• 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:
    rolling bearing for turbo-reactor of aircraft equipped with means of axial retention of its outer ring. the invention relates to a structure (40) for aircraft turbo-reactors and an associated assembly process, the structure comprising a rolling bearing (12a) comprising an outer ring (46), a bearing support (14a) , a ferrule (44) interposed between the ring and the support, means of connection of the ring on the support that integrates a fixing flange (50) mounted on the bearing support and flexible connection means (52) fixed on the ring and on the flange, the structure also comprising means that allow axial retention of the ring, in case of rupture of the flexible connection means, these means comprising first stop means that take the form of a plurality of pins (64) in pin housing holes (66) open in this ferrule (44) and capable of axially retaining this ferrule in relation to the support (14a), and second stop means (64) attached to the ferrule and capable of axially retaining the ring (46) in relation to this ferrule .
    公开号:BR112012030027B1
    申请号:R112012030027-0
    申请日:2011-05-31
    公开日:2020-09-24
    发明作者:Serge Louis Antunes；Michel Brault
    申请人:Snecma；
    IPC主号:
    专利说明:

    [0001] [001] The invention relates to the field of aircraft turbo-reactors, and, more particularly, to the means used in the middle of these turbo-reactors to cope with the imbalance caused by a loss of blower blade. This issue is addressed notably in EP 1 653 051, EP 1 916 431, FR 2 752 024 and FR 2 888 621. PREVIOUS TECHNICAL STATUS
    [0002] [002] The loss of one or more blower blades usually generates a strong imbalance on the blower rotor carrying the blades, this imbalance being able to endanger the integrity of the turbo-reactor structures. In order to face this problem and protect these structures, the practice of fusible zones on the path of resumption of radial efforts is known.
    [0003] [003] Indeed, for example, it is foreseen to make mechanical fuse connections between the outer ring of the two most ready bearing bearings of the blower rotor, and the turbo-reactor housing. These mechanical connections are dimensioned, in order to withstand the radial efforts in normal flight configuration, and to break in case of loss of at least one blower blade without consequence to the imbalance caused by that loss. This system is also known as a mechanical decoupling system.
    [0004] [004] As a result of these two ruptures, a single rolling bearing, over the three initially planned, continues to ensure the centering of the drive shaft. Considering that this single centering is insufficient to preserve the integrity of the turbo-reactor, the means of connection of the intermediate bearing on the crankcase contain a retaining part located radially in front of a complementary retaining part, provided on the crankcase and centered with the retaining part. Before the rupture of the fusible mechanical connections, this retaining part and the complementary retaining part remain at radial distance from each other, and are therefore not active. On the contrary, after the rupture of the fusible mechanical connections, according to a loss of the blower blade, the radially requested retaining part is foreseen to come into contact with the complementary retaining part, after having a relative movement in relation to it, under the combined effect of a precession movement of the blower rotor and contact with the complementary retaining part. When the retaining part and the complementary retaining part respectively take the form of two annular raceways, of different sizes, the relative movement of the retaining part is a bearing thereof over the complementary retaining part. During this bearing, the axis of rotation of the retaining part is therefore in motion in relation to the complementary retaining part, which remains attached to the housing.
    [0005] [005] The design as described above is designed to ensure mechanical decoupling as quickly as possible. Thus, it is done, for example, so that a duration of the millisecond order is not exceeded between the instant of the blower blade loss, and the instant of the rupture of the fusible mechanical connections.
    [0006] [006] During this duration, called decoupling time, the outer rings of the rolling bearings, in particular that of the bearing closest to the blower, are subjected to very high radial loads. These radial loads result in a consumption of the clearance between the outer ring and the cylindrical housing, in which it is arranged, this housing being generally defined by a ferrule, itself fixed in the bearing support, fusibly connected to the crankcase. turbo-reactor. Once the clearance is consumed, the outer ring of the bearing is provided with a relative movement in relation to the ferrule, under the combined effect of a precession movement of the blower rotor and contact with that same ferrule. More precisely, the relative movement of the outer ring is a bearing of it over the cylindrical housing of circular section defined by the ferrule. During this bearing, the shaft of the outer ring is therefore in motion in relation to the ferrule, which remains fixed in relation to the bearing support. But, above all, the bearing of the outer bearing ring on the ferrule leads to a relative tangential / circumferential displacement between these elements, capable of damaging the flexible connection means usually provided for between them.
    [0007] [007] A rupture in these flexible means of connection is therefore not to be excluded. However, in the event of rupture of these means, the outer bearing ring must be retained axially, in order to avoid the emission of waste. In addition, its axial retention allows the continuation of its bearing on the ferrule, until the moment of mechanical decoupling.
    [0008] [008] From the prior art, it is known to interpose axial retention means of the outer ring between the bearing support and the end upstream of the ring. Indeed, a plurality of shims can be provided mounted by bolts with nuts on a front end of the bearing support, and cooperating with a front end of the outer ring. This technical solution is criticized for the fact that it causes an important volume and global mass, notably due to the need to extend the outer bearing ring forward, in order to offer a stop surface to the shims supported by the bearing support. In effect, this forward ring extension is justified by the need for it to extend beyond the ferrule in which it is housed, in order to receive the stop blocks supported by the bearing support that surrounds the ferrule.
    [0009] [009] This extension towards the front of the outer bearing ring is sometimes even impossible to perform, due to volume problems in this area of the already dense turbo-reactor.
    [0010] [0010] There is certainly a possibility to reduce the axial dimension of the ferrule and the axial dimension of the part of the ring that ensures its accommodation in that ferrule, but this reduction could lead to a very small assembly mechanically. Furthermore, in the preferred case in which a damping system by annular oil film is provided between the ferrule and the outer ring, this would also reduce the axial dimension of that film again, and would therefore imply a low efficiency of the ring's damping bearing housing. EXPOSURE OF THE INVENTION
    [0011] [0011] The invention therefore has the purpose of at least partially preventing the aforementioned drawbacks relating to the prior art's achievements.
    [0012] - um mancal de rolamento que compreende um anel externo; - um suporte de mancal que envolve esse anel externo; - uma virola interposta entre o anel externo de mancal e o suporte de mancal; - meios de conexão do anel externo sobre o suporte de mancal, esses meios compreendendo: - um flange de fixação montado sobre o suporte de mancal; e - meios flexíveis de conexão fixados, por um lado, no anel externo de mancal, e, por outro, no flange de fixação;essa estrutura compreendendo, além disso, meios que permitem a retenção axial do anel externo de mancal, em caso de ruptura desses meios flexíveis de conexão,de acordo com a invenção, esses meios que permitem a retenção axial do anel externo compreendem: - primeiros meios de batente solidários à virola e capazes de reter axialmente essa virola em relação ao suporte de mancal, em caso de ruptura desses meios flexíveis de conexão; e - segundos meios de batente solidários à virola e capazes de reter axialmente o anel externo em relação a essa virola, em caso de ruptura desses meios flexíveis de conexão. [0012] For this purpose, the invention has as its object a structure for aircraft turbo-reactors, comprising: - a roller bearing comprising an outer ring; - a bearing support that surrounds this outer ring; - a ferrule interposed between the outer bearing ring and the bearing support; - means for connecting the outer ring to the bearing support, these means comprising: - a fixing flange mounted on the bearing support; and - flexible connection means fixed, on the one hand, to the outer bearing ring, and, on the other hand, to the fixing flange; this structure, furthermore, comprising means that allow axial retention of the outer bearing ring, in the event of rupture of these flexible connection means, according to the invention, these means which allow axial retention of the outer ring comprise: - first stop means attached to the ferrule and capable of axially retaining this ferrule in relation to the bearing support, in case of rupture of these flexible connection means; and - second stop means attached to the ferrule and capable of axially retaining the outer ring in relation to this ferrule, in case of rupture of these flexible connection means.
    [0013] [0013] Furthermore, these second stop means take the form of a plurality of pins spaced circumferentially from each other and each housed in an open pin housing orifice in that ferrule, these pins having a radially internal end which is located in a gutter open on that outer bearing ring equipped with a plurality of through radial through holes, opening into the bottom of that gutter, with these pins each being situated radially in relation to a full part of the bottom of that gutter.
    [0014] [0014] The invention is therefore notable in that it provides for axial retention of the outer ring through the ferrule. This leads globally to a decrease in the overall volume and mass of the structure in relation to the solution of the prior art described above, in particular due to a decrease in the axial length of the outer ring, which does not, however, weaken the mechanical assembly of the ring in the ferrule.
    [0015] [0015] In addition, as will be explained below, the radial passages allow for an easier assembly of the pins on the ferrule, while the full part of the gutter bottom prevents, in operation, the extraction of these pins radially inwards.
    [0016] [0016] Preferably, these first stop means take the form of a ferrule arranged axially between the bearing support and this fixing flange. This ferrule can be placed with or without clearance between the two elements specified, ensuring the limitation / interdiction of axial displacement in both directions.
    [0017] [0017] In this configuration, on the other hand, it is preferentially provided that this ferrule is provided with notches spaced circumferentially from each other, and cooperating with appendages attached to this bearing support, in order to limit / prevent the rotation of the ferrule in this bearing support.
    [0018] [0018] Preferably, these pins are each located radially in front of the fixing flange. This configuration also prevents, in operation, the extraction of these pins radially outwards.
    [0019] - inserção do anel externo de mancal na virola, de maneira a alinhar radialmente cada um dos orifícios de passagem abertos no anel com um orifício de alojamento de pino aberto na virola; - inserção dos pinos nos orifícios de alojamento de pino, pelos orifícios de passagem, de maneira a colocar a extremidade radialmente interna de cada pino na calha desse anel externo; - rotação do anel externo de mancal, de maneira que cada pino se situa diante radialmente da parte plena do fundo dessa calha;e - montagem do flange de fixação sobre o suporte de mancal. [0019] The invention also has as its object a process of assembling a structure for aircraft turbo-reactors defined above, comprising the following steps: - insertion of the external bearing ring in the ferrule, in order to radially align each of the through holes opened in the ring with an open pin housing hole in the ferrule; - insertion of the pins in the pin housing holes, through the through holes, in order to place the radially inner end of each pin in the groove of this outer ring; - rotation of the outer bearing ring, so that each pin is located radially in front of the full bottom part of this channel; and - mounting of the fixing flange on the bearing support.
    [0020] [0020] Finally, the invention also has as its object an aircraft turbo-reactor that comprises a structure, as described above.
    [0021] [0021] Other advantages and features of the invention will appear in the detailed non-limiting description below. BRIEF DESCRIPTION OF THE DRAWINGS
    [0022] - a figura 1 representa uma vista esquemática em corte longitudinal de uma parte de um turbo-reator, conforme um modo de realização preferido da presente invenção; - a figura 2 representa uma vista similar àquela da figura 1, com o turbo-reator achando-se em uma configuração tal como adotada após o desacoplamento mecânico dos mancais segundo a perda de uma lâmina de sopradora; - a figura 3 representa uma vista mais detalhada em corte de uma estrutura do turbo-reator mostrado nas figuras precedentes, essa estrutura compreendendo, em particular, o mancal de rolamento o mais próximo da sopradora, e apresentando-se sob a forma de um modo de realização preferido da invenção; - a figura 4 representa uma vista em corte feita ao longo da linha IV-IV da figura 3; - a figura 5 representa uma vista em corte feita ao longo da linha V-V da figura 3; - a figura 6 representa uma vista parcial em perspectiva de meios flexíveis de conexão entre o anel externo do mancal de rolamento da figura precedente, e o flange de fixação desse anel sobre o suporte de mancal; - as figuras 7a e 7b esquematizam o movimento do anel externo de mancal antes do desacoplamento mecânico dos mancais; e - as figuras 8a e 8b esquematizam etapas de um processo de montagem preferido da estrutura mostrada nas figuras precedentes. [0022] This description will be made with respect to the attached drawings, among which; figure 1 represents a schematic longitudinal sectional view of a part of a turbo-reactor, according to a preferred embodiment of the present invention; - figure 2 represents a view similar to that of figure 1, with the turbo-reactor being in a configuration as adopted after the mechanical decoupling of the bearings according to the loss of a blower blade; - figure 3 represents a more detailed cross-sectional view of a turbo-reactor structure shown in the preceding figures, that structure comprising, in particular, the rolling bearing closest to the blower, and in the form of a preferred embodiment of the invention; figure 4 represents a sectional view taken along line IV-IV in figure 3; figure 5 represents a sectional view taken along line VV in figure 3; figure 6 represents a partial perspective view of flexible means of connection between the outer ring of the bearing housing of the preceding figure, and the fixing flange of that ring on the bearing support; figures 7a and 7b show the movement of the outer bearing ring before mechanical decoupling of the bearings; and figures 8a and 8b outline steps in a preferred assembly process for the structure shown in the preceding figures.
    [0023] [0023] With reference to figure 1, a part of a turbo-reactor 1 for aircraft can be seen schematically, according to a preferred embodiment of the present invention.
    [0024] [0024] In a conventional way, this turbo-reactor 1 has a longitudinal axis 2 on which are centered a blower rotor 4 that holds blower blades 6, as well as a drive tree 8, solidary in rotation with rotor 4, also called a blower disk.
    [0025] [0025] The turbo-reactor 1 also includes a crankcase 10 that forms a fixed rigid envelope, this crankcase being represented very schematically in figure 1. To ensure the maintenance and orientation of the tree 8, three spaced roller bearings are provided of each other, according to the direction of axis 2, these bearings being referenced, respectively, from front to back, 12a, 12b and 12c.
    [0026] [0026] The outer ring of each of these three rolling bearings is fixed to the housing 10 by means of connection referenced 14a, 14b and 14c respectively. As shown in figure 1, these connection means each take the form of a bearing support, which forms an annular structure that connects the outer ring directly to the housing, or to an internal extension thereof, as is the case for the two front bearings 12a, 12b, located closest to the rotor 4.
    [0027] [0027] The furthest bearing 12a and the furthest bearing 12c are each designed to resume radial stresses, while intermediate bearing 12b is also designed to ensure axial retention of the shaft 8.
    [0028] [0028] Regarding the two front bearings 12a, 12b, their bearing supports 14a, 14b are each connected to the housing 10 by a fusible mechanical connection 16a, 16b. These connections are, for example, made with the aid of screws, whose number, dimension and whose position are retained in order to give the desired fuse character, which will be explained below.
    [0029] [0029] The bearing support 14b of the outer ring 18 of the intermediate bearing 12b, on the housing 10, furthermore, has the feature of comprising a retaining part 20 that forms an annular bearing track 22 centered on the axis 2. This annular track 22 is oriented radially outwards, and located radially in front of a complementary retaining part 24 provided on the housing 10. More precisely, that part 24 comprises a complementary bearing track 26, also annular and centered on the axis 2 In normal flight configuration, as shown in figure 1, runway 26 is therefore located around and at a distance from runway 22, so that they do not cooperate with each other. Thus, the retaining means constituted by the two parts 20, 24 remain inactive, since the raceways 22, 26 are at radial distance from each other, forming an annular clearance 34 that is substantially constant over the entire contour thereof.
    [0030] [0030] In this normal configuration, the mechanical fuse connections 16a, 16b are sufficiently resistant to withstand the radial forces transmitted by the front bearings 12a, 12b, serving to maintain the rotation of the shaft 8, along the longitudinal axis 2 of the turbo-reactor.
    [0031] [0031] An exceptional problem case, leading to the loss of one or more blower blades 6, the rotor 4 suffers a disturbance that causes extremely high radial stresses in the turbo-reactor structures, and in particular in the bearing supports 14a , 14b and 14c.
    [0032] [0032] As previously mentioned, the two fusible mechanical connections 16, 16b are designed to break, when the supports 14a, 14b are subjected to these extremely high radial forces, of predetermined magnitude. With reference to figure 2, the almost immediate consequence of these ruptures resides in the radial bending of the tree 8 that sustains the rotor 4 which suffers an imbalance, this bouncing causing the raceway 22 to also move radially with the support 14b, until it comes into contact contact with the complementary raceway 26, after consumption of the radial clearance 34. A point contact 36 is then established between the two raceways 22, 26 initially separated from each other, as shown in figure 4.
    [0033] [0033] Once the contact is established, the radial bending of the tree 8 is stopped. This tree then undergoes, in a manner known to the technician, a precession movement during which it continues to turn on itself, and also rotates around the longitudinal axis 2 of which it remains angularly out of phase. In relation to this, it is necessary that the rear bearing 12c continues to orient and center this tree 8 on the axis 2 punctually.
    [0034] [0034] The precession movement of the tree 8 and its rotor 4, combined with the contact of the retaining parts 20, 24, causes the retaining part 20 to be provided with a relative movement in relation to the complementary retaining part 24.
    [0035] [0035] This relative movement is a bearing, usually without sliding due to the very high contact forces, of track 22 over fixed track 26 of a larger diameter.
    [0036] [0036] The design as described above is designed to ensure mechanical decoupling as fast as possible. Thus, it is done, for example, in such a way that a duration of the millisecond order is not exceeded between the instant of the blower blade loss 6, and the rupture of the fuse mechanical connections 16a, 16b.
    [0037] [0037] The invention aims more particularly to limit the risks of damage to the turbo-reactor before mechanical decoupling, as will be detailed here. In effect, during the decoupling time, the outer rings of the two front bearing bearings, in particular that of the bearing 12a closest to the blower, are subjected to very high radial loads.
    [0038] [0038] With reference at the moment to figures 3 to 6, there is a structure 40 of the turbo-reactor, whose core is constituted by the front bearing 12a. This structure 40 also includes the annular bearing support 14a, defining a perforation 42 centered on the axis 2. This perforation tightly houses the ferrule 44 in the form of a sleeve or metal ring centered on the axis 2, which defines itself a perforation 45 in which the outer ring 46 of the bearing 12a is housed. The ferrule 44 is therefore interposed radially between the perforation 42 of the support 14a and the ring 46, which internally supports the bearing cylinders 48.
    [0039] [0039] The outer ring 46 bears two annular joints or metal segments 47 axially spaced from each other, and each establishing a watertight connection with the hole 45 defined by the ferrule 44. Among these joints 47, preferably made of cast iron , an annular joint is provided between the outer surface of the ring 46 and the perforation 45, that gap being filled with oil, in order to form a film of annular oil 49 which constitutes a damping system. This system, also called "Squeeze Film", allows, in effect, to dampen the vibrations of ring 46, essentially in the radial direction. As an indication, the oil is fed classically through port 61 shown in figure 3.
    [0040] [0040] Means of connection are provided between the ring 46 and the support 14a. These means initially comprise a fixing flange 50 centered on the axis 2 and mounted, screwed on a lower flank of the support 14a. This flange 50 is then disposed radially in front of and at a distance from the rear end of the outer ring 46. For its connection, flexible means are provided, for example, which take the form of a plurality of fasteners 52 spaced circumferentially from each other, as shown in figures 3 and 6. Each of these fasteners 52, for example U-shaped and adjusted in a radial plane, has two side branches connected by a base at the level of its rear end, and whose two front ends are respectively fixed on the flange 50 and on the rear end of the ring 46, preferably by welding. These fasteners 52 allow radial folding of the ring 46 in the hole 45, ensuring the damping of the bearing 12 by the oil film 49.
    [0041] [0041] At its rear end 44 it is provided with a ferrule 54 which extends radially outwards and defining notches 56 spaced circumferentially from each other. These notches 56, radially open to the outside, each house an appendix 58, forming an axial backward protrusion, starting from the lower flank of the bearing support 14a, to which these appendages 58 are attached. The mechanical connection provided by the cooperation between the grooves 56 and the appendages 58, as shown in figure 4, prevents / limits rotation, along the axis 2 of the ferrule 44 in the perforation 42 of the support 14a.
    [0042] [0042] Figure 3 shows that the toothed ferrule 54 is housed axially between the lower flank of the support 14a, and an annular axial stop surface 60 practiced on the flange 50, with the aid of a flange. This axial tightening of the ferrule 54, carried out with or without play, allows the ferrule to be axially retained in relation to the support 14a and the flange 50, in both directions of the axial direction. The ferrule 54 therefore forms first stop means integral with the ferrule, capable, in particular, of axially retaining this ferrule 44 in relation to the bearing support 14a, in case of rupture of the fasteners 52.
    [0043] [0043] The ferrule 44 also comprises an annular rear extension 62 equipped with pins 64 spaced circumferentially from each other. As shown in figures 3 and 5, each pin 64 is housed in a housing hole 66 opened over extension 62. The assembly is done in any way deemed appropriate for the technician, for example, by force or by screwing.
    [0044] [0044] Each pin 64 is oriented radially, with its radially internal end housed in a rail 68 open over the rear end of ring 46, being opened radially outwards. As best seen in figure 5, it is noted that the radially inner end of each pin 64 is located radially in front of a full part 70 of the trough bottom. This gutter bottom is not, in effect, filled over its entire annular contour, since the filled part is interrupted by the presence of a plurality of radial through holes 72 that pass through the ring 46. These holes 72 are circumferentially spaced from each other and thus opening each one at the bottom of the channel, between two parts of the full part 70, allow the assembly of the pins 64, as will be explained below.
    [0045] [0045] In addition, the radially outer end of each pin 64 is located radially in front of the fixing flange 50. Thus, the pins 64 regularly arranged around the axis 5 are trapped in both directions in the radial direction, which prevents their loss in case of rupture of its connection with the annular extension 62.
    [0046] [0046] The pins 64, contained with or in play between the two lateral flanks of the rail 68 centered on the axis 2, allow axially to retain the annular extension of ferrule 62 in relation to the outer ring of bearing 46, in both directions of the axial direction . These pins 64 therefore form second stop means integral with the ferrule, capable, in particular, of axially retaining the outer bearing ring 46 with respect to this ferrule 44, in the event of failure of the fasteners 52.
    [0047] [0047] Figures 7a and 7b show schematically the movement of the outer bearing ring 46 before mechanical decoupling of the bearings, and after the loss of the blower blade, during the decoupling time. In these figures, it is shown that during the rolling of the outer ring 46 over the hole in the ferrule 45, a relative tangential / circumferential displacement between these two elements is simultaneously created, as evidenced by the evolution of the relative positions between the two crosses 76, respectively symbolizing two any points on the ferrule and ring. This tangential / circumferential relative displacement causes an agreement in circumferential pressure of the flexible connection fasteners 52, which can therefore be damaged, until eventually breaking.
    [0048] [0048] When this accidental rupture of the flexible fasteners 52, the outer ring 46 of the front bearing is no longer axially retained by these damaged fasteners, but the relay is secured by the first and second stop means needed, capable, in combination, of ensuring the axial retention of the ring 46e of the bearing assembly 12a, in relation to the bearing support 14a.
    [0049] [0049] As an indication, it is noted that the location of this rupture of the fasteners 52 can be predetermined, for example at the level of a reduced section part. This location is chosen so that, after rupture, the pins 64 continue to be held radially by the rear end of the ring 46, and by the fixing flange 50.
    [0050] [0050] Thanks to this auxiliary axial retention, the outer ring 46 can continue to roll over the ferrule perforation 45 until the moment of mechanical decoupling of the bearings, from which that ring 46 is no longer requested radially, and does not run more risk of being damaged. In fact, after the mechanical decoupling of the bearings, the radial forces essentially pass through the intermediate bearing 12b, as described above with reference to figure 2.
    [0051] [0051] Figures 8a and 8b outline a process for assembling the structure 40 shown in figures 3 to 7b.
    [0052] [0052] Initially, the ferrule 44 is mounted tightly on the perforation 42 of the support 14a. The relative angular position between the two elements is chosen, so that, at the end of assembly, the appendages 58 are housed in the grooves 56 of the ferrule 54.
    [0053] [0053] Then, the outer bearing ring 46 is inserted in the hole in the ferrule 45, by axial relative displacement between these two elements. This insertion is carried out, in order to radially align each of the through holes 72 opened in the ring 46 with a pin housing hole 66 opened in the ferrule, as shown in figure 8a. In the same figure, the next step was represented, which consists of inserting the pins 64 in the holes of pin housing 66, passing through the holes 72. Each pin 64, therefore, radially outwards a hole 72, until it is kept in its associated housing orifice 66. In its final position, pin 64 has its radially internal end housed in channel 68 of the outer ring, and is completely extracted from the orifice 72 that it has passed through.
    [0054] [0054] Then, as shown in figure 8b, the rotation of the outer ring 46 is preceded, so that each pin 64 is located radially in front of the full part 70 of the bottom of the rail. Thus, instead of being radially in front of the through holes 72, the pins 64 are in front of the full part 70, forming a radial stop inwards. The rotation of the ring 46 therefore resembles a pin locking operation 64.
    [0055] [0055] Finally, the mounting flange 50 is mounted on the bearing support 14a, by screwing with nut.
    [0056] [0056] It is necessary that assembly is performed, so that each pin 64 is located, according to the tangential / circumferential direction, between two fasteners 52. This allows to ensure a better control of the presence of these pins, for example with the aid of a shim to be inserted axially between the flange 50 and the ring 46, from a tangential space delimited between the two fasteners 52, easily accessible to the operator.
    [0057] [0057] Of course, several modifications can be made by the technician to the invention that has just been described, solely by way of non-limiting examples.
    权利要求:
    Claims (7)
    [0001]
    Structure (40) for aircraft turbo-reactors, comprising: - a roller bearing (12a) comprising an outer ring (46); - a bearing support (14a) that surrounds this outer ring; - a ferrule (44) interposed between the outer bearing ring and the bearing support; - means for connecting the outer ring to the bearing support, these means comprising: - a fixing flange (50) mounted on the bearing support; and - flexible connection means (52) fixed, on the one hand, to the outer bearing ring, and, on the other hand, to the fixing flange; this structure, furthermore, comprising means that allow axial retention of the outer bearing ring, in the event of rupture of these flexible connection means, characterized by the fact that those means that allow axial retention of the outer ring include: - first stop means (54) attached to the ferrule (44) and capable of axially retaining this ferrule in relation to the bearing support (14a) in case of rupture of these flexible connection means (52); and - second stop means (64) attached to the ferrule (44) and capable of axially retaining the outer ring (46) in relation to this ferrule, in case of rupture of these flexible connection means, these second stop means taking the form of a plurality of pins (64) spaced circumferentially from each other and each housed in a pin housing orifice (66) opened in this ferrule (44), these pins (64) having an end radially internal which is located in a gutter (68) open on that outer bearing ring (46) equipped with a plurality of through radial through holes (72), ending at the bottom of that gutter (68), with these pins (64) each one being in radial relation to a full part (70) of the bottom of that channel.
    [0002]
    Structure, according to claim 1, characterized by the fact that these pins (64) are each located radially in front of the fixing ring (50).
    [0003]
    Structure according to claim 1 or 2, characterized in that these flexible means of connection take the form of a plurality of pins (52) spaced circumferentially from each other, each presenting a U-shape arranged in a radial plane.
    [0004]
    Structure according to any one of the preceding claims, characterized in that these first stop means take the form of a ferrule (54) adjusted axially between the bearing support (14a) and this fixing flange (50).
    [0005]
    Structure, according to claim 4, characterized by the fact that this ferrule (54) is provided with notches (56) spaced circumferentially from each other, and that cooperate with appendages (58) attached to this bearing support (14a), the in order to limit / prevent the rotation of the ferrule in relation to this bearing support.
    [0006]
    Process for assembling a structure (40) for aircraft turbo-reactors, as defined in any of the preceding claims, characterized by the fact that it comprises the following steps: - insertion of the outer bearing ring (46) in the ferrule, in order to radially align each of the through holes (72) opened in the ring with a pin housing hole (66) opened in the ferrule (44); - insertion of the pins (64) in the pin housing holes (66), through the through holes (72), in order to place the radially inner end of each pin (64) in the groove (68) of that outer ring; - rotation of the outer bearing ring (46), so that each pin (64) is located radially in front of the full part (70) of the bottom of this channel; and - mounting the fixing flange (50) on the bearing support (14a).
    [0007]
    Aircraft turbo-reactor (1), characterized by the fact that it comprises a structure (40), as defined in any one of claims 1 to 5.
    类似技术:
    公开号 | 公开日 | 专利标题
    BR112012030027B1|2020-09-24|AIRCRAFT TURBO-REACTOR STRUCTURE, AIRCRAFT STRUCTURE AND ASSEMBLY PROCESS
    BR112013008391B1|2020-08-25|aircraft engine and connection box between an aircraft engine fan drive tree and a rolling bearing
    BRPI0803674B1|2020-09-29|FAN FOR AIRCRAFT TURBOMACH AND AIRCRAFT TURBOMACH
    BR112013025372B1|2021-05-25|process of assembling an aircraft engine on a pillar
    BRPI0500246B1|2017-02-21|turbojet
    BRPI0500271B1|2015-06-23|Turbojet engine
    EP1022438B1|2005-05-11|Method and apparatus for supporting a rotatable shaft within a gas turbine engine
    BRPI0922745B1|2020-03-31|FAN FOR AIRCRAFT TURBOMACH AND AIRCRAFT TURBOMACH
    US8262353B2|2012-09-11|Decoupler system for rotor assemblies
    JP6464168B2|2019-02-06|Apparatus for centering and guiding the rotation of a turbine engine shaft including improved means for retaining an outer bearing ring
    BR102014016599A2|2015-11-24|torque support of an engine and bearing of a torque support
    JPH0783237A|1995-03-28|Bearing mechanism of shaft
    BR112014000600B1|2021-06-22|WIND TURBINE ROTOR, WIND TURBINE AND METHOD FOR MANUFACTURING A PITCH BEARING FOR A WIND TURBINE ROTOR
    US9359073B2|2016-06-07|Aircraft tail rotor system
    BRPI0914718B1|2019-11-26|axial-centrifugal compressor
    BR112013026763B1|2021-06-15|WHEEL WITH TURBOMACHINE BLADE, E, WHEEL ASSEMBLY AND BALANCE PROCESS
    BR112013031379A2|2020-05-19|osteosynthesis device with plate and pins
    ES2415505T3|2013-07-25|An electric machine and a procedure for mounting it
    BR112013017741B1|2021-03-23|FAN ROTOR AND ASSOCIATED TURBORREATOR
    BRPI1102297A2|2012-11-20|generator with a segmented stator
    ES2774507T3|2020-07-21|Planetary gear for a wind turbine with slidably supported planetary wheels
    BR112013015196B1|2020-12-22|suspension device of a turbo-reactor
    BRPI0924900B1|2019-01-22|bearing assembly and electric motor
    CN103998773A|2014-08-20|Locking device for wind turbines
    BR112014001381B1|2021-07-20|TURBOMACHINE BLADE WHEEL AND WHEEL ASSEMBLY AND BALANCE PROCESS
    同族专利:
    公开号 | 公开日
    EP2576997B1|2016-07-20|
    JP2013528742A|2013-07-11|
    RU2012157717A|2014-07-20|
    EP2576997A1|2013-04-10|
    RU2559953C2|2015-08-20|
    JP5816274B2|2015-11-18|
    WO2011151592A1|2011-12-08|
    US20130156574A1|2013-06-20|
    CA2800986C|2017-09-12|
    CN102939437A|2013-02-20|
    FR2960907A1|2011-12-09|
    CN102939437B|2015-01-21|
    FR2960907B1|2012-07-27|
    BR112012030027A2|2016-08-02|
    CA2800986A1|2011-12-08|
    US9341079B2|2016-05-17|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2484574B1|1980-06-13|1982-06-18|Snecma|
    FR2752024B1|1996-08-01|1998-09-04|Snecma|SHAFT SUPPORT BREAKING AT THE APPEARANCE OF A BALOURD|
    US5813214A|1997-01-03|1998-09-29|General Electric Company|Bearing lubrication configuration in a turbine engine|
    US6240719B1|1998-12-09|2001-06-05|General Electric Company|Fan decoupler system for a gas turbine engine|
    US6491497B1|2000-09-22|2002-12-10|General Electric Company|Method and apparatus for supporting rotor assemblies during unbalances|
    US6413046B1|2001-01-26|2002-07-02|General Electric Company|Method and apparatus for centering rotor assembly damper bearings|
    US6540483B2|2001-08-27|2003-04-01|General Electric Company|Methods and apparatus for bearing outer race axial retention|
    FR2866069A1|2004-02-06|2005-08-12|Snecma Moteurs|SOLIDARITY BLOWER TURBOREACTOR OF A DRIVE SHAFT SUPPORTED BY A FIRST AND A SECOND BEARING|
    RU2265728C1|2004-04-29|2005-12-10|Открытое акционерное общество "Научно-производственное объединение "Сатурн" |Turbomachine rotor thrust-damper support|
    US7384199B2|2004-08-27|2008-06-10|General Electric Company|Apparatus for centering rotor assembly bearings|
    FR2877046B1|2004-10-26|2010-09-24|Snecma Moteurs|TURBOMACHINE WITH DECOUPLING DEVICE AND FUSE SCREW FOR TURBOMACHINE DECOUPLING DEVICE|
    FR2888621B1|2005-07-15|2007-10-05|Snecma|DEVICE FOR RETENTION OF A BEARING SUPPORT IN A TURBOMACHINE COMPRISING A DECOUPLING DEVICE|
    FR2907861B1|2006-10-26|2008-12-26|Snecma Sa|BEARING ARRANGEMENT OF A ROTATING SHAFT AND TURBOREACTOR EQUIPPED WITH SUCH AN ARRANGEMENT|
    FR2908153B1|2006-11-07|2011-05-13|Snecma|DEVICE FOR HITCHING A DISTRIBUTOR OF A TURBINE, TURBINE COMPRISING THEM, AND AN AIRCRAFT ENGINE WHICH IS EQUIPPED|
    US8182156B2|2008-07-31|2012-05-22|General Electric Company|Nested bearing cages|CA2870683C|2012-04-25|2017-03-28|General Electric Company|Apparatus and method for assembling a damper bearing assembly|
    DE102012208744A1|2012-05-24|2013-11-28|Schaeffler Technologies AG & Co. KG|roller bearing|
    JP6056074B2|2012-08-28|2017-01-11|学校法人福岡大学|Forward / reverse fine rotation bearing|
    CN103101628B|2013-02-06|2015-05-27|中国商用飞机有限责任公司|Front installation joint integrated with airplane hang|
    CN103112595B|2013-02-06|2016-01-27|中国商用飞机有限责任公司|The hanging structure of Propulsion Integrated|
    FR3013760B1|2013-11-26|2015-12-25|Snecma|DEVICE FOR THE CENTERING AND ROTATION GUIDING OF A TURBOMACHINE SHAFT COMPRISING IMPROVED MEANS FOR RETAINING EXTERNAL BEARING RING|
    PL406855A1|2014-01-15|2015-07-20|General Electric Company|An unit immobilizing a bearing and method for assembling it|
    CN105443587A|2014-08-29|2016-03-30|中航商用航空发动机有限责任公司|Integrated bearing supporting structure used for aviation engine|
    DE102014220317A1|2014-10-07|2016-04-07|Rolls-Royce Deutschland Ltd & Co Kg|Aircraft gas turbine engine with shock absorbing element for fan blade loss|
    FR3042215B1|2015-10-13|2019-09-13|Safran Aircraft Engines|STRUCTURE FOR TURBOMACHINE COMPRISING AXIAL RETAINING ROLLS FOR EXTERIOR BEARING BEARING BEARING|
    FR3066550B1|2017-05-18|2019-07-12|Safran Aircraft Engines|DEVICE FOR THE CENTERING AND ROTATION GUIDING OF A TURBOMACHINE TREE COMPRISING AXIAL RETAINING RINGS OF EXTERNAL BEARING RING|
    US10480572B2|2018-04-18|2019-11-19|United Technologies Corporation|Bearing centering spring and damper|
    US10415638B1|2018-04-18|2019-09-17|United Technologies Corporation|Bearing centering spring and damper|
    FR3086020B1|2018-09-13|2020-12-25|Safran Aircraft Engines|AXIAL RETAINING SYSTEM OF A BEARING BUSH|
    FR3088672B1|2018-11-16|2020-12-18|Safran Aircraft Engines|DEVICE FOR CENTERING AND GUIDING IN ROTATION OF A ROTATING PART WITH INTERLACED ARMS|
    FR3089547B1|2018-12-06|2021-04-02|Safran Aircraft Engines|Improved bearing support|
    FR3095481B1|2019-04-25|2021-05-21|Safran Aircraft Engines|Double row angular contact ball bearing comprising emergency axial retention means integrated into the bearing|
    法律状态:
    2018-12-26| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|
    2019-11-12| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|
    2020-06-30| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|
    2020-09-24| B16A| Patent or certificate of addition of invention granted|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 31/05/2011, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1054283A|FR2960907B1|2010-06-02|2010-06-02|BEARING BEARING FOR AIRCRAFT TURBOJET ENGINE WITH IMPROVED AXIAL RETENTION MEANS FOR ITS OUTER RING|
    FR1054283|2010-06-02|
    PCT/FR2011/051244|WO2011151592A1|2010-06-02|2011-05-31|Antifriction bearing for an aircraft jet engine provided with a means for axially holding the outer ring thereof|
    [返回顶部]