUEL HELICOPTER SYSTEM|
    EP3412577B1|2008-05-13|2020-03-18|Sikorsky Aircraft Corporation|Fuel system|
    FR3021629B1|2014-05-28|2016-06-10|Airbus Helicopters|BRAKE MACHINE EQUIPPED WITH A FUEL SUPPLY INSTALLATION OF A POWER UNIT COMPRISING AN AUXILIARY POWER UNIT |FR3021629B1|2014-05-28|2016-06-10|Airbus Helicopters|BRAKE MACHINE EQUIPPED WITH A FUEL SUPPLY INSTALLATION OF A POWER UNIT COMPRISING AN AUXILIARY POWER UNIT |
    US11174015B2|2019-02-05|2021-11-16|Textron Innovations Inc.|Multimode clutch assemblies having engagement status sensors|
    US11174014B2|2019-02-05|2021-11-16|Textron Innovations Inc.|Failsafe multimode clutch assemblies for rotorcraft|
    US10793284B2|2019-02-05|2020-10-06|Bell Textron Inc.|Multimode clutch assemblies for rotorcraft|
    US11174013B2|2019-02-05|2021-11-16|Textron Innovations Inc.|Failsafe multimode clutch assemblies for rotorcraft|
    US10788088B2|2019-02-05|2020-09-29|Bell Textron Inc.|Multimode powertrains for rotorcraft|
    US11104430B2|2019-09-27|2021-08-31|Textron Innovations Inc.|Multimode powertrains for multi engine rotorcraft|
    法律状态:
    2015-04-22| PLFP| Fee payment|Year of fee payment: 2 |
    2015-12-04| PLSC| Search report ready|Effective date: 20151204 |
    2016-05-20| PLFP| Fee payment|Year of fee payment: 3 |
    2017-05-23| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1401226A|FR3021629B1|2014-05-28|2014-05-28|BRAKE MACHINE EQUIPPED WITH A FUEL SUPPLY INSTALLATION OF A POWER UNIT COMPRISING AN AUXILIARY POWER UNIT |FR1401226A| FR3021629B1|2014-05-28|2014-05-28|BRAKE MACHINE EQUIPPED WITH A FUEL SUPPLY INSTALLATION OF A POWER UNIT COMPRISING AN AUXILIARY POWER UNIT |
    EP15001347.2A| EP2949578B1|2014-05-28|2015-05-06|Twin-engined rotorcraft provided with a system for supplying fuel to a power unit comprising an auxiliary power unit |
    PL15001347T| PL2949578T3|2014-05-28|2015-05-06|Twin-engined rotorcraft provided with a system for supplying fuel to a power unit comprising an auxiliary power unit |
    RU2015119679/11A| RU2600180C1|2014-05-28|2015-05-25|Twin-engine rotary-winged aircraft equipped with motor group fuel supply plant containing auxiliary power plant|
    US14/722,365| US9580184B2|2014-05-28|2015-05-27|Twin-engined rotorcraft having a fuel supply installation for a power plant auxiliary power unit |
    [返回顶部]