• 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 turbine engine comprising a gas generator (5) adapted to be rotated and a free turbine (6) driven in rotation by the gases of said gas generator, characterized in that it comprises a device (40). controlled mechanical coupling of said gas generator (5) and said free turbine (6) adapted to mechanically and commandably link said gas generator (5) and said free turbine (6) as soon as the rotational speed of said generator (5) ) gas reaches a predetermined threshold speed.
    公开号:FR3019223A1
    申请号:FR1452654
    申请日:2014-03-27
    公开日:2015-10-02
    发明作者:Patrick Marconi；Romain Thiriet；Camel Serghine
    申请人:Turbomeca SA；
    IPC主号:
    专利说明:

    [0001] TURBOMOTEUR COMPRISING A CONTROLLED MECHANICAL COUPLING DEVICE, HELICOPTER PROVIDED WITH SUCH A TURBOMOTOR AND METHOD FOR OPTIMIZING THE SUPER-SLOWING SYSTEM WITH NULL POWER OF SUCH A HELICOPTER 1. Technical Field of the Invention The invention relates to a turbine engine for to equip a multi-engine helicopter, especially twin-engine. The invention also relates to a method for optimizing the zero-power super-idling speed of such a multi-engine helicopter, in particular a twin-engine helicopter. 2. Technological background A helicopter is usually equipped with at least two turboshaft engines operating at speeds that depend on the flight conditions of the helicopter. In the following text, a helicopter is said to be in a cruising flight situation when operating under normal conditions, known as AEO (All Engines Operative), during all phases of flight, except transient phases of takeoff, landing or hovering. 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 revving in which one of the turboshaft engines failed, designated by the acronym OEI (One Engine Inoperative). It is known that when the helicopter is in cruise flight, the turboshaft engines operate at low levels of power, lower than their maximum continuous power (hereinafter, PMC). In certain configurations, the power provided by the turbine engines, during a cruising flight, may be less than 50% of the maximum takeoff power (hereinafter, PMD). 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 power supplied by this turbine engine, which is in the order of 30% greater than the Cs of the PMD, and therefore an overconsumption of fuel in cruising flight. Finally, during the waiting phases on the ground, the pilots generally prefer to put the various engines in idle in order to be sure of being able to restart them. The turbine engines then continue to consume fuel although they provide no power. 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, very restrictive, especially when the helicopter has a mass close to its maximum take-off weight, are encountered only in certain cases of use of certain helicopters. As a result, some turboshaft engines, although sized to provide such power, will never fly under such conditions. These oversized turboshaft engines are penalizing in terms of weight and fuel consumption. In order to reduce this consumption in all the flight cases described above (cruise flight, OEI regime, taxiing, hovering or ground waiting), it is possible to place one of the turboshaft engines in the so-called standby mode. The active engine (s) then operate at higher power levels to provide all the power required and therefore at more favorable Cs levels. A helicopter turbine engine comprises in a known manner a gas generator and a free turbine powered by the gas generator to provide power. The gas generator is conventionally composed of air compressors supplying a fuel combustion chamber in the compressed air which deliver hot gases to gas partial expansion turbines which rotate the compressors via drive shafts. The gases then drive the free power transmission turbine. The free turbine transmits power to the rotor of the helicopter through a gearbox. 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 flight regime, said continuous, and at least one turbine engine in a particular watch mode from which it can leave 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 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 urgent when a power failure or power deficit of the active engine occurs or the flight conditions suddenly become difficult. Such emergency standby output is performed for a period of less than 10s. In particular, the applicants proposed the following two watch modes: a standby mode, called super slow idle, in which the combustion chamber is lit and the shaft of the gas generator rotates at a speed of between 20 and 60% of the nominal speed, a standby mode, said super-idle assisted, in which the combustion chamber is lit and the shaft of the gas generator rotates, mechanically assisted, at a speed between 20 and 60% of the nominal speed. The usual super-idle regime is penalized by operating temperatures which are becoming higher and higher as one seeks to reach a lower and lower idle, which nevertheless has the advantage of minimizing its consumption. fuel in this scheme. The assisted super-idle system overcomes this operating temperature problem while further reducing fuel consumption. That being so, it imposes the use of a pneumatic or hydraulic electric drive machine and a corresponding coupling. Also, there is now the technical problem of obtaining a super-idle regime which is no longer mechanically assisted and less limited by the temperatures of the turbine engine. There is therefore the technical problem of providing a turbine engine to provide such an improved super-idle regime. 3. OBJECTIVES OF THE INVENTION The object of the invention is to provide a turbine engine which can have a super-idle speed, in which the combustion chamber is lit and the shaft of the gas generator rotates at a speed of between 20 and 60%. the nominal speed, which is less penalized by the operating temperatures of the turbine engine, nor mechanically assisted by an external drive device. The invention therefore aims to provide a turbine engine that can present a new super idle regime. The invention also aims to provide a twin-engine helicopter comprising at least one turbine engine according to the invention. The invention also aims to provide a method for optimizing the super-idle speed at zero power of a twin-engine helicopter according to the invention comprising at least one turbine engine according to the invention. 4. DESCRIPTION OF THE INVENTION To this end, the invention relates to a turbine engine comprising a gas generator adapted to be rotated and a free turbine driven in rotation by the gases of said gas generator.
    [0002] A turbine engine according to the invention is characterized in that it comprises a mechanical coupling device controlled said gas generator and said free turbine adapted to mechanically link and on command said gas generator and said free turbine as soon as the speed of rotation said gas generator reaches a predetermined threshold speed.
    [0003] A turbine engine according to the invention thus allows the gas generator and the free turbine to be mechanically and on order. The link control of the gas generator and the free turbine is a function of the rotational speed of the gas generator. A turbine engine according to the invention therefore allows a mechanical assistance to the rotation of the gas generator which may not use an external drive machine. The power is directly derived from the free turbine turbine turbine and transmitted through the coupling device. Advantageously and according to the invention, the controlled mechanical coupling device is adapted to mechanically link and order said gas generator and said free turbine as soon as said rotational speed of said gas generator is lower than said predetermined threshold speed and to separate upon command of said gas generator and said free turbine as soon as said rotational speed of said gas generator is greater than said predetermined threshold speed. Thus, according to this aspect of the invention, the controlled coupling device makes it possible to force the gas generator to be driven by the free turbine when the gas generator rotates at a speed lower than a predetermined threshold speed. In other words, a turbine engine according to the invention equipped with a controlled mechanical coupling device of the gas generator and the free turbine makes it possible to switch, on command, the turbine engine of a configuration (or mode) called turbines free, in which the gas generator and the free turbine are mechanically independent, to a configuration (or mode) called linked turbines, wherein the gas generator and the free turbine are mechanically linked. The predetermined threshold speed is advantageously chosen so that the mechanical connection between the gas generator and the free turbine is only possible when the turbine engine is in super-idle mode, that is to say when the free turbine no longer produces torque and rotates freely at a speed lower than that of the input of the gearbox of the aircraft to which it is connected. By forcing the free turbine to rotate slower than its equilibrium speed at zero torque, it will then provide a motor torque that will allow the gas generator to drive the compressor, which then corresponds to a turbine configuration linked. A turbine engine according to the invention can therefore be placed in a super idle regime during which the free turbine drives the gas generator, which makes it possible to reduce the temperatures of the hot parts of the turbine engine and to reduce the fuel consumption.
    [0004] Advantageously and according to the invention, the threshold speed is a function of a nominal speed of said gas generator. According to this aspect of the invention, the threshold speed is directly dependent on the nominal speed of the gas generator.
    [0005] Advantageously and according to this variant, the threshold speed is chosen in the range [20% .N1, 60% .N1], where N1 is said nominal speed of said gas generator. In other words, a turbine engine according to this variant switches from a free turbine mode to a tied turbine mode as soon as the speed of rotation of the gas generator becomes lower than a threshold value corresponding to an idling speed (defined here as 20 % to 60% of the nominal speed of the gas generator). Advantageously and according to the invention, said controlled mechanical coupling device comprises: means for reading an information representative of said rotational speed of said gas generator, reversible mechanical coupling means between a shaft mechanically connected to said gas generator and a shaft mechanically connected to said free turbine, means for controlling said coupling means according to said information representative of said rotational speed of said gas generator and said threshold speed. Advantageously and alternatively, the coupling device further comprises means for authorizing said coupling means by a command from an engine computer having previously requested a standby of the engine. According to this aspect of the invention, reading means make it possible to acquire information representative of the speed of rotation of the gas generator. Control means make it possible to interpret this information and to compare it with the threshold speed. If the speed of rotation is determined to be lower than the threshold speed and the engine computer has previously requested a standby of the engine, a command is sent to coupling means which ensure the mechanical coupling between the generator of gas and the free turbine, thus tilting the turbine engine in a linked turbine mode. This mechanical coupling is achieved by means of intermediate shafts mechanically connected respectively to the gas generator and the free turbine. Throughout the text that follows, the term "tree" means a means adapted to be rotated and to transmit a torque. It can therefore be a shaft extending longitudinally, but also a single gear 10 gear. These coupling means can be of all types. According to an advantageous variant, these coupling means are chosen from the group comprising at least one friction clutch, a clutch and a clutch equipped with a synchronizer. A clutch equipped with a synchronizer allows, prior to interconnection, to synchronize the respective speeds of the shafts, which allows better management of the speed differential than in the absence of a synchronizer. Advantageously, these coupling means are configured to allow temporary sliding between the shaft mechanically connected to said gas generator and the shaft mechanically connected to said free turbine during a preliminary coupling phase. Advantageously, a turbine engine according to the invention further comprises a spontaneous mechanical coupling device of said gas generator and said free turbine adapted to mechanically and spontaneously bind said gas generator and said free turbine as soon as the ratio of the rotational speed said gas generator by the speed of rotation of said free turbine reaches a predetermined threshold value. This threshold value of the ratio of the rotational speed of said gas generator by the rotational speed of said free turbine is substantially lower than that which is obtained during the activation of the controlled coupling device so that when the free turbine rotates at its nominal speed being coupled to the rotor the gas generator does not rotate more than 10 to 20% faster than its rotation speed at idle vol. A turbine engine according to another embodiment comprises, in addition to a mechanical coupling device controlled on reaching a speed threshold of the gas generator, a spontaneous mechanical coupling device. The mechanical connection of the gas generator and the free turbine through the spontaneous mechanical coupling device is not a function of the rotation speed of the gas generator, as for the controlled mechanical coupling device, but of the ratio of the speed of rotation of the gas generator by the speed of rotation of the free turbine.
    [0006] A turbine engine according to this variant of the invention therefore makes it possible to force the drive of the gas generator by the free turbine when predetermined conditions are reached. In other words, a turbine engine according to the invention equipped with a device for spontaneous mechanical coupling of the gas generator and the free turbine makes it possible to switch automatically and spontaneously, without assistance device and / or external control, the turbine engine of the configuration called free turbines in the so-called turbine configuration. Thus, this changeover from a free mode to a linked mode is not only a function of the speed of rotation of the gas generator, but also of the ratio of the speed of rotation of the gas generator to the speed of rotation of the free turbine. .
    [0007] Advantageously and according to this variant, said spontaneous mechanical coupling device is adapted to mechanically and spontaneously bind said gas generator and said free turbine as soon as said gear ratio is lower than said predetermined threshold value and to spontaneously separate said gas generator and said free turbine as soon as said ratio is greater than said predetermined threshold value. Advantageously, the operation of turbines connected to the vicinity of the idle improves the transient performance, in particular in the event of a fall of the rotor turns during a setting of fast steps. In fact, the gas generator then rotates at a speed greater than its necessary speed at zero power in free turbine mode. The engine thus very rapidly produces a significant power on the free turbine, corresponding to the value that the free turbine engine would have at this speed, increased by the additional power due to the fact that the acceleration limit is reached quickly before same as the gas turbine began to accelerate.
    [0008] Advantageously and according to this variant, said spontaneous mechanical coupling device comprises at least one free wheel connecting a first shaft having with said gas generator a reduction ratio K1 and a second shaft having with the free turbine a reduction ratio K2, said wheel wherein said free turbine spontaneously drives said gas generator, through said shafts and said freewheel, as soon as said gear ratio is lower than the ratio K2 / K1. Advantageously, a turbine engine according to this variant comprises a generator-starter integral with an intermediate shaft and said spontaneous mechanical coupling device comprises two freewheels respectively connecting said intermediate shaft with said first shaft having with said gas generator a reduction ratio K1 and said second shaft having with the free turbine a reduction ratio K2, said wheels being arranged such that said free turbine spontaneously drives said gas generator, through said shafts and said free wheels, as soon as said gear ratio is lower to the ratio K2 / K 1. In addition, said generator-starter secured to the intermediate shaft is thus driven by the free turbine when said generator-starter operates as a generator and said generator-starter drives the gas generator when said generator-starter operates as a starter.
    [0009] The invention also relates to a twin-engine helicopter characterized in that it comprises at least one turbine engine according to the invention. The invention also relates to a method for optimizing the zero-power super-idle speed of a twin-engine helicopter comprising at least one turbine engine comprising a gas generator adapted to be rotated and a free turbine driven in rotation by the gases. said gas generator, characterized in that it comprises a controlled mechanical coupling step of said gas generator and said free turbine as soon as the rotational speed of said gas generator reaches a predetermined threshold speed. Advantageously, a method according to the invention further comprises a step of spontaneous mechanical coupling of said gas generator and the free turbine as soon as the ratio of the speed of rotation of said gas generator by the speed of rotation of said free turbine reaches a maximum of predetermined threshold value. The invention also relates to a turbine engine, a helicopter and a method of optimization of the super-idle speed at zero power, characterized in combination by all or some of the characteristics mentioned above or 10 below. 5. BRIEF DESCRIPTION OF THE DRAWINGS Other objects, features and advantages of the invention will appear on reading the following description given solely by way of nonlimiting example and which refers to the appended figures in which: FIG. 1 is a diagrammatic view of A turbine engine according to a first embodiment of the invention, FIG. 2 is a schematic view of a turbine engine according to a second embodiment of the invention, FIG. 3 is a schematic view of a turbine engine according to a third embodiment of the invention. DETAILED DESCRIPTION OF AN EMBODIMENT OF THE INVENTION A turbine engine according to the invention comprises, as represented in the figures, a gas generator 5 and a free turbine 6 supplied by the gas generator 5. A gas generator 5 comprises in known manner at least one air compressor 7 supplying a combustion chamber 8 with a fuel in the compressed air which delivers hot gases to at least one turbine 9 for partial expansion of the gases which rotates the compressor 7 via a drive shaft. The gases further drive the free power transmission turbine 6. This free turbine 6 comprises a power transmission shaft 11 connected to a power transmission box, not shown in the figures, by means of a free wheel 12. This free wheel 12 prevents a blocking Mechanical turbine engine causes a mechanical blocking of the power transmission box and by extension of the rotor of the helicopter on which the turbine engine is mounted.
    [0010] A turbine engine according to the invention furthermore comprises a device 40 for mechanical coupling controlled by the gas generator 5 and the free turbine 6 adapted to mechanically and commandably link the gas generator 5 and the free turbine 6 as soon as the NGG speed of The rotation of the gas generator is less than a threshold speed. Throughout the text, the rotational speed NGG of the gas generator designates the rotational speed of the drive shaft of the gas generator. In the same way, the speed NTL of rotation of the free turbine designates the speed of rotation of the drive shaft 11 of the free turbine. This threshold speed is for example set at 30% .N1, where N1 is the nominal rotation speed of the gas generator. In other words, the controlled mechanical coupling device 40 is adapted to ensure the coupling between the gas generator and the free turbine when the turbine engine is in an idle mode. As soon as the rotation speed NGG of the gas generator is greater than the threshold speed, the gas generator and the free turbine are mechanically independent of each other. According to the embodiment of the figures, the control device 40 comprises a shaft 42 mechanically connected to the gas generator 5 and a shaft 43 mechanically connected to the free turbine. The control device 40 further comprises means for reading information representative of said NGG rotation speed of the gas generator 5. These reading means include, for example, a speed sensor mounted on the shaft of the gas generator so that the information provided is directly a measure of the speed of the gas generator. 11 further comprises means 41 for reversibly coupling the two shafts 42, 43 and control means of these coupling means 41. According to one embodiment, the coupling means 41 comprise a friction clutch, such as a centrifugal clutch, a cone clutch, a single-disk clutch or a multi-disk clutch. Such coupling means have the advantage of allowing sliding between the shafts in a first coupling phase. According to one embodiment, the control means of this friction clutch are hydraulic or electrical control means of the actuator type. In addition, the control means comprise a module adapted to receive the measurement of the speed of the gas generator and compare it with the threshold speed. Such a module is for example a software element, a subset of a software program, or a hardware element, or a combination of a hardware element and a software subprogram.
    [0011] According to another embodiment, the coupling means 41 comprise a clutch, possibly equipped with a synchronizer which allows better management of the speed differential, making it possible to directly couple the shafts 42 and 43. FIGS. two embodiments in which the turbine engine further comprises a device 20 for spontaneous mechanical coupling between the gas generator 5 and the free turbine 6. This spontaneous mechanical coupling device 20 is adapted to mechanically and spontaneously link the gas generator 5 and the free turbine 6 as soon as the ratio of the rotational speed of the shaft 10 of the gas generator 5 to the speed of rotation of the gas generator 5. shaft 11 of the free turbine 6 is less than a predetermined threshold value and to spontaneously separate the gas generator 5 and the free turbine 6 as soon as the ratio is greater than this predetermined threshold value. According to a first embodiment and as represented in FIG. 3, this spontaneous mechanical coupling device 20 comprises a shaft 22 mechanically connected to the shaft 10 of the gas generator 5. These shafts 22 and 10 have a reduction ratio K1 between them. The spontaneous mechanical coupling device 20 further comprises a shaft 23 mechanically connected to the shaft 11 of the free turbine 6. These trees 23 and 11 have between them a reduction ratio K2.
    [0012] The spontaneous mechanical coupling device 20 further comprises a free wheel 21 arranged between the shafts 22 and 23.
    [0013] Therefore, the rotational speed of the shaft 22 is equal to K1.NGG, where NGG is the rotational speed of the shaft 10 of the gas generator 5. The rotational speed of the shaft 23 is equal to K2.NTL, where NTL is the speed of rotation of the shaft 11 of the free turbine 6.
    [0014] The freewheel 21 is oriented so that the shaft 23 can drive the shaft 22 via this free wheel 21. If the speed of rotation of the shaft 23 is less than the rotation speed of the tree 22, the two trees are independent. Otherwise, the two trees are linked. In other words, the trees are independent if the following equation is respected: K2.NTL <K 1 .NGG. The trees are therefore independent if the ratio NGG / NTL> K2 / K1. If the speed ratio is less than or equal to K2 / K1, then a driving torque is transmitted from the free turbine 6 to the gas generator 5. In other words, the spontaneous mechanical coupling device 20 described in connection with FIG. 3 makes it possible to mechanically and spontaneously bind the gas generator 5 and the free turbine 6 as soon as the NGG / NTL ratio is less than or equal to K2 / K1. which therefore acts as a predetermined threshold value. The device also makes it possible to spontaneously separate the gas generator 5 and the free turbine 6 as soon as the ratio NGG / NTL becomes greater than K2 / K1. If the NGG rotation speed of the gas generator 5 is lower than the threshold speed, the controlled mechanical coupling device 40 mechanically couples the gas generator 5 and the free turbine 6 through the means 41 of the gas generator 5. coupling. When this coupling is effective, the ratio NGG / NTL becomes significantly higher than K2 / K1. The spontaneous mechanical coupling device 20 is therefore not active and the free wheel 21 slides. The two control devices 20, 40 are therefore perfectly compatible with each other. According to a second embodiment and as shown in FIG. 2, the turbine engine further comprises a generator-starter 30. In this case, the coupling device further comprises shafts 22 and 23 described in connection with FIG. an intermediate shaft integral with the generator-starter 30.
    [0015] The coupling device 20 further comprises a first freewheel 26 which connects the intermediate shaft with the shaft 23. It further comprises a second freewheel 24 which connects the intermediate shaft with the shaft 22. same way as for the embodiment of Figure 3, the rotation speed of the shaft 22 is equal to K1 .NGG and the rotation speed of the shaft 23 is equal to K2.NTL. The wheels 26, 24 are oriented such that the intermediate shaft integral with the generator-starter 30 is adapted to drive the shaft 22, and the shaft 23 is adapted to drive the intermediate shaft integral with the generator. The two freewheels 26, 24 drive simultaneously if the ratio NGG / NTL is equal to K2 / K1. If the ratio NGG / NTL is less than or equal to K2 / K1, then the shafts 10, 11 are mechanically linked and a driving torque is transmitted from the free turbine 6 to the gas generator 5. If the ratio NGG / NTL is greater than K2 / K1, then the trees are mechanically independent. The generator-starter 30 is either driven by the free turbine (case of a generating function) or drives the gas turbine (case of a starter function).
    [0016] In other words, the spontaneous mechanical coupling device 20 described in connection with FIG. 2 also makes it possible to mechanically and spontaneously bind the gas generator 5 and the free turbine 6 as soon as the ratio NGG / NTL is less than or equal to K2 / K1. The device also makes it possible to spontaneously separate the gas generator 5 and the free turbine 6 as soon as the ratio NGG / NTL becomes greater than K2 / K1. In addition, in this embodiment, the generator and / or starter function is possible. If the rotation speed NGG of the gas generator 5 is lower than the threshold speed, the controlled mechanical coupling device 40 ensures the mechanical coupling of the gas generator 5 and the free turbine 6 via the coupling means 41. . When this coupling is effective, the ratio NGG / NTL becomes significantly higher than K2 / K1. The device 20 spontaneous mechanical coupling is not active and at least one of the two freewheels 21, 26 slides. The two control devices 20, 40 are therefore perfectly compatible with each other. The invention also relates to a method for optimizing the zero-power super-idle speed of a twin-engine helicopter comprising at least one turbine engine according to one of the embodiments described. Such a method therefore comprises a step of mechanically coupling the gas generator 5 and the free turbine 6 as soon as the speed NGG of rotation of the gas generator 5 is lower than a predetermined threshold speed.
    [0017] A method according to the invention is advantageously implemented by a turbine engine according to one of the embodiments described. A turbine engine according to one of the embodiments described advantageously implements a method according to the invention.
    权利要求:
    Claims (14)
    [0001]
    REVENDICATIONS1. Turbomotor comprising a gas generator (5) adapted to be rotated and a free turbine (6) driven in rotation by the gases of said gas generator, characterized in that it comprises a device (40) for mechanical coupling controlled by said generator (5) of gas and of said free turbine (6) adapted to mechanically link and on command said gas generator (5) and said free turbine (6) as soon as the speed of rotation of said gas generator (5) reaches a predetermined threshold speed.
    [0002]
    2. Turbomotor according to claim 1, characterized in that said device (40) of controlled mechanical coupling is adapted to mechanically link and on command said generator (5) of gas and said turbine (6) free as soon as said speed (NGG) of rotation of said gas generator (5) is lower than said predetermined threshold speed and to separate on command said gas generator (5) and said free turbine (6) as soon as said rotational speed (NGG) of said generator (5) of gas is greater than said predetermined threshold speed.
    [0003]
    3. Turbomotor according to one of claims 1 or 2, characterized in that said threshold speed is a function of a nominal speed of said generator (5) of gas.
    [0004]
    4. Turbomotor according to claim 3, characterized in that said threshold speed is chosen in the range [20% .N1, 60% .N1], where N1 is said nominal speed of said gas generator.
    [0005]
    5. Turbomotor according to one of claims 1 to 4, characterized in that said device (40) for controlled mechanical coupling comprises: means for reading an information representative of said speed (NGG) of rotation of said gas generator, reversible mechanical coupling means (41) between a shaft (42) mechanically connected to said gas generator and a shaft (43) mechanically connected to said free turbine (6), means for controlling said coupling means (41) according to said information representative of said speed of rotation of said gas generator and said threshold speed.
    [0006]
    6. Turbomotor according to claim 5, characterized in that said coupling means (41) are selected from the group comprising at least one friction clutch, a clutch, and a clutch equipped with a synchronizer.
    [0007]
    7. Turbomotor according to one of claims 4 or 5, characterized in that said coupling means (41) are configured to allow a temporary sliding between the shaft (42) mechanically connected to said gas generator (5) and the shaft (43) mechanically connected to said free turbine (6) during a preliminary mating phase.
    [0008]
    8. Turbomotor according to one of claims 1 to 7, characterized in that it further comprises a device (20) for spontaneous mechanical coupling of said generator (5) of gas and said turbine (6) free adapted to mechanically bind and spontaneously said generator (5) of gas and said turbine (6) free as soon as the ratio of the speed (NGG) of rotation of said generator (5) of gas by the speed (NTL) of rotation of said turbine (6) free reaches a predetermined threshold value.
    [0009]
    9. Turbomotor according to claim 8, characterized in that said device (20) for spontaneous mechanical coupling is adapted to mechanically and spontaneously bind said generator (5) of gas and said turbine (6) free as soon as said gear ratio is lower. at said predetermined threshold value and for spontaneously separating said gas generator (5) and said free turbine (6) as soon as said ratio (NGG / NTL) is greater than said predetermined threshold value.
    [0010]
    10. Turbomotor according to one of claims 8 or 9, characterized in that said device (20) for spontaneous mechanical coupling comprises at least one free wheel (21) connecting a first shaft (22) having with said gas generator a ratio reduction device K1 and a second shaft (23) presenting with the free turbine (6) a reduction ratio K2, said free wheel (21) being arranged in such a way that said free turbine (6) spontaneously drives said generator (5) gas, through said shafts and said free wheel (21), as soon as said ratio (NGG / NTL) velocities is lower than the ratio K2 / K 1.
    [0011]
    11. Turbomotor according to claim 10, characterized in that it comprises a generator-starter (30) integral with an intermediate shaft (25) and in that said device (20) for spontaneous mechanical coupling comprises two wheels (24, 26). ) respectively connecting said shaft (25) intermediate with said first shaft (22) having with said gas generator (5) a reduction ratio K1 and said second shaft (23) having with the turbine (6) free a reduction ratio K2, said wheels (24, 26) being arranged in such a way that said free turbine (6) spontaneously drives said gas generator (5), through said shafts and said free wheels, as soon as said ratio (NGG / NTL) speeds is less than the K2 / K1 ratio.
    [0012]
    12. Helicopter twin engine characterized in that it comprises at least one turbine engine according to one of claims 1 to 11.
    [0013]
    13. A method for optimizing the zero-power super-idle speed of a twin-engine helicopter comprising at least one turbine engine comprising a gas generator (5) adapted to be rotated and a free turbine (6) driven in rotation by the gases of said gas generator (5), characterized in that it comprises a controlled mechanical coupling step of said gas generator (5) and said free turbine (6) as soon as the speed of rotation of said gas generator reaches a speed predetermined threshold.
    [0014]
    14. An optimization method according to claim 13, characterized in that it further comprises a step of spontaneous mechanical coupling of said gas generator and the free turbine as soon as the ratio of the speed (NGG) of rotation of said generator ( 5) of gas by the speed (NTL) of rotation of said free turbine (6) reaches a predetermined threshold value.
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    EP3123008A1|2017-02-01|
    EP3123008B1|2018-05-16|
    US20170101936A1|2017-04-13|
    KR20160135765A|2016-11-28|
    RU2016140813A|2018-04-28|
    FR3019223B1|2016-03-18|
    JP6553636B2|2019-07-31|
    RU2674861C2|2018-12-13|
    CA2943618A1|2015-10-01|
    US10415482B2|2019-09-17|
    RU2016140813A3|2018-10-09|
    JP2017520706A|2017-07-27|
    WO2015145045A1|2015-10-01|
    ES2674392T3|2018-06-29|
    CN106460661A|2017-02-22|
    CN106460661B|2018-11-13|
    PL3123008T3|2018-08-31|
    KR102298941B1|2021-09-07|
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    法律状态:
    2015-03-16| PLFP| Fee payment|Year of fee payment: 2 |
    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
    FR1452654A|FR3019223B1|2014-03-27|2014-03-27|TURBOMOTOR COMPRISING A CONTROLLED MECHANICAL COUPLING DEVICE, HELICOPTER EQUIPPED WITH SUCH A TURBOMOTOR, AND METHOD FOR OPTIMIZATION OF THE NULL POWER SUPER-SLOWING REGIME OF SUCH A HELICOPTER|FR1452654A| FR3019223B1|2014-03-27|2014-03-27|TURBOMOTOR COMPRISING A CONTROLLED MECHANICAL COUPLING DEVICE, HELICOPTER EQUIPPED WITH SUCH A TURBOMOTOR, AND METHOD FOR OPTIMIZATION OF THE NULL POWER SUPER-SLOWING REGIME OF SUCH A HELICOPTER|
    JP2016558681A| JP6553636B2|2014-03-27|2015-03-20|Turboshaft engine with controlled and mechanically coupled device, helicopter equipped with such a turboshaft engine, and method for optimizing the unloaded super idle speed of such helicopter|
    PCT/FR2015/050701| WO2015145045A1|2014-03-27|2015-03-20|Turboshaft engine comprising a controlled mechanical coupling device, helicopter equipped with such a turboshaft engine, and method for optimising the zero-power super-idle speed of such a helicopter|
    KR1020167028885A| KR102298941B1|2014-03-27|2015-03-20|Turboshaft engine comprising a controlled mechanical coupling device, helicopter equipped with such a turboshaft engine, and method for optimising the zero-power super-idle speed of such a helicopter|
    US15/128,375| US10415482B2|2014-03-27|2015-03-20|Turboshaft engine comprising a controlled mechanical coupling device, helicopter equipped with such a turboshaft engine, and method for optimising the zero-power super-idle speed of such a helicopter|
    ES15717554.8T| ES2674392T3|2014-03-27|2015-03-20|Turbomotor that includes a commanded mechanical coupling device, helicopter equipped with such a turbomotor and super-idle speed optimization procedure with zero power of such helicopter|
    PL15717554T| PL3123008T3|2014-03-27|2015-03-20|Turboshaft engine comprising a controlled mechanical coupling device, helicopter equipped with such a turboshaft engine, and method for optimising the zero-power super-idle speed of such a helicopter|
    RU2016140813A| RU2674861C2|2014-03-27|2015-03-20|Turboshaft engine comprising controlled mechanical coupling device, helicopter equipped with such turboshaft engine, and method for optimising zero-power super-idle speed of such helicopter|
    EP15717554.8A| EP3123008B1|2014-03-27|2015-03-20|Turboshaft engine comprising a controlled mechanical coupling device, helicopter equipped with such a turboshaft engine, and method for optimising the zero-power super-idle speed of such a helicopter|
    CN201580020372.3A| CN106460661B|2014-03-27|2015-03-20|The method of turboaxle motor including controlled mechanical attachment equipment, the super idle speed of zero energy equipped with the helicopter of this turboaxle motor and for optimizing this helicopter|
    CA2943618A| CA2943618A1|2014-03-27|2015-03-20|Turboshaft engine comprising a controlled mechanical coupling device, helicopter equipped with such a turboshaft engine, and method for optimising the zero-power super-idle speedof such a helicopter|
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