• 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 turbojet engine comprising a fan shaft (12) driven by a turbine shaft (16) via a device (20) for reducing the speed of rotation, characterized in that it comprises a means (28) for decoupling the reduction device (20) and the turbine shaft (16) in response to the exceeding of a determined resisting torque exerted by the reduction device (20) on the shaft (16) of turbine.
    公开号:FR3022890A1
    申请号:FR1455939
    申请日:2014-06-25
    公开日:2016-01-01
    发明作者:Alexandre Tan-Kim；Julien Fabien Patrick Becoulet
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The field of the present invention is that of aeronautical turbomachines and, more particularly that of turbomachines with a double flow comprising a reduction device for driving the fan. Conventionally, the turbomachines comprise, starting from upstream, one or more compressor modules arranged in series, which compress air sucked into an air inlet. The air is then introduced into a combustion chamber where it is mixed with fuel and burned. The combustion gases pass through one or more turbine modules that drive the compressor (s) through associated turbine shafts. The gases are finally ejected either in a nozzle to produce a propulsive force or on a free turbine to produce power that is recovered on a transmission shaft.
    [0002] Current turbofan turbomachines with high dilution rate comprise several stages of compressor, including a low pressure compressor (LP) and a high pressure compressor (HP), crossed by a primary flow. These low pressure (LP) and high pressure (HP) compressors are each driven by a respective low pressure (LP) or high pressure (HP) turbine shaft. Upstream of the low pressure compressor (BP) is disposed a wheel having large blades or blades, or blower, which feeds both the primary flow through the compressors BP and HP and a cold flow, or secondary flow, which is directed directly to a cold flow nozzle, called secondary nozzle. The blower is driven by the BP turbine rotation shaft of the BP body and generally rotates at the same speed as it. It may be advantageous to rotate the fan at a lower rotational speed than the LP shaft, especially when it is of very large size, in order to better adapt aerodynamically. For this, there is a reduction device between the LP turbine shaft and a fan shaft, which is carrying the fan. Such a configuration is described in particular in patent applications FR 1251655 and 1251656 filed on February 23, 2012.
    [0003] In this configuration, it may occur that the fan loses a blade, for example in case of ingestion of a foreign body such as a bird. This phenomenon, also known by the Anglo-Saxon term "Fan Blade Out" (FBO) causes an eccentricity of the blower resulting in contact with the ends of its blades with the fan housing. This contact can brutally brake the blower while the reduction device and the turbine shaft are still driven by the LP turbine, which can create a high torque torque in the LP turbine shaft and in the reduction device .
    [0004] Such a torsion torque in the event of blade loss could severely damage the reduction device, which could then become blocked and make the rotation of the fan impossible. This would have the effect of sharply increasing the aerodynamic drag of the engine, making the aircraft impossible to fly.
    [0005] To overcome this drawback, one solution is to limit the torque that can pass through the reduction device and in the LP turbine shaft, to prevent the blocking of the fan.
    [0006] Furthermore, the limitation of this torque makes it possible to avoid over-sizing of the reduction device members and the low pressure turbine shaft, and consequently to reduce the design of the reduction device and the LP turbine shaft. .
    [0007] For this purpose, the invention proposes a turbomachine of the type described above, characterized in that it comprises a means of decoupling the reduction device and the turbine shaft in response to exceeding a determined resisting torque exerted by the reduction device on the turbine shaft.
    [0008] According to preferred embodiments of the invention, the decoupling means comprises at least one fusible link element which is interposed between the reduction device and the turbine shaft and which is capable of being broken when it is subjected to a decoupling resistant torque exerted by the speed reduction device on the turbine shaft.
    [0009] According to a first embodiment of the invention, the fuse element consists of a section of an input shaft of the reduction device connected to the turbine shaft, said section being able to be broken when is subjected to a maximum torsion torque corresponding to the decoupling resistant torque.
    [0010] According to a second embodiment of the invention, an input shaft of the reduction device comprises a tubular end section which is coupled with a complementary tubular end section of the turbine shaft via at least one radial element capable of being broken when it is subjected to a shear stress corresponding to the decoupling resistant torque. In this configuration, the radial element comprises a pin which is received in a radial orifice of the end section of the input shaft and in an orifice facing the end section of the turbine shaft. In a preferential manner of the invention, the determined decoupling resisting torque corresponds to a resistant torque exerted by the fan on the speed reduction device in the event of the loss of at least one blade of a fan driven by said fan shaft. . Furthermore, the resistive torque is strictly greater than any torque corresponding to a resistant torque exerted by the fan on the speed reduction device in the event of ingestion without loss of blade of a bird by said fan. For this purpose, an order of magnitude of the second determined decoupling torque determined, when the fan comprises metal blades, is 120 to 140% of a normal torque in maximum speed of the turbomachine. Similarly, an order of magnitude of the determined second decoupling torque, when the fan comprises blades of composite material is 130 to 170% of a normal torque in maximum speed of the turbomachine. Finally, in order to prevent runaway of the turbines in the event of decoupling, the turbomachine according to the invention advantageously comprises means for detecting the decoupling of the reduction device and the turbine shaft capable of controlling a reduction in speed of rotation. the turbine and / or a shutdown of the turbomachine. The invention will be better understood, and other objects, details, features and advantages thereof will appear more clearly in the following detailed explanatory description of an embodiment of the invention given as a purely illustrative and non-limiting example, with reference to the accompanying schematic drawings in which: - Figure 1 is an overall view of a turbomachine according to a prior art; FIG. 2A is a sectional view of the front part of a turbomachine according to a first embodiment of the invention equipped with a reduction device; Figure 2B is a detail view of Figure 2A; FIG. 3A is a sectional view of the front part of a turbomachine according to a second embodiment of the invention equipped with a reduction device; FIG. 3B is a detail view of FIG. 3A, FIG. 4 is a diagram illustrating the resistance torque exerted by the speed reduction device on the turbine shaft as a function of time during the loss of a blower blade. In the following description, like reference numerals refer to like parts or having similar functions. FIG. 1 shows a turbomachine such as a turbojet engine 10 produced according to a previous state of the art. In known manner, the turbojet engine comprises, from upstream to downstream according to the flow "F" of gas flow, a fan 12, a low-pressure compressor 14, a high-pressure compressor, a combustion chamber, a turbine high pressure and a low pressure turbine (not shown). The fan 12 comprises blades 13. The high pressure compressor and the high pressure turbine are connected by a high pressure shaft and form with it a high pressure body. The low pressure compressor 14 and the low pressure turbine are connected by a low pressure shaft 16 and form with it a low pressure body. The fan 12 is, in turn, carried by a fan shaft 18 which, in the example shown, is rotatably connected to the LP shaft 16, by means of a device 20 for reducing the speed of rotation. rotation between the two shafts 16, 18. Indeed, it is advantageous to rotate the blower 12 at a lower rotational speed than that of the LP shaft 16, especially when it is of very large size, for the purpose to better adapt it aerodynamically. The HP and BP shafts 16 extend along an axis "A" of rotation of the turbojet engine 10.
    [0011] The turbojet engine 10 also comprises, conventionally, a fan casing (not shown) which makes it possible to channel the gases sucked by the fan 12 to a stream 22 of primary flow, which passes through the BP and HP bodies, and a secondary flow vein ( not shown) which surrounds a casing of the BP and HP bodies and joins the primary flow stream in a nozzle (not shown) of the turbojet engine.
    [0012] As illustrated in FIG. 1, the reduction device 20 is positioned between the fan shaft 18 and the LP shaft 16. This reduction device, for example of the epicyclic type, is represented in the schematic form of rectangles showing than its bulkiness. It is driven by a sun gear 24 carried by an input shaft 26 which is rotatably connected to the LP shaft 16, the shaft 16 being, by way of example only, received without play by fitting into the shaft 26. In this configuration, it may occur that the blower 12 loses a blade 13, for example in case of ingestion of a foreign body such as a bird or as a result of a fatigue break resulting from improper maintenance . This phenomenon, also known by the Anglo-Saxon term called "Fan Blade Out" (FBO) causes an eccentricity of the fan 12 relative to the axis "A", which has the effect of causing a contact of the ends of its blades 13 with the casing (not shown) of the blower 12. This contact can brutally brake the blower 12 while the reduction device 20 and the LP turbine shaft 16 are still driven by the LP turbine, which can create a high torque in the LP turbine shaft 16 and in the reduction device 20.
    [0013] Such a torsion torque in the event of the loss of a blade 13 may seriously damage the reduction device 20, which could then become blocked and make the rotation of the fan impossible. This would have the consequence of increasing the drag considerably. aerodynamic engine, making the aircraft impossible to fly.
    [0014] To remedy this drawback, one solution consists in limiting the torque that can pass through the reduction device 20 and in the LP turbine shaft 16, in order to prevent the blower 12 from being blocked.
    [0015] The limitation of the torsion torque has another advantage, which is to make it possible to avoid over-dimensioning the elements of the reduction device 20 and the LP turbine shaft 16 capable of ensuring their resistance to such a torsion torque when passing. a determined resisting torque exerted by the speed reduction device 20 on the turbine shaft 16.
    [0016] Moreover, the limitation of this torque makes it possible to avoid any oversizing of the members of the reduction device 20 and the low-pressure turbine shaft 16, and consequently to reduce the design of the reduction device 20 and the shaft 16 of BP turbine.
    [0017] For this purpose, the invention proposes a turbomachine of the type described above, characterized in that it comprises a means 28 for decoupling the reduction device 20 and the turbine shaft 16 in response to exceeding a determined resistive torque exerted by the speed reduction device 20 on the turbine shaft 16.
    [0018] More particularly, as illustrated in FIGS. 2A and 3A, the decoupling means 28 comprise at least one fusible link element 30, 30 'which is interposed between the reduction device 20 and the turbine shaft 16 and which is capable of to be broken when subjected to a so-called decoupling resisting torque exerted by the speed reduction device on the turbine shaft, and which corresponds in particular to a determined resisting torque exerted by the fan 12 on the reduction device 20 of speed, then transmitted by said speed reduction device.
    [0019] The positioning of the fusible link element 30, 30 'between the reduction device 20 and the turbine shaft 16 has several advantages. In the first place, this positioning of the fusible link element 30, 30 'between the reduction device 20 and the turbine shaft 16 is easy to achieve at the level of the reduction device 20 because the shaft 18 of the fan is supported by two bearings 32, 34, and because the shaft 16 of the LP turbine is also supported by two bearings, a single bearing 36 has been shown in Figures 2A, 3A. The rupture of the element 30, 30 'fuse therefore does not affect the maintenance in rotation of the LP turbine shaft 16 or the shaft 18 of the fan. In the second place, the decoupling of the reduction device 20 and the turbine shaft 16 implies a free rotation speed of the fan 12 after stopping the turbojet engine higher than that which the same fan would have in a conventional turbojet engine. the turbojet engine would be stopped without the fan 12 being decoupled. Thus, the blower is subjected to a free rotation speed or "windmilling" which allows the turbojet engine to produce only a reduced drag. Thirdly, the positioning of the fusible connecting element 30, 30 'between the reduction device 20 and the turbine shaft 16 makes it possible, as will be seen later in the rest of this description, to protect the device 20 reduction in case of overspeed of the shaft 16 of the turbine.
    [0020] According to a first embodiment which has been shown in FIG. 2A and in particular in FIG. 2B, the fuse element consists of a section 30 of the input shaft 26 of the reduction device linked to the shaft. 16 of the turbine. This section 30 is capable of being broken when it is subjected to a maximum torque corresponding to the determined decoupling resisting torque exerted by the reduction device 20 on the shaft 16. Any known solution of the state of the art can to suit the good realization of a section 30 of reduced torsional rigidity. In particular, the section may be a tubular section of reduced thickness "e", as shown in FIG. 2A. It may also be a perforated section 30 and / or with rupture initiation zones (not shown). According to a second embodiment which has been shown in FIG. 3A and in particular in FIG. 3B, the input shaft 26 of the reduction device comprises a tubular end section 38 which is coupled with an end section. 40 tubular complementary to the turbine shaft 16 through at least one radial element 31, forming the fusible link element. This radial element 31 is capable of being broken when subjected to a shear stress corresponding to the decoupling resisting torque. It will be understood that the radial element 31 forming the fuse element can be shaped according to many embodiments. However, preferably of the invention, the radial element 31 consists of a pin, in particular cylindrical, which is received in a radial orifice 42 of the end section of the input shaft 26 and in an orifice 44. facing the end portion of the shaft 16 of the turbine. In each of these two embodiments, it will be understood that the positioning of the element 30, 31 fuse link on the input shaft ensures the support of the sun gear 24 of the reduction device after decoupling. Indeed, the sun gear 24 is supported via the planet carrier by the output shaft (not shown) of the reduction device 20.
    [0021] In each of these two embodiments, the fuse element 30 is calibrated to break when respectively the section 30 or the pin 31 is subjected to a decoupling torque corresponding to a resistant torque exerted by the fan on the device 20 for reducing the speed in case of loss of at least one blade 13 of the fan driven by said fan shaft 18, and transmitted by the reduction device 20. Thus the break is expected at least and this, since the loss of a single blade 13.
    [0022] Conversely, it is expected that the rupture occurs only in case of breakage or loss of a blade 13, and not in the event of a simple slowing down of the fan 12. Thus, it is expected that the determined resisting torque is strictly greater to any torque corresponding to a resistant torque exerted by the blower 12 on the speed reduction device 20 and transmitted by the device 20, in the event of ingestion without blade loss of a bird by said blower 12, such an event being able to produce a tangential force slowing the blower 12, but which does not risk damaging the reduction device 20 nor block the kinematic chain considered.
    [0023] FIG. 4 comparatively illustrates the resistive torque "C" transmitted, as ordinate, as a function of time "t" on the abscissa, in the event of rupture of a fan blade 13.
    [0024] As can be seen on the curve in strong lines, in a conventional turbomachine, from an optimal operating torque Co, it can occur at a time TR a rupture of a blade 13. This rupture leads to an increase in resistant torque up to a limit value Cmax corresponding to the blocking of the reduction device 20 and the blower 12, or more precisely to a risk of blockage according to the specifications of the reduction device, making it unsuitable for use. In the turbomachine according to the invention, the maximum torque is calibrated to a CD torque or decoupling torque. Therefore, during operation, it can also occur at a time TR a rupture of a blade 13, which leads to an increase in the resistive torque up to the value CD or torque decoupling value. The torque then decreases, according to the dotted line curve, to a value C 1, corresponding to a state of free rotation of the fan 12. By way of example, and in a nonlimiting manner of the invention, an order of magnitude of the determined decoupling torque determined, when the fan comprises metal blades, is from 120 to 140% of a normal torque in maximum speed of the turbomachine. When the fan comprises blades of composite material, an order of magnitude of the determined decoupling torque determined is 130 to 170% of a normal torque at maximum speed of the turbomachine. By way of example only, and in a nonlimiting manner of the invention, the value of the transmitted decoupling torque determined in these two cases therefore varies substantially between 50000 Nm and 400000 Nm. It will be understood that these values are not they are indicative and depend both on the type of blade used, and on the architecture and size of the engine. It will be understood that from the moment when the fan is decoupled from the turbine shaft 16, the turbine is no longer subjected to a resisting torque from said fan. There is therefore a risk of runaway of the turbine. It will be noted that another essential advantage of the positioning of the fusible connecting element 30, 30 'between the reduction device 20 and the turbine shaft 16 is to make it possible to protect the reduction device 20 in the event of a runaway. the turbine, the latter not risking being subjected to high rotational speeds for which it would not be expected. However, according to the invention, the turbomachine or turbojet engine 10 comprises means for detecting the decoupling of the reduction device 20 and 10 of the turbine shaft 16 able to control at least a speed reduction of the turbine, or even a stop complete turbojet engine. Thus, it is known to measure the speed of the turbine shaft by a speed sensor. A detection of the runaway of the measured speed can thus be interpreted as a decoupling and trigger the activation of motor control members. It is therefore possible to limit the fuel flow to reduce the speed of the turbine, or, if there is a turbine comprising an axial brake between a rotor portion and a stator portion, to activate this brake to slow down and / or stop the turbine. The invention therefore provides a safe solution to the risk of fan blade rupture of a turbomachine.
    [0025] Finally, the invention also makes it possible, by limiting the transmitted torque, to avoid any oversizing of the reduction device 20 and the low pressure turbine shaft 16 in order to overcome the known risks of increasing said torque in case of blade loss. Since these members no longer need to be oversized to respond to high torsional stresses, they can be reduced in size, which has the effect of reducing overall the design of the reduction device 20 and the LP turbine shaft 16. .
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Turbomachine (10) comprising a fan shaft (12) driven by a turbine shaft (16) via a device (20) for reducing the speed of rotation, characterized in that it comprises means ( 28) for decoupling the reduction device (20) and the turbine shaft (16) in response to exceeding a determined resistive torque exerted by the reduction device (20) on the turbine shaft (16).
    [0002]
    2. The turbomachine (10) according to the preceding claim, characterized in that the means (28) for decoupling comprises at least one fusible link element (30) which is interposed between the device (20) for reduction and the shaft (16). ) turbine which is capable of being broken when subjected to a decoupling resistance (CD) torque exerted by the device (20) for reducing speed on the turbine shaft (16).
    [0003]
    3. Turbomachine (10) according to the preceding claim, characterized in that the fuse element consists of a section (30) of an input shaft (26) of the device (20) of reduction linked to the shaft (16) of the turbine, said section (30) being capable of being broken when subjected to a maximum torque corresponding to the decoupling resisting torque (CD).
    [0004]
    4. Turbine engine (10) according to claim 2, characterized in that an input shaft (26) of the reduction device (20) comprises a tubular end section (38) which is coupled with an end section. tubular (40) complementary to the turbine shaft (16) via at least one radial element (30 ') of fusible link capable of being broken when subjected to a shear stress corresponding to the resistant torque (CD) decoupling.
    [0005]
    5. Turbomachine (10) according to the preceding claim, characterized in that the radial element comprises a pin (30 ') which is received in a radial orifice (42) of the end section (38) of the shaft of inlet (26) and in an orifice (44) facing the end section (40) of the turbine shaft (16).
    [0006]
    6. Turbomachine (10) according to one of the preceding claims, characterized in that the determined decoupling resisting torque (CD) corresponds to a resistant torque exerted by the fan on the device speed reduction in case of loss of at least a blade of a fan driven by said fan shaft.
    [0007]
    7. Turbomachine (10) according to one of the preceding claims, characterized in that the resistive torque (CD) is strictly greater than any torque corresponding to a resistant torque exerted by the fan (12) on the device (20) reduction of speed in case of ingestion without loss of blade of a bird by said blower (12).
    [0008]
    8. turbomachine (10) according to one of claims 6 or 7, characterized in that the decoupling resisting torque (CD) associated with a fan having metal blades is between 120 and 140% of a normal torque regime maximum of the turbomachine.
    [0009]
    9. Turbine engine (10) according to one of claims 6 or 7, characterized in that the decoupling resisting torque (CD) associated with a fan comprising blades of composite material is between 130 and 170% of a normal torque in maximum speed of the turbomachine.
    [0010]
    10. Turbomachine (10) according to one of the preceding claims, characterized in that it comprises means for detecting the decoupling of the device (20) for reduction and the shaft (16) of turbine adapted to control a reduction of turbine speed and / or a shutdown of the turbomachine (10).
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    引用文献:
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    GB2377731A|2001-07-21|2003-01-22|Rolls Royce Plc|Rotor shaft assembly for a gas turbine engine|
    EP2048330A2|2007-10-09|2009-04-15|United Technologies Corporation|Systems and methods involving multiple torque paths for gas turbine engines|
    US20130014513A1|2011-07-15|2013-01-17|Barry Barnett|Connection for generator in a gas turbine engine|
    US20130324343A1|2012-05-30|2013-12-05|Snecma|Reduction gear with epicyclic gear train having roller-bearing-mounted planet spindles|EP3296540A1|2016-09-20|2018-03-21|Rolls-Royce Deutschland Ltd & Co KG|Gas turbine engine with a geared turbofan arrangement|
    EP3296525A1|2016-09-20|2018-03-21|Rolls-Royce Deutschland Ltd & Co KG|Gas turbine engine with a geared turbofan arrangement|
    FR3061238A1|2016-12-23|2018-06-29|Safran Aircraft Engines|REDUCING TURBOMACHINE FOR AN AIRCRAFT EQUIPPED WITH FUSIBLE MEANS|
    EP3396115A1|2017-04-28|2018-10-31|Rolls-Royce Deutschland Ltd & Co KG|Gas turbine engine|
    EP3415726A1|2017-06-16|2018-12-19|United Technologies Corporation|Geared turbofan with overspeed protection|
    US10428741B2|2016-09-20|2019-10-01|Rolls-Royce Deutschland Ltd & Co Kg|Gas turbine engine with a geared turbofan arrangement|
    WO2019186028A1|2018-03-27|2019-10-03|Safran Aircraft Engines|Turbine shaft of a turbomachine and method for protecting against overspeed of said shaft|
    US10502144B2|2016-09-20|2019-12-10|Rolls-Royce Deutschland Ltd & Co Kg|Gas turbine engine with a geared turbofan arrangement|
    FR3106363A1|2020-01-22|2021-07-23|Safran Aircraft Engines|BLOWER MODULE FOR AN AIRCRAFT TURBOMACHINE TEST BENCH|FR1251656A|1960-03-18|1961-01-20|Fitting for plastic and other pipes|
    FR1251655A|1960-03-18|1961-01-20|Camping tent|
    US4651521A|1985-11-21|1987-03-24|Avco Corporation|Convertible turbo-fan, turbo-shaft aircraft propulsion system|
    FR2826052B1|2001-06-19|2003-12-19|Snecma Moteurs|RELIEF DEVICE FOR THE IGNITION OF A SELF-ROTATING TURBO-JET|
    FR2845126B1|2002-09-26|2004-12-03|Snecma Moteurs|TRACTION COUPLER DEVICE|
    CN203271949U|2013-04-18|2013-11-06|李宇霞|Novel small-sized duct turbofan engine|
    FR3013385B1|2013-11-21|2015-11-13|Snecma|PRE-SEALED SPEAKER DURING MODULAR DISASSEMBLY OF A REDUCING TURBOREACTOR|GB201419859D0|2014-11-07|2014-12-24|Rolls Royce Plc|No title listed|
    US10737801B2|2016-10-31|2020-08-11|Rolls-Royce Corporation|Fan module with rotatable vane ring power system|
    US10738646B2|2017-06-12|2020-08-11|Raytheon Technologies Corporation|Geared turbine engine with gear driving low pressure compressor and fan at common speed, and failsafe overspeed protection and shear section|
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    法律状态:
    2015-06-11| PLFP| Fee payment|Year of fee payment: 2 |
    2016-01-01| PLSC| Search report ready|Effective date: 20160101 |
    2016-05-06| RM| Correction of a material error|Effective date: 20160404 |
    2016-06-16| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-28| PLFP| Fee payment|Year of fee payment: 4 |
    2017-11-10| CD| Change of name or company name|Owner name: SNECMA, FR Effective date: 20170713 |
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    优先权:
    申请号 | 申请日 | 专利标题
    FR1455939A|FR3022890B1|2014-06-25|2014-06-25|TURBOMACHINE COMPRISING A MEANS FOR DECOUPLING A BLOWER|
    FR1455939|2014-06-25|FR1455939A| FR3022890B1|2014-06-25|2014-06-25|TURBOMACHINE COMPRISING A MEANS FOR DECOUPLING A BLOWER|
    PCT/FR2015/051614| WO2015197949A1|2014-06-25|2015-06-17|Turbomachine comprising a means of uncoupling a fan|
    JP2016574387A| JP6682458B2|2014-06-25|2015-06-17|Turbomachine with means for separating fans|
    CN201580037563.0A| CN106661959B|2014-06-25|2015-06-17|Turbine including the device for making the de- connection of fan|
    CA2952914A| CA2952914A1|2014-06-25|2015-06-17|Turbomachine comprising a means of uncoupling a fan|
    EP15738729.1A| EP3161270B1|2014-06-25|2015-06-17|Turbomachine comprising means for decoupling a fan|
    RU2017100264A| RU2681392C2|2014-06-25|2015-06-17|Turbomachine comprising means of fan disconnecting|
    US15/390,353| US20170175753A1|2014-06-25|2016-12-23|Turbomachine comprising a means of uncoupling a fan|
    US16/728,992| US20200149542A1|2014-06-25|2019-12-27|Turbomachine comprising a means of uncoupling a fan|
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