• 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 turbomachine comprising a fixed structure (7), a rotor (3) of a fan (1), having an axis (XX) of rotation, and emergency braking means (12, 13) of the rotor ( 3), in particular in case of loss of a blade of the blower (1), characterized in that said means (12, 13) for emergency braking comprise a first (18) and a second (22) worn organs by the fixed structure (7), said members (18, 22) being respectively configured to cooperate by friction with a first (20) complementary element of the rotor (3), forming a stop of the rotor (3) rearward following the axis (XX), and a second (24) complementary element of the rotor (3), forming a stop of the rotor (3) forward along the axis (XX), when the emergency braking means (12, 13) are active.
    公开号:FR3026774A1
    申请号:FR1459595
    申请日:2014-10-07
    公开日:2016-04-08
    发明作者:Julien Fabien Patrick Becoulet；Alexandre Jean-Marie Tan-Kim
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] Field of the Invention: The present invention relates to a turbomachine comprising a blower with a device for reducing the dynamic loads in the event of an accident on the blower, leading to the loss of a blade.
    [0002] State of the art: A turbomachine mounted on an aircraft comprises, from front to rear, or upstream to downstream, in the direction of the flow of gases, a fan, one or more compressor stages, a combustion chamber , one or more turbine stages and a gas exhaust nozzle. The fan comprises a rotor provided with vanes at its periphery which, when they are rotated, drive the air into the turbomachine. The fan rotor is connected to a drive shaft, which is centered on the axis of the turbomachine by a series of bearings, supported by support parts connected to a fixed structure of the stator of the turbomachine.
    [0003] It can happen, accidentally and luckily infrequently, the rupture of a fan blade during a flight. In this case, the engine is stopped but the rotor of the low pressure part goes into autorotation, mainly because of the aerodynamic forces on the fan, related to the speed of the aircraft. This phenomenon is commonly referred to as the Anglo-Saxon windmilling term. This results in a significant imbalance on the drive shaft of the fan, which causes dynamic loads and vibrations on the bearings, transmitted to the fixed structure of the turbomachine. It is particularly important to allow the entire structure of the turbomachine and the aircraft to withstand, without further damage, these efforts for a significant period, of the order of a few hours, to allow the plane to come back to rest after such an incident. In order to be able to size the structure of the turbomachine less cumbersome and less expensive, the prior art teaches, as for example in documents FR-A1- 2 752 024 and FR-A1- 2 877 046, to provide a system of decoupling one or more bearings in case of loss of a blade. This modifies the flexibility of the assembly of the fan rotor and makes it possible to adapt its resonance modes to reduce the forces produced by the unbalance. The structure of the turbomachine and the aircraft is sized to withstand the unbalance created by the fan rotor after the loss of a blade and the decoupling. In particular, some supports have thicknesses or manufacturing characteristics, in material or structure, oversized compared to normal operating constraints. Known solutions for reducing the load and the vibrations during this autorotation are intended to shift the frequency response of the structure, when the rotor is in decoupled mode, outside the frequency range of the stresses, for example by modifying the flexibility of the upstream structure holding the rotor or the position of a bearing of the fan shaft. However, this displacement of the response of the structure in decoupled mode can cause problems, in particular increase the loads at the beginning of the accident, during the loss of the blade, before the speed of rotation of the fan decreases. It can therefore be difficult to find the right compromise between the maximum loads appearing during the loss of the blade and those that must be supported during the autorotation flight phase. The present invention therefore aims to provide a means of reducing the weight of the elements of the turbomachine and the aircraft sized to withstand unbalance in case of dawn loss, by reducing the loads and vibrations to which will be subjected the structure of the turbomachine during the autorotation flight phase, which also reduces the stresses that the turbomachine transmits to the aircraft structure during this phase of flight.
    [0004] SUMMARY OF THE INVENTION For this purpose, the invention relates to a turbomachine comprising a fixed structure, a fan rotor, having an axis of rotation, and emergency braking means of the rotor, in particular in case of loss of power. a blade of the fan, characterized in that said emergency braking means comprise first and second members carried by the fixed structure, said members being respectively configured to cooperate by friction with a first complementary element of the rotor, forming a stop of the rotor rearward along the axis, and a second complementary element of the rotor, forming a stop of the rotor forward along the axis (XX), when the emergency braking means are active. The term blower rotor here designates all the parts at the front of the turbomachine rotating together with the blades of the blower, including the drive shaft to which it is attached and which passes in the bearing or bearings guiding the rotation of the blower. The braking of the rotor plays at least two ways to reduce the induced loads and vibrations. In the first place, it decreases the value at which the speed of rotation of the autorotative blower rotor is established for a given speed of the aircraft. This decreases the intensity of the vibrations, which decrease with the speed of rotation of the blower during the stabilized flight phase after the accident. Secondly, the braking decreases the maximum load level by slowing down the rotor more strongly and limiting the transition time in the vicinity of the resonance mode before the rotation regime stabilizes.
    [0005] The first member and complementary element, on the one hand, and the second member and complementary element, on the other hand, form two braking devices playing in two opposite directions along the axis of rotation. This uses the axial movement of the fan rotor which tends, in a first step after the accident, to go backwards, then in a second step to start forward. From the accident, there will always be at least one active braking device and, over time, during a flight phase to return to an airport, both intervene. A second advantage of the invention is to maintain the rotor axially around an average position, so as to prevent it damaging other parts of the turbomachine by excessive displacement to the rear, or that it does not escape forward.
    [0006] Furthermore, the friction between an element and its complementary element is a simple way to obtain significant braking. In view of the fact that this system must be activated in the event of an accident and operate for a limited number of hours, the dimensioning of the members and elements ensuring the friction can be limited in weight.
    [0007] Advantageously, the extension of the contact surfaces between the members and the complementary elements is mainly radial. On the one hand, this makes it possible to optimize the extent of the friction surface in the environment of the rotor of the fan. On the other hand, since the intensity of the friction depends, inter alia, on the pressure force exerted on the contacts, it is easier to provide axial support between a part connected to the rotor and a part connected to the stator, which a radial interference of a rotor element by a member connected to the structure. Furthermore, the contact surfaces between the members and their complementary elements may also have a portion of axial extension. This makes it possible to increase the contact surfaces between the members and their complementary elements without greatly impacting the size of the system.
    [0008] Advantageously, the turbomachine comprises at least a first bearing, mounted between the fan rotor and a support member, said support member being connected to the fixed structure by a decoupling device arranged to break in case of loss of a blade of the blower. In itself, the decoupling process releases the movements of the fan rotor along the axis of rotation and thus increases the possibilities of friction of an organ on the complementary element. In addition, it is desired that the device is put in place automatically at the time of the accident. The triggering of the decoupling device is a good marker for activating the braking means, since this decoupling takes place at the very beginning of the incident, before the constraints go through a maximum after the loss of the blade. It is thus possible to mechanically depend on the implementation of the braking means by moving the parts of the turbomachine at the moment of this decoupling. Advantageously, at least one of said members is released in translation relative to the fixed structure along the axis of rotation, in the direction opposite to that for which it forms a stop, when the decoupling device is broken. This allows him to follow the movement of the rotor in the opposite direction to its stop direction, so to continue to ensure friction in this case. Preferably, the turbomachine further comprises means configured to urge at least one of said members against the corresponding complementary element when said decoupling device is broken. Such biasing means makes it possible, in particular, to keep the member released in translation pressed against the corresponding element on the rotor, when the rotor starts in the direction opposite to the stop formed by said member. Furthermore, at least one of said members may be secured to a part connected to the fixed structure by said decoupling device. Furthermore, the biasing means may comprise a spring means between the support piece of said member and the fixed structure. . Advantageously, only the first member is biased by a biasing means, the second member being mounted integral with the fixed structure. Indeed, the rotor tends to start forward during a major flight phase after the first sequences of the accident. It is therefore advantageous for the first member to follow this movement, against a fixed device for the second member is simpler design and can be naturally solicited during these phases of flight. Advantageously, in this case, the turbomachine comprises a normal operating configuration, in particular before the loss of a fan blade, in which the emergency braking means are inactive and configured so that the spacing along the axis between the first member and element is greater than the spacing between the second member and member. Thus, pressing forward the first member which drives the complementary element on the rotor causes the second member and the complementary element on the rotor to form a stop towards the front of the fan rotor. in touch. The two braking devices are therefore active together during the flight phases after the accident by means of pushing the first device. Also preferably, the fan rotor is centered and guided by at least one second bearing mounted between the fixed structure and the rotor, said second bearing being located between said members. The first bearing has been decoupled, this second bearing is a fixed point for unbalance movements of the fan rotor. It is therefore easier to design the braking devices for the surfaces of the members connected to the fixed structure and the elements connected to the rotor rub substantially in a rotational movement.
    [0009] Advantageously, the forward thrust means of said first member bears between the support piece of this member and a support piece of the second bearing. Advantageously, the fan rotor comprises a drive shaft, which can support at least one of said elements. BRIEF DESCRIPTION OF THE FIGURES: The present invention will be better understood and other details, characteristics and advantages of the present invention will emerge more clearly on reading the description of a nonlimiting example which follows, with reference to the appended drawings in which: - Figure 1 schematically shows a section along the axis of the turbomachine, its front portion comprising the fan rotor; FIG. 2 shows an axial section of the front part of the turbomachine comprising the invention, when the turbomachine is operating normally; FIG. 3 shows an axial section of the front part of the turbomachine comprising the invention, during a first phase of accidental sequence; FIG. 4 shows an axial section of the front part of the turbomachine comprising the invention, during a second accidental sequence phase; and FIG. 5 shows the principle of observed dynamic forces as a function of the rotational speed of the fan rotor for a turbomachine, according to the invention and without the invention.
    [0010] DESCRIPTION OF AN EMBODIMENT With reference to FIG. 1, a turbomachine according to the invention comprises a fan 1 fixed to a drive shaft 2 which drives it in rotation around the axis XX of the turbomachine, when the motor, not shown back, works.
    [0011] In this example, the fan rotor 3 comprises the fan itself with its vanes, the drive shaft 2, connection pieces 4 between the shaft 2 and the fan 1, as well as the rotor part of the compressor. low pressure, integral with the fan 1. This rotor is here supported by two successive bearings, from front to rear following the flow of gas. A first bearing 5 is connected to a flange 6 of the fixed structure 7 of the turbomachine by a frustoconical piece 8, called bearing support piece. A second bearing 9 directly supports the drive shaft 2 and is connected to the fixed structure 7 by a second support part 10, which is here secured to the flange 6. The support part 8 of the first bearing 5 is fixed to the flange 6 by a plurality of longitudinal fusible screws 11, passing through the various parts that they join by circular orifices distributed circumferentially and matched during assembly. According to known techniques, for example that described in the patent application FR-A1- 2,877,46, these fusible screws 11 are designed to break if the longitudinal forces to which they are subjected exceed a certain threshold, corresponding, for example, to the unbalance in case of loss of a blade of the fan 3. By breaking, these screws 11 decouple the support part 8 of the first bearing 5 of the flange 6 and thus allow the assembly of the fan rotor 3 to move relative to the fixed structure 7 of the turbomachine. Generally, means, not shown in FIG. 1, block in rotation the support part 8 of the first bearing 5 and limit its translation towards the front of the turbomachine.
    [0012] According to the invention, devices 12, 13 are arranged, here at the level of the shaft 2 around the second bearing 9, to brake the fan rotor 3 in the event of decoupling with respect to the flange 8. FIGS. and 4 allow to detail the characteristics of a preferred embodiment, not limiting, of the invention. Referring to Figure 2, the support part 10 of the second bearing 5 comprises a cylindrical portion 10a to which is fixed the outer ring of the second bearing 9 and a portion 10b, forming a disc integral with the flange 6. These two parts, 10a and 10b, are connected by a portion 10c, substantially frustoconical. The front face of the disk 10b of the support part 10 of the second bearing 9 is slightly set back with respect to the front face of the flange 6.
    [0013] In the normal operating position of the turbomachine, shown in FIG. 2, the fusible screw 11 holds the support piece 8 of the first bearing 5, not shown, against the flange 6, by tightening a transverse piece 14 between the two parts. extends radially towards the shaft 2 of the fan rotor 3. The peripheral portion of the transverse part 14 has a bent rim 15 which is placed behind a radial peripheral flange 16 of the flange 6, leaving a gap. The central portion of the transverse piece 14, having the shape of a disc, plate against the front face of the disc 10b of the support piece 10 of the second bearing 9, a washer 17, which is housed in the withdrawal relative to the face before the flange 6. The washer 17 used here may be a washer "Grower", an Anglo-Saxon word that can be translated as "that extends", or a washer "Belleville", the name of their inventor . This type of washer has the property of moving elastically, as it is compressed or not along its axis, the shape of a flat washer to a helical washer, for a washer "Grower", or frustoconical, for a "Belleville" puck. In fact, this washer 17 can be replaced by any form of spring, 15 able to separate the transverse part 14 of the support part 10 in the direction of the axis of the turbomachine and to be housed in the shrinkage formed by shaped part disc 10b, when the fusible screws 11 are tightened. The radially inner part of the piece 14, in the form of a frustoconical shoe, is housed radially under the frustoconical portion 10c of the support piece 10 of the second bearing 9. On its internal radial corner, at the front, a notch forms, in recess in the part 14, a surface 18 of revolution about the axis of the turbomachine. This surface 18, facing the front of the turbomachine has a substantially transverse portion and a cylindrical portion. An annular ring 19 is fixed on the shaft 2, facing the notch on the transverse part 14. The rear face 20 of this ring 19 takes the hollow shape of the surface of revolution 18 of the notch of the piece 14, so that the transverse portions of the rear face 20 of the abutment and the surface 18 of the notch are joined together if they are translated against each other. In the configuration shown in FIG. 2, the rear face 20 of the ring 19 and the surface 18 of the notch of the transverse part 14 are spaced by a determined distance d1 and are not in contact. They form a member 18 connected to the fixed structure 7 of the turbomachine and a complementary element 20 connected to the fan rotor 3, making up a first braking device 12 of the fan rotor 3, which is seen here in the inactive mode. Furthermore, the cylindrical portion 10a of the support member 10 comprises, on the other side relative to the bearing 9, a ring 21 on the radially inner face of its rear end. This ring 21 has on its rear face a notch which forms a surface of revolution 22, similar to the surface 18 of the notch before, but turned towards the rear of the turbomachine. Similarly, an annular ring 23 is fixed on the shaft 2, facing the notch of the ring 21 on the support member 10. The front face 24 of this annular ring 23 has a shape that adapts to that of the surface of revolution 22 of the ring 21 on the support part 10, when pressed in translation along the axis of the turbomachine. In the configuration shown in FIG. 2, the front face 24 of the ring 23 fixed to the shaft 2 and the surface 22 of the rear notch of the ring 21 on the support part 10 are spaced apart by a determined distance d2 and are not in contact. They form a member 20 connected to the fixed structure 7 of the turbomachine and a complementary element 24 connected to the fan rotor 3, constituting a second braking device 13 of the fan rotor 3, which is shown here, also in idle mode. . It can be noted at this stage that the axial displacement d2 of the second braking device 13 is significantly smaller than the axial displacement d1 of the first device 12. Advantageously, the contact surfaces 18, 20, 22, 24 of the two braking devices are formed of a layer of carbon or steel material, of the type used in known manner in disk brake devices. With reference to FIG. 3, the configuration will now be described in a first situation in decoupled mode, when the fusible screws 11 have yielded. In this situation, the support part 8 of the first bearing and the transverse part 14 are free in translation along the axis of the turbomachine with respect to the fastening flange 6 to the fixed structure 7 of the turbomachine. For various reasons, among which we can cite the vibrations, the behavior of the fan rotor 3 and the thrust made by the washer "Grower" 17, these two parts tend to move forward, the flange 6 of fixation.
    [0014] However, the bent flange 15, abutting the peripheral flange 16 of the flange 6, prevents them from escaping and keeps them close to this flange 6. Moreover, the portion of each screw 11 which remains connected to the workpiece support 8 and the transverse part 14, remains nested in its through hole through the flange 6, due to the limitation of the spacing. In this way, the support part 8 of the first bearing and the transverse part 14 remain locked in rotation relative to the fixed structure 7 of the turbomachine. In alternative embodiments, other known devices, not shown here, can be arranged to achieve this effect. The situation described in FIG. 3 corresponds to the case where, at first, the fan rotor has moved backwards. Near the fan rotor drive shaft 2, the first braking device 12 is now in active mode because the surface 18 of the notch of the transverse part 14 and the surface of the rear face 20 of the ring 19 on the shaft 2 are in contact. In particular, their axially transverse parts rub against each other. Indeed, the movement of the fan rotor 3 rearwardly drives that of the shaft 2 relative to the fixed structure 7 of the turbomachine. By itself, this effect can catch the axial deflection dl arranged between the two surfaces 18, 20 for the normal operation of the turbomachine. Incidentally, by the way, this device 12 also serves as a backward stop to prevent a rearward displacement of the shaft 2, which could damage the low pressure part of the turbomachine with which it is in relation. In addition, as noted above, the washer "Grower" 17 has deployed as a result of the rupture of the fusible screws 11. This washer 17 moves the cross piece 14 forward. It thus makes it possible to catch up more quickly the axial displacement d1 and increases the pressure force between the friction surfaces 18, 20. On the other hand, during this first phase, the second braking device 13 remains inactive, since the contact surfaces 22 and 24, on the contrary, tend to move away.
    [0015] Referring to Figure 4, in a second step, when the fan rotor 3 tends to start forward, the two braking devices 12 and 13 are active.
    [0016] Indeed, the second device 13 has a low axial displacement d2, as noted above. It will therefore intervene very quickly as a stop preventing the shaft 2, and therefore the fan rotor 3, to continue its forward movement. Thus the two friction surfaces 22 and 24 come into contact, in particular at their transverse parts and brake the rotor 3. With regard to the first braking device 12, at the front of the bearing 9, the washer "Grower" 17 continuing to push the crosspiece 14, it follows the forward movement of the shaft 2 and the friction surfaces 18 and 20 remain in contact to brake the fan rotor 3.
    [0017] In addition, the shaft 2 is very quickly retained in its forward movement by the clearance d2 of the second braking device 13, which is small compared to the displacements d1 provided for the first device 12, the thrust of the washer " Grower »17 on the transverse part 14 induces a pressure along the axis XX of the shaft 2, which is exerted on the contact surfaces of the two braking devices 12 and 13. Indeed, the two contact surfaces 18 and 22 related to the fixed structure 7, respectively of the two braking devices 12, 13, are spaced apart from each other by the thrust of the washer "Grower" 17. In fact, the elastic thrust of the washer "Grower" 17 on the transverse part 14 keeps the shaft 2 in a middle position around the second bearing 9, by opposing thrusts transmitted to the two rings, 19 and 23, which surround it on the shaft. Having seen how the invention works, we can look at its effects on an accidental sequence, after the loss of a blade of the fan 1. With reference to FIG. 5, the curve 31 indicates the principle form of the level response. transverse dynamic forces exerted on the second bearing 9 by a fan rotor 3 in decoupled mode, when not braked. This curve has a maximum Nd for an ad regime of the fan rotor, which corresponds to the eigenfrequencies in decoupled mode. During an accidental sequence, the speed of the fan rotor 3 decreases from the speed Oc, corresponding to the cruising speed in normal operation, to a speed ni, corresponding to the autorotation of the fan rotor 3 for flight conditions to reach a runway to land. As mentioned above, the turbomachine is designed so that the speed ni is lower than the decoupled mode ad resonance regime. The forces Ni are therefore less than the maximum Nd. However, during the transient, the speed of the fan rotor passes through this resonance value ad and the bearing 9 is temporarily subjected to the maximum forces Nd. Curve 32 indicates the principle form of the same response in transverse dynamic force levels exerted on the second bearing 9 by a fan rotor 3 in decoupled mode, when it is braked by a device according to the invention. This curve is substantially the same as the previous one for the regimes distant from the regime ad corresponding to the proper response in decoupled mode. The first effect of the braking is to reduce the value c) 2 of the speed at which the autorotation of the fan rotor 3 stabilizes under the stabilized flight conditions after the accident. The dynamic forces increasing strongly with the small regimes with the regime, one sees that the braking makes it possible to strongly reduce the level N2 of these efforts in condition of stabilized flight after the accident compared to the value Ni obtained without braking.
    [0018] Furthermore, the comparison between the two response curves, 31 and 32, shows that the braking greatly reduces the maximum level of forces around the resonance regime ad. Braking therefore provides a second advantage which is to reduce by a significant value AN, the maximum level of dynamic forces observed during the phase of decay of the fan rotor speed 3 after the loss of a blade.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Turbomachine comprising a fixed structure (7), a rotor (3) for a fan (1), having an axis (XX) of rotation, and emergency braking means (12, 13) of the rotor (3), in particular in case of loss of a blade of the blower (1), characterized in that said means (12, 13) of emergency braking comprise a first (18) and a second (22) members carried by the fixed structure ( 7), said members (18, 22) being respectively configured to cooperate by friction with a first (20) complementary element of the rotor (3), forming a stop of the rotor (3) rearward along the axis (XX). ), and a second (24) complementary element of the rotor (3), forming a stop of the rotor (3) forwardly along the axis (XX), when the emergency braking means (12, 13) are active.
    [0002]
    2. Turbomachine according to the preceding claim, comprising at least a first bearing (5), mounted between the rotor (3) of a fan and a support member (8), said support member (8) being connected to the fixed structure ( 7) by a decoupling device (11) arranged to break in case of loss of a blade of the fan (1).
    [0003]
    3. A turbomachine according to the preceding claim, wherein at least one of said members (18) is released in translation relative to the fixed structure (7) along the axis of rotation (XX), in the opposite direction to that for which it forms a stop when the decoupling device (11) is broken.
    [0004]
    4. A turbomachine according to the preceding claim, further comprising means (17) configured to urge at least one of said members (18, 22) against the corresponding complementary element (20, 24) when said decoupling device (11). is broken.30
    [0005]
    5. Turbomachine according to the preceding claim, wherein at least one of said members (18) is integral with a part (14) connected to the fixed structure (7) by said decoupling device (11).
    [0006]
    6. The turbomachine according to the preceding claim, wherein the biasing means (17) comprises a spring means between the piece (14) for supporting said member (18) and the fixed structure (7).
    [0007]
    7. A turbomachine according to one of claims 3 to 6, wherein only the first member (18) is biased by means (17) for biasing, the second member (22) being mounted integral with the fixed structure (7).
    [0008]
    8. The turbomachine according to the preceding claim, comprising a normal operating configuration, especially before the loss of a fan blade (1), wherein the emergency braking means (12, 13) are inactive and configured so that that the spacing (dl) along the axis (XX) of rotation between the first member (18) and element (20) is greater than the spacing (d2) between the second member (22) and element (24) .
    [0009]
    9. A turbomachine according to one of the preceding claims, wherein the rotor (3) of the fan is centered and guided by at least one second bearing (9) mounted between the fixed structure (7) and the rotor (3), said second bearing (9) being located between said members (18, 22).
    [0010]
    10. Turbomachine according to one of the preceding claims, wherein the fan rotor (3) comprises a drive shaft (2) which supports at least one of said elements (20, 24).
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    同族专利:
    公开号 | 公开日
    US10001027B2|2018-06-19|
    GB2531162B|2020-08-12|
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    FR3026774B1|2020-07-17|
    GB2531162A|2016-04-13|
    GB201517103D0|2015-11-11|
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    FR2916483B1|2007-05-25|2013-03-01|Snecma|SYSTEM FOR DISSIPATING ENERGY IN THE EVENT OF TURBINE SHAFT BREAKAGE IN A GAS TURBINE ENGINE|
    FR2930760B1|2008-05-05|2010-09-10|Airbus France|APPARATUS FOR DISPLACING THE GROUND OF AN AIR TURBINE AIR VEHICLE|GB2550397B|2016-05-19|2018-11-21|Derwent Aviation Consulting Ltd|A turbo machine comprising a compressor system|
    US10422347B2|2017-02-10|2019-09-24|Asia Vital ComponentsCo., Ltd.|Braking structure for fan|
    FR3063310B1|2017-02-28|2019-04-26|Safran Aircraft Engines|AIRCRAFT ENGINE COMPRISING A BEARING BETWEEN TWO CONCENTRIC TREES|
    GB201704984D0|2017-03-29|2017-05-10|Rolls Royce Plc|Mitigation of effects of fan blade off in a gas turbine engine|
    FR3075864B1|2017-12-22|2019-11-15|Safran Aircraft Engines|TURBOMACHINE COMPRISING A TURBINE-DISCHARGING BLOWER THROUGH AN ELASTICALLY REMOVABLE CURVIC COUPLING|
    法律状态:
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    2016-04-08| PLSC| Search report ready|Effective date: 20160408 |
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    2018-06-29| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
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    优先权:
    申请号 | 申请日 | 专利标题
    FR1459595A|FR3026774B1|2014-10-07|2014-10-07|TURBOMACHINE COMPRISING A BLOWER ROTOR BRAKING DEVICE.|
    FR1459595|2014-10-07|FR1459595A| FR3026774B1|2014-10-07|2014-10-07|TURBOMACHINE COMPRISING A BLOWER ROTOR BRAKING DEVICE.|
    GB1517103.6A| GB2531162B|2014-10-07|2015-09-28|Turbo engine comprising a device for braking the fan rotor|
    US14/876,585| US10001027B2|2014-10-07|2015-10-06|Turbine engine comprising a device for braking the fan rotor|
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