• 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:
    A turbomachine bearing assembly is provided, comprising a shaft (1) provided with a sleeve (13) which has an external surface located, radially to the axis of the shaft, at a first distance d1 from this axis, a oil enclosure (8), a seal (9) bearing against the sleeve of the shaft. A nozzle (19) arranged to project oil towards the drive shaft, in the oil chamber, is mounted so that its free end is located, radially to the axis, at a second distance d2 greater than the first distance d1.
    公开号:FR3036441A1
    申请号:FR1554596
    申请日:2015-05-22
    公开日:2016-11-25
    发明作者:Boris Briantais；Gerard Philippe Gauthier；Laurent Gille；Serge Rene Morreale
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to the field of turbomachines, in particular that of gas turbine engines intended for the propulsion of aircraft. The invention relates to the mounting of a rotating shaft of the turbomachine and the control of the lubrication in order to ensure that the shaft a good rotation. Thus, a turbomachine bearing assembly is firstly concerned, comprising: a shaft rotating around an axis and of which a sleeve which surrounds it locally and which has an external surface located radially to the axis, with a first distance from this axis, - at least one bearing supporting the rotating shaft, - a housing in which is disposed the shaft, - a partition separating an air chamber and an oil chamber, - a seal radial contact arranged between the wall and the sleeve of the shaft which rotate relative to each other. It will be understood that in the present description, the radial and axial terms are to be considered with reference to the axis (LL below) of the aforementioned rotating shaft. An aircraft turbomachine generally comprises, upstream to downstream in the direction of the gas flow, a fan, one or more compressor stages, a combustion chamber, one or more turbine stages and an exhaust nozzle. gas. Rotors, which can be coupled together by different transmission and gear systems, correspond to these different elements. Furthermore, in order to allow lubrication and cooling of the guide bearings of the rotating bodies, in particular rotating shafts, the turbomachine conventionally comprises a lubrication circuit. The lubrication circuit of a bearing comprises a lubrication chamber, or oil chamber, which can be formed by a part of the inner casing of the turbomachine (fixed structure of the engine) surrounding a portion of rotor, of part and of other of the landing. Sealing means are provided in the areas where the fixed and movable parts meet. These means, which include seals, should allow the oil to be retained as much as possible within the oil enclosure. However, during assembly of the rotating shaft, which is generally from downstream to upstream, the seals can be damaged, especially when the shaft, not properly aligned, meets the housing in which it is mounted. In addition, mounted shaft, at least some joints are no longer accessible; we no longer make a visual check of their state. In addition, the quality of the lubrication also depends on the conditions in which the jet of oil is dispersed in the oil chamber. And if a means of supply from outside the enclosure is used, it should be made compatible with the installation of the rotating shaft, in particular if, as here, this rotating shaft is secured locally, in a said oil chamber, a sleeve which surrounds it and against the outer surface of which a seal is mounted. In addition this seal, which is therefore in radial contact, between two parts rotating relative to each other, if it requires only a slight difference in pressure between the air chamber and the outside, limiting the air consumption to pressurize this chamber (lower pressure to the rest of the environment), however requires cooling to remain effective. The invention aims to promote this.
    [0002] To this end, it proposes that there is provided a nozzle arranged to project oil to the drive shaft, in the oil chamber where the nozzle extends to a free end, which is located, radially to the axis at a second distance from this axis, the second distance being greater than the first distance.
    [0003] Occupying such a radially external position vis-à-vis the rotating shaft surrounded by its sleeve, the nozzle will not interfere with the axial passage of this shaft, while ensuring a favorable dispersion of the oil within the oil enclosure. Note also that the sleeve will favorably present an internal cavity. This will further promote efficient cooling of the seal. Indeed, the nozzle will then send oil into this cavity of the sleeve, to cool the sleeve and the seal, closer to the heating zone. Regarding further the mounting of the nozzle, it is advisable that is provided, at a radial distance from the upper axis to the second distance, a bearing support part of the bearing connected to the housing, this support piece having a passage through which will pass the nozzle, which will be attached to the housing. Thus, it will be possible to ensure proper installation of the nozzle, while securing its fixing, including if, for a good drive in 15 rotation of the shaft and avoid critical modes of vibration, it is expected to make said support piece the bearing in the form of a flexible cage with small columns, and therefore generally axial slots between these columns. Indeed one of these slots can be used as space to pass the jet. In addition, fixing the nozzle to the casing, radially beyond this support piece, will ensure a certain length of guiding the oil, pledge of jet quality preferably rectilinear, not dispersed, even at high pressure and high temperature, and all the more so if radially the nozzle passes through the wall of the oil chamber. With regard to this mounting of the shaft and the nozzle, it is furthermore recommended: - that before mounting the rotating shaft, the nozzle is placed in the oil chamber and positioned therein that, radially to the axis, it extends exclusively beyond said first distance, - then then we pass, in the chamber, opposite the nozzle and substantially parallel to its axis of rotation, shaft integral with the sleeve.
    [0004] 3036441 4 Thus, axial assembly and disassembly of the shaft will be facilitated, without altering the quality of the oil diffusion in the oil chamber, via the nozzle. A corollary problem taken into account relates precisely to the dispersion of the oil in the oil chamber. Indeed, the oil jets typically project an oil jet according to a kind of a dispersion cone. However, in some cases, this cone may be very wide. There is then a risk that high velocity oil particles will be projected toward the seal, especially if it is located around the shaft sleeve of the rotating shaft. Particles of high energy oil can then leak from the oil chamber, especially since the gasket provided here can operate with very low pressurization. There is therefore a risk of significantly increasing the oil consumption of the engine. In fact, there will be in the oil chamber a rotating oil mist and air leaking slightly sealing from the outside to the vacuum enclosure. In this oil chamber the nozzles also project, with high energy or speed, oil jets which, if they are directed directly towards the seals, can pass through them despite a flow of air that can pass in the opposite direction: depression is of the order of the millibar, 20 while the oil arrives in the enclosure in overpressure of the order of the bar. The oil in suspension in the fog is also in contact with the joints. However, as its energy is less, it is normally discharged by said air flow and by the protective tendrils, if the seals are, as preferred, equipped with de-oiling spins 25 arranged on axial flanges and arranged opposite the outer surface of the sleeve of the rotating shaft. In addition, if the nozzle sends oil into a cavity of the sleeve, as close as possible to the heating zone, it is recommended to avoid any direct jet towards the joint which would have the effect of drowning it and letting it pass. 30 oil outside the enclosure.
    [0005] As a solution to these problems or goals to be achieved, and in connection with the above, it is proposed that a cowling is arranged around the nozzle, so to protect the seal of a direct projection of oil, the cowling extending radially inward to a distance greater than the first distance. Thus, while satisfying a mounting requirement that prevents the nozzle from being placed radially at the sleeve, and in particular its cavity if provided with it, this cavity can be aimed without aiming at the radial contact seal.
    [0006] By dispersing and differently directing a portion of the jets from the nozzle relative to another uncovered portion, an even greater decrease in some leaks and oil consumption in the enclosure concerned are further provided. And even more if the cowling is shaped to flare towards the free end of the nozzle, there will be an economical solution, with a conventional nozzle: - projecting oil in a cone wide enough for the intended application, and having manufacturing characteristics similar to that feeding the bearing nearby, the hood being a simple solution to have a jet quality easily reproducible despite the hazards of manufacture. The hood solution also avoids premature degradation of the seal or clogging thereof (coking of the oil at the seal located in high temperature areas, because of friction in the seal ).
    [0007] It is therefore advisable that, since the nozzle comprises oil outlet channels in the oil chamber, the cowling covers only the channel (s) which direct (s) directly towards the seal and / or the sleeve the (s) outgoing oil jets (s). Preferably, the assembly will be carried out as follows: before mounting the rotating shaft provided with its sleeve, and after positioning the nozzle in the oil chamber: - the cowling is positioned so that in the oil enclosure it extends, radially inward, to a distance greater than the first distance, and thus will fix the cowling at the nozzle, arranging it around the oil outlet orifices of said nozzle . Certainly, it will take a tool to fix the cowling. But, in this way, it will be exempted from the passage through the support part of the bearing and it may be sufficient to a ring to fix the cowling nozzle. Note also that the solution of the cowling is particularly adapted to the favorable case where: the sleeve comprises a branch substantially parallel to the axis, which defines between it and the shaft an interior space open downstream and which presents said outer surface, - the seal is disposed around the outer surface of said leg, - and the cowling is disposed around the nozzle to protect said seal from a direct projection of oil exiting the nozzle. Indeed, it will then be possible, by the cowling, to break the jet high speed towards the seal seal. The nozzle will then send high velocity particles only in the direction of the sleeve, under the seal to be cooled. It should also be noted that, all the more with the roll-over solution, it will be possible to retain the preferred use of a seal provided with a de-oiling auger, thus provided on an axial flange and disposed opposite the outer surface of the sleeve of the rotating shaft. Indeed, if, to provide a seal protection, such a spin is adapted to repel droplets suspended in an oil mist, direct oil jets would drown. Other details, characteristics and advantages of the solutions presented here will become apparent upon reading the description which will now follow, given by way of nonlimiting example with reference to the accompanying drawings, in which: FIG. 1 shows schematically in longitudinal local section (LL axis) an inner part of an operational aerospace turbine engine, while the rotating shaft (1 below) is mounted; FIG. 2 is an identical view, while the rotating shaft is being mounted (the arrow indicates the axis and the mounting direction), FIG. 3 shows an enlarged detail of FIG. 1, with the cowling. mounted around the free end of the nozzle, and FIG. 4 shows an enlarged detail of FIG. 3, with the nozzle and its cowling mounted around the shaft and its sleeve. FIG. 1 shows a turbomachine shaft 1 rotatable about an axis LL, installed, in the operating position, in a casing 2, at a bearing 3 for guiding the shaft 1 in the turbomachine.
    [0008] In FIG. 1 and following, the main flow of the gases in the turbomachine goes from the upstream (AM) to the downstream (AV). The elements represented in the example corresponding to the figures are in a part of the turbomachine surrounded by this main flow. In the remainder of the description, the terms upstream and downstream refer to this main flow. The guide bearing 3 is formed in particular by an outer ring 4, fixed to the casing 2, and an inner ring 5, fixed to the shaft 1, between which rollers 6 can roll freely. The bearing 3 is designed such that the rollers 6 remain held in the inner ring 5 when the shaft 1 is moved out of its operating position for assembly or disassembly operations. Other bearings than the rollers, for example balls, can be used. It is also conceivable to design a bearing 3 where the bearings 6 are held on the side of the outer ring 4 when the rotary shaft 1 is disassembled (not shown).
    [0009] The outer ring 4 is connected to the casing 2 by a support bearing part 7 of the bearing 3. The inner ring 5 is generally fixed to the surface of the rotary shaft 1. The casing 2 and the rotary shaft 1 are arranged to form a chamber 8 for lubrication 4 around the bearing 3. This enclosure 8 comprises a passage of the shaft 1 upstream of the bearing 3 and a passage of the shaft 1 downstream of the bearing 3. The enclosure 8 lubrication , or oil chamber, is part of the lubrication circuit of the turbomachine.
    [0010] The oil enters the chamber 8 via an inlet (dispersing orifices of the nozzle 19 below) and is then directed towards the bearing 3 to lubricate it. The oil having lubricated the bearing 3 comes out being projected in different directions. The purpose of the enclosure 8 is to recover this oil so that it goes back through an outlet orifice, not shown in the figure, so as to return it to the lubrication circuit. To prevent oil losses, the passages of the shaft 1 in the chamber 8 are equipped with seals, or radial means, sealing 9, 10, especially able to block the oil. Moreover, in particular with a view to improving the tightness of these radial sealing means 9, 10, during the rotation of the shaft 1, the element is designed so that the pressure PO of the enclosure 8 is less than the pressures P1, P2, which are outside the passages of the shaft 1, when the turbomachine is operating. This depressurization contributes to the sealing of the enclosure 8. In order to obtain this result, the radial sealing means 9 of the upstream passageway here comprise a segmented radial sealing seal 11 (JRS) consisting of a ring of sealing of carbon segments held pressed against each other, integral with the casing 2. This segmented radial sealing seal 11 cooperates with an outer surface 12 coming into contact with its inner surface. The outer surface 12 may be cylindrical. It belongs to a sleeve 13 secured at 130 to the rotary shaft 1 and thus rotates with it around the axis LL. The section of the sleeve 13 in a meridian plane here has a shape of U parallel to the axis of rotation LL. Thus, the outer surface 12 extends substantially parallel to the axis LL. An interior space 24, open towards the downstream, is preferably defined under the branch 120 of the sleeve having the outer surface 12. As already mentioned, such an interior space or cavity 24 serves for cooling the radial contact seal 11. With such a sleeve, the shaft 1 goes, as shown by the arrow in Figure 2, can be mounted substantially along the axis LL in the housing 10 2 going here from the right to the left along the axis LL , then the radial seal 11 and the surface 12 will bear when the shaft 1 is in the operating position relative to the casing 2, as in Figure 1. The design of the segmented radial seal 11 provides a sufficient seal to slow the passage of the air and thereby establish a pressure difference between its two sides. In this way, when the turbomachine is operating, the pressure PO of the chamber 8 can be maintained at a value lower than the pressure P1 which is established in the space upstream of the radial sealing means 9 of the upstream passage, which is in communication with higher pressure zones in the turbomachine.
    [0011] The upstream radial sealing means 9 is carried by a partition 17 which separates the oil chamber 8 from an air chamber 18. Here, the partition 17 comes into sealing engagement (preferably with the interposition of a seal) against the upstream end of the support member 7 of the bearing 3. Thus, the upstream radial sealing means 9 will ensure sealing between the partition 17 and the sleeve 13 of the shaft 1. It is here provided with a swirler 14, inside the enclosure 8 with respect to the segmented radial seal 11. This swirler 14, formed on a flange axial 140 cooperates with a portion of the outer surface 12 extending downstream of that cooperating with the segmented radial seal 11. The function of the auger 14 is to return to the enclosure 8 the oil can reach 3036441 10 upstream passage and to protect the segmented radial seal 11 from this oil. The axial flange 140 may form an extension of the radial partition 17. To the downstream end of the oil enclosure 8, the radial sealing means 10 of the downstream passage of the rotary shaft 1 here comprises a labyrinth seal, con stitué wipers 15 integral with the shaft 1 which meet a cylindrical surface 16 integral with the housing 2, of abradable material. Returning towards the upstream end of this enclosure 8, it will be noted that the sleeve 13 locally surrounds the shaft 1, partly in the air chamber 18, partly in the oil chamber 8.
    [0012] In order to supply oil to the zone of the sleeve in the oil chamber 8, a nozzle 19 is disposed therein. It is mounted so as to project oil towards the drive shaft 1 and not to interfere with the aforementioned operations of assembly / disassembly of the shaft 1. Thus, if one names dl the (first) distance which, radially to the axis LL, separates from this axis the outer surface 12 of the sleeve 13 where the gasket 9 rests, the nozzle 19 extends into the chamber 8 (and closer to the axis) to a free end 19a, which is located radially to the axis LL, at a (second) distance d2 of this axis LL, the second distance being greater than the first distance dl.
    [0013] For its mounting and maintenance, it will be preferred that the nozzle is fixed to the casing 2 at 20 and passes through a passage 21 formed in the support part 7 of the bearing 3 connected to the casing 2. This bearing support piece 7 3 will advantageously comprise a deformable annular portion 70 (FIG. 2) having a plurality of through slots defining between them rectilinear and longitudinal tongues or posts 71 which are elastically deformable in the axial and / or radial direction. One of these through slots will then define the passage 21 for mounting the nozzle 19. The tabs or balusters 71 are regularly distributed around the longitudinal axis of the part 7, which axis is coaxial with the axis LL.
    [0014] In operation, the portion 70 of the part 7 is deformed to allow decentrations of the bearing 6, for example under the effect of an imbalance. It will have been noticed that the support piece 7 of the bearing 3 is located at a minimum radial distance d3 from the axis LL greater than the second radial distance d2. Even more so if the seal 9 comprises a radial contact seal 11 (JRS) and a swirler 14, it should be protected from a direct projection of oil from the nozzle which has been schematized in a channel 22 oil outlet located towards its end 19a. Thus, as shown in the detail of FIG. 3, it is arranged around the nozzle 19 a cowling 23. It will be noted that only a part of the jets coming from the nozzle can be deflected by the cowling 23 (channel 22, FIG. 4), another part, not directly directed towards the seal 9 and / or the sleeve 13 and issuing FIG 3,4 of the channel 220, not deviated, since in this embodiment illustrated the cowling covers only the channel (s) which directs (s) the jet (s) from the nozzle directly to the seal 9 and / or the sleeve 13, as shown schematically in Figure 4.
    [0015] Both for the efficiency in the distribution of the oil and not to interfere with the aforesaid operations of assembly / disassembly substantially axial shaft 1, the cowling 23 extends radially inwards, until a radial distance d4 greater than the first radial distance d1.
    [0016] With the cowling, the jet of oil from the nozzle and directed towards the sleeve 13 will be broken, while being able to reach the interior space 24 open downstream of the U-shape of this sleeve. Thus, while satisfying an assembly obligation which prevents the nozzle 19 from being placed radially at the level of the sleeve 13, and in particular in the case of its cavity 24, it will be possible to aim this cavity without aiming at the seal 9; see arrow 230 figure 3.
    [0017] 3036441 12 And even more if the cowling 23 is shaped to flare towards the free end of the nozzle (see Figures 3 and 4), there will be a cost-effective solution, with despite all a conventional nozzle. For ease of assembly and disassembly, the cowling 23 has been fixed here around the nozzle by a ring 25. The ring serves the nozzle 19 radially beyond the annular bead 190 which it has towards its free end 19a. where it is crossed by the oil outlet channels, that 22. Preferably, these channels will be angularly distributed around the radial axis 26 along which here extends the nozzle 19, being inclined globally in the direction 1. With such an architecture means, it will be all the easier to assemble as follows, along the oil chamber 8, the shaft 1 provided with its sleeve 13, for the purpose in particular to limit downtime of the engine and to make sensitive parts accessible, to check and / or replace. Thus it is advisable: - that before mounting the shaft 1, it has in the chamber 8 oil nozzle 19 that we will have previously positioned so that radially to the axis is respected the distance d2, 20 - then to pass, in the chamber 8, in front of the nozzle 13 and substantially parallel to the axis LL, the shaft 1 integral with the sleeve, as indicated by the arrow in Figure 2 With regard to the cowling 23, it is also advisable to proceed as follows for its assembly, before mounting the shaft 1 and after positioning the nozzle 13 in the oil chamber 8: - position the cowling 23 of in such a way that it extends, radially inwards, to the distance d4, and thus fixes the cowling to the nozzle 23, thus arranging it around the orifices of the oil outlet channel (s) 22 in the direction of the sleeve 13.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Turbomachine bearing assembly (3), comprising: - a shaft (1) rotating about an axis (LL) and which is secured to a sleeve (13) which surrounds it locally and which has an outer surface (12) located , radially to the axis (LL), at a first distance (dl) from this axis, - at least one bearing (3) supporting the shaft (1) in rotation, - a housing (2) in which is disposed l shaft (1), - a partition (17) separating an air chamber (18) and an oil chamber (8), - a radial contact seal (9) arranged between the partition (17) and the sleeve (13) of the shaft (1) which rotate relative to each other, characterized in that it further comprises a nozzle (19) arranged to project oil towards the shaft (1). ) in the oil chamber (8) where the nozzle (19) extends to a free end (19a) which is located radially to the axis (LL) at a second distance ( d2) of this axis, the second distance (d2) being greater than at first distance (dl).
    [0002]
    A turbomachine bearing assembly according to claim 1, which comprises, at a radial distance (d3) from the upper axis to the second distance (d2), a bearing support member (7) connected to the housing (2). ), said support piece (7) having a passage (21) through which the nozzle (19), which is fixed to the housing, passes.
    [0003]
    A turbomachine bearing assembly according to claim 1 or 2, wherein the sleeve has a cavity (24) for cooling the seal (9).
    [0004]
    4. A turbomachine bearing assembly according to one of claims 1 to 3, which comprises a cowling (23) disposed around the nozzle (19) for protecting the seal (9) from a direct projection of oil, the cowling extending radially inwardly to a distance (d4) greater than the first distance (d1). 3036441 14
    [0005]
    5. Turbomachine bearing assembly according to one of claims 1 to 4, wherein the seal is equipped with a de-oiling worm (6) provided on an axial flange (14) and arranged opposite the outer surface. (12) of the sleeve of the rotating shaft (1). 5
    [0006]
    6. A turbomachine bearing assembly according to claims 3 and 4, or claims 3, 4 and 5, wherein: - the sleeve comprises a branch (120) substantially parallel to the axis (LL), which defines between it and the An inner shaft (24) open downstream (AV), which has said outer surface (12) and defines said cavity (24), - the seal (9) is disposed around the surface external of said branch, - and the cowling (23) is arranged around the nozzle (19) to protect said seal from a direct projection of oil exiting the nozzle. 15
    [0007]
    A turbomachine bearing assembly according to claim 4 or one of claims 5 or 6, when appended to claim 4, wherein the cowling (23) flares out towards the free end of the nozzle.
    [0008]
    A turbomachine bearing assembly according to claim 3 or one of claims 5 to 7, when appended to claim 4, wherein: the nozzle comprises oil outlet channels (22,220) in the oil chamber (8), and the cowling (23) covers only the channel (22) directing directly to the gasket (9) and / or the sleeve (13). ) oil jet (s) leaving (s).
    [0009]
    9. A method of mounting, in an enclosure (8) oil, a shaft (1) adapted to rotate about an axis and which is secured to a sleeve (13) which surrounds locally and has a surface ( 12) external, located radially to the axis, at a first distance (dl) from this axis, characterized in that: - before mounting the shaft (1) rotating, is disposed in the enclosure (8) oil a nozzle (19) adapted to project oil therein and positioned therein so that, radially to the axis (LL), said nozzle extends exclusively beyond said first distance, from a second distance (d2) from said axis which is greater than the first distance (d1), and then, in the chamber (8), is passed in front of the nozzle and substantially parallel to the axis, shaft (1) integral with the sleeve.
    [0010]
    10. The method of claim 9, wherein, before mounting the shaft (1) rotating and after positioning the nozzle (19) in the chamber (8) oil: - it positions the cowling (23) so that it extends, radially inwards, to a distance (d4) greater than the first distance 10 (d1), and thus fixes the cowling at the nozzle, by arranging it around orifices (22); ) of oil outlet of said nozzle.
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    同族专利:
    公开号 | 公开日
    FR3036441B1|2019-06-07|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2956824A|1957-12-27|1960-10-18|Koppers Co Inc|Vented shaft seal|
    US4858426A|1988-07-21|1989-08-22|General Motors Corporation|Secondary oil system for gas turbine engine|
    US5301957A|1992-04-27|1994-04-12|General Electric Company|Expanding circumferential seal with upper-cooled runner|
    US5593165A|1994-09-20|1997-01-14|Allison Engine Company, Inc.|Circumferential flow channel for carbon seal runner cooling|
    US20030110778A1|2001-12-18|2003-06-19|Karafillis Apostolos Pavlos|Flexibly coupled dual shell bearing housing|US20160348522A1|2015-05-26|2016-12-01|Pratt & Whitney Canada Corp.|Seal and bearing assembly for a gas turbine engine and method of assembling same|
    FR3080650A1|2018-04-26|2019-11-01|Safran Aircraft Engines|LUBRICATION ASSEMBLY FOR A TURBOMACHINE|
    FR3094403A1|2019-04-01|2020-10-02|Safran Transmission Systems|Turbomachine jet comprising an oblique face ejection head|
    法律状态:
    2016-05-25| PLFP| Fee payment|Year of fee payment: 2 |
    2016-11-25| PLSC| Search report ready|Effective date: 20161125 |
    2017-04-27| PLFP| Fee payment|Year of fee payment: 3 |
    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2018-04-23| PLFP| Fee payment|Year of fee payment: 4 |
    2019-04-19| PLFP| Fee payment|Year of fee payment: 5 |
    2020-04-22| PLFP| Fee payment|Year of fee payment: 6 |
    2021-04-21| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1554596|2015-05-22|
    FR1554596A|FR3036441B1|2015-05-22|2015-05-22|CAPOTE OIL SPRINKLER|FR1554596A| FR3036441B1|2015-05-22|2015-05-22|CAPOTE OIL SPRINKLER|
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