• 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 lubricating and cooling device (40) for a turbomachine bearing (10). The device is at least partially annular. The device (40) includes a first conduit (60) and a second conduit (80) inclined relative to the first conduit (60). The first conduit (60) is configured to be in thermal contact with an outer race (20) of the bearing at least partially surrounding it. The second conduit (80) is fluidly connected to the first conduit (60). The first conduit (60) is configured to circulate lubricant to cool the outer race (20) to an exhaust outlet (45) of the lubricant. The second conduit (80) is configured to eject lubricant through a lubrication outlet (43) to the bearing (10).
    公开号:FR3071548A1
    申请号:FR1758792
    申请日:2017-09-22
    公开日:2019-03-29
    发明作者:Lionel Bauduin；Othmane Ez-Zahraouy
    申请人:Safran Transmission Systems SAS；
    IPC主号:
    专利说明:

    BEARING LUBRICATION AND COOLING DEVICE FOR A TURBOMACHINE
    DESCRIPTION
    TECHNICAL AREA
    The invention relates to bearings for rotating shafts of an aircraft turbomachine. More specifically, the invention relates to the lubrication and cooling of a turbomachine bearing.
    PRIOR STATE OF THE ART
    The rotating turbomachine shafts are supported and guided in rotation by bearings.
    The outer ring of a bearing of known structure is fixed to a support which is part of the stator of the turbomachine. The bearing is continuously supplied with oil, to lubricate it and to limit its wear by friction.
    The oil flow used to cool the bearing is much higher than that used to lubricate the bearing. The importance of the overall oil flow supplying the bearing generates significant energy losses and reduces the bearing efficiency.
    STATEMENT OF THE INVENTION
    The invention aims to at least partially solve the problems encountered in the solutions of the prior art.
    In this regard, the invention relates to a lubrication and cooling device for a turbomachine bearing. The lubrication device is at least partially annular around an axis of the lubrication and cooling device.
    According to the invention, the device comprises a first conduit and a second conduit which is fluidly connected to the first conduit.
    The first conduit is configured to be in thermal contact with an outer ring of the bearing, at least partially surrounding the outer ring. The first conduit is configured to circulate lubricant to cool the outer ring, to a lubricant discharge outlet configured to discharge lubricant in the opposite direction of the bearing.
    The second conduit is inclined relative to the first conduit. The second conduit is configured to eject lubricant through a lubrication outlet to the bearing to lubricate the bearing.
    Thanks to the lubrication and cooling device according to the invention, the bearing is lubricated and cooled sufficiently, while increasing the efficiency of the bearing.
    The invention may optionally include one or more of the following characteristics, whether or not combined.
    Preferably, the second conduit has no thermal contact with the bearing. The second conduit is very preferably located at a distance from the outer ring.
    Advantageously, the device comprises a common lubricant inlet for supplying the first conduit and the second conduit with lubricant.
    According to a particular embodiment, the first conduit is located axially between the lubrication outlet and the common lubricant inlet or else between the lubrication outlet and the discharge outlet.
    According to an advantageous embodiment, the device comprises a lubricant inlet which is located near a first transverse end of the first conduit. The first conduit includes the discharge outlet which is located at a second transverse end of the first conduit which is opposite the first end.
    According to another particular feature, the lubrication outlet is oriented so as to spray lubricant onto a side of a rolling element, preferably substantially axially.
    Preferably, the discharge outlet is oriented substantially axially or substantially radially.
    Advantageously, the lubrication device comprises a plurality of lubricant inlets, a plurality of discharge outlets and / or a plurality of lubrication outlets, which are spaced around the axis of the lubrication and cooling device.
    Preferably, the lubricant inlets, the discharge outlets and / or the lubrication outlets are distributed symmetrically around the axis of the lubrication and cooling device.
    According to an advantageous embodiment, the first conduit is oriented substantially axially, the second conduit being oriented substantially radially inward, relative to the axis of the lubrication and cooling device.
    According to another particular feature, the lubrication and cooling device is annular, the first conduit being configured to be in thermal contact with the outer ring at least over the majority of the circumferential length of the outer ring.
    Preferably, the second conduit forms a circumferential rim of the lubrication and cooling device.
    Advantageously, the first conduit comprises a wall which comprises at least one cooling element projecting inside the first conduit. The cooling element is configured to increase the heat exchanges between the lubricant in the first conduit and the outer ring.
    Advantageously, the wall of the first conduit and / or a wall of the second conduit comprises at least one reinforcement configured to increase the mechanical resistance of the lubrication and cooling device. The reinforcement is also configured to increase the heat exchanges between the lubricant in the duct and the outer ring.
    The invention also relates to an assembly for a turbomachine comprising a fixed bearing support, the bearing which comprises an outer ring, and a lubrication and cooling device as defined above.
    The lubrication and cooling device at least partially surrounds the outer ring and is located radially between the bearing and the support.
    Preferably, the lubrication and cooling device is rigidly assembled to the support by the outer ring.
    Preferably, the support comprises a radially exterior surface and a radially interior surface opposite the radially interior surface, the support being configured to supply lubricant to the device by a conduit which extends through the support from the radially exterior surface to to the radially inner surface.
    BRIEF DESCRIPTION OF THE DRAWINGS
    The present invention will be better understood on reading the description of exemplary embodiments, given for purely indicative and in no way limiting, with reference to the appended drawings in which:
    Figure 1 is a schematic view in longitudinal section of a turbomachine according to the invention;
    Figure 2 is a schematic view in longitudinal half-section of an assembly of the turbomachine of Figure 1, according to a first preferred embodiment of the invention;
    Figure 3 is a partial schematic view in longitudinal half-section of a lubrication and cooling device according to the first embodiment of the invention;
    Figure 4 is a partial schematic view in longitudinal half-section of a lubrication and cooling device according to a first alternative embodiment of the first embodiment of the invention;
    Figure 5 is a partial schematic view in longitudinal half-section of a lubrication and cooling device according to a second alternative embodiment of the first embodiment of the invention;
    Figure 6 is a schematic view in longitudinal half-section of an assembly of the turbomachine of Figure 1, according to a second preferred embodiment of the invention;
    Figure 7 is a partial schematic view in longitudinal half-section of a lubrication and cooling device according to the second embodiment of the invention.
    DETAILED PRESENTATION OF PARTICULAR EMBODIMENTS
    FIG. 1 represents an aircraft turbomachine 1 according to a preferred embodiment of the invention. The turbomachine 1 is a turbofan engine. It comprises a rotating shaft 30 which is movable around the main longitudinal axis 3 of the turbomachine 1.
    The shaft 30 comprises in particular a front part 31 and a rear part 32 coaxial. The front 31 and rear 32 parts are joined by a reduction gear 2 shown very schematically. They carry fan blades 6, straightening blades 8 and compressor blades 8.
    The fan blades 6 and the compressor blades 8 can be driven at different rotational speeds through the reduction gear 2. The front shaft 31 is generally supported from front to back by a ball bearing 11 and by a roller bearing 12 placed in the area of the reducer 2. The rear part 32 of the shaft 30, much longer, is in this case supported from front to back first by a pair of ball bearings 13 and 14 then by a pair of roller bearings 16 and 18. The outer ring of each of these six bearings is generally fixed firmly to a housing of the stator 5.
    Usually, the efficiency of the shaft line 31, 32 is between 0.96 and 0.99, with losses essentially produced in the reduction gear 2. Despite this high value of the efficiency, it is important to cool the rotating shaft 30 to dissipate the calorific power dissipated there.
    Each of the six bearings 11, 13, 14, 12, 16, 18 can support the shaft 30. It can also be mounted on a rotating shaft of a low pressure turbine (not shown) or possibly on a turbomachine shaft configured to rotate at high rotational speeds, such as a high pressure turbine shaft (not shown).
    The assembly 4 for a turbomachine comprises a fixed support 50, a bearing 10, and a lubrication and cooling device 40. The lubricant used is typically oil.
    The assembly 4 is annular around an axis of revolution X-X of the lubrication and cooling device. The axis X-X of the lubrication and cooling device is substantially coincident with the longitudinal axis 3 of the turbomachine.
    In the remainder of the description, the front and rear directions are defined relative to the direction of flow of the gases in the turbomachine, in the direction of the fan towards the low pressure turbine.
    The upstream and downstream directions are defined with reference to the direction of flow of the lubricant. The lubricant flows from upstream to downstream in the lubrication and cooling device 40.
    Unless otherwise specified, the adjectives "axial" and "radial" are defined relative to the axis of revolution XX of the lubrication and cooling device 40. An axial direction is a direction substantially parallel to the axis XX of the lubrication device and cooling 40. A radial direction is a direction substantially orthogonal to the axis XX of the lubrication and cooling device 40 and intersecting with the axis XX of the lubrication and cooling device. A circumferential direction is a direction around the X-X axis of the lubrication and cooling device.
    The fixed support 50 is part of the stator 5 of the turbomachine. It includes a housing portion 52 and a lubricant supply duct 51. It serves as a support for the bearing 10 and for the lubrication and cooling device 40.
    The housing portion 52 comprises a radially outer surface Si, a radially inner surface S 2 and a front surface S 3 . The radially inner surface S 2 is opposite to the radially inner surface Si.
    The inlet duct 51 extends from the radially outer surface Si to the radially inner surface S 2 . It is used to convey lubricant through the housing segment 52 to the lubrication and cooling device 40.
    The inlet duct 51 comprises a supply cavity 53 which is located near the radially inner surface S 2 and which serves as a reserve of lubricant for the lubrication and cooling device 40.
    The bearing 10 comprises an outer ring 20, an inner ring 26, a bearing cage 28 and rolling elements 29. The bearing 10 is in particular one of the bearings 11,12,13,14,16,18 which is shown in Figure 1.
    The outer ring 20 comprises a body 22 and a fastener 24 which is rigidly secured to the body 22. The outer ring 20 is in particular one piece.
    The body 22 forms a raceway for the rolling elements 29. The attachment 24 serves to rigidly secure the bearing 10 to the support 50. The attachment 24 attaches the body 22 and the lubrication and cooling device 40 to the front surface S 3 of support 50.
    The inner ring 26 is located radially inwards relative to the outer ring 20. It is rigidly secured to the shaft 30 of the turbomachine.
    The rolling cage 28 and the rolling elements 29 are located radially between the inner ring 26 and the outer ring 20. The rolling cage 28 is configured to guide the movement of the rolling elements 29 in the rolling path relative to the support 50.
    The rolling elements 29 can be of different natures, typically balls, rollers or needles. They are distributed around the axis X-X of the lubrication and cooling device 40.
    The lubrication and cooling device 40 is annular around the axis X-X of the device. The lubrication and cooling device 40 partially surrounds the outer ring 20. It is located radially between the bearing 10 and the support 50.
    It takes the form of a ring comprising a first conduit 60 which forms the body of the ring, and a second conduit 80 which forms a circumferential rim of the device 40.
    It also includes a plurality of lubricant inlets 41, a plurality of discharge outlets 45 and a plurality of lubrication outlets 43. The device 4 comprises in particular as much lubricant inlet 41 as lubrication outlets 43 and as many lubrication outlets 43 than discharge outlets 45.
    The first conduit 60 comprises a tubular wall 62 which is in mechanical and thermal contact with the outer ring 20. The tubular wall 62 surrounds the outer ring 20 over substantially the entire circumferential length of the outer ring 20.
    The first conduit 60 is oriented transversely axially in a transverse direction Yi-Yi. It extends axially between a first transverse end 61a and a second transverse end 61b. The first transverse end 61a forms the front end of the first conduit 60. The second transverse end 61b forms the rear end of the first conduit 60.
    Referring to Figures 2 and 3, the tubular wall 62 is crossed by the lubricant inlets 41 which are located near the first transverse end 61a. The tubular wall 62 is also traversed by discharge outlets 45 which are situated at the level of the second transverse end 61b. In other words, the first conduit 60 extends transversely between the lubricant inlets 41 and the lubrication outlets 43.
    The first conduit 60 is configured to circulate lubricant from the lubricant inlet 41 to the discharge outlet 45, without this lubricant supplying the bearing 10. The first conduit 60 is used to circulate lubricant to cool the outer ring 20.
    The second conduit 80 is fluidly connected to the first conduit 60, being inclined relative to the first conduit 60.
    The second conduit 80 comprises a tubular wall 82 which forms an elbow with the tubular wall 62 of the first conduit, being located axially near the second end 61b of the first conduit.
    The tubular wall 82 of the second conduit 80 is located axially at a distance from the bearing 10. The tubular wall 82 is opposite the outer ring 20 and the bearing cage 28 over substantially the entire circumferential length of the bearing 10. The tubular wall 82 is crossed by the lubrication outlets 43 which are oriented towards the bearing 10.
    The second conduit 80 is oriented transversely radially inwards in a transverse direction Y2-Y2 · The second conduit 80 extends radially between a first transverse end 81a and a second transverse end 81b. The first transverse end 81a forms the upper end of the second conduit 80. The second transverse end 81b forms the lower end of the first conduit 80.
    The second conduit 80 is configured to eject lubricant having circulated in the first conduit 60 towards the bearing 10, to lubricate the bearing 10.
    Referring to Figures 2 and 3, the lubricant inlets 41 are spaced from each other symmetrically about the axis X-X of the device, being located near the front transverse end 61a. The lubricant inlets 41 are each opposite an outlet from the supply cavity 53 which supplies them with lubricant. They are oriented substantially radially.
    The inputs 41 are inputs common to the first conduit 60 and to the second conduit 80, which they supply with lubricant.
    The discharge outlets 45 are spaced from each other symmetrically around the axis X-X of the device, being located at the distal end 61b of the first conduit. They cross the rear of the wall 82 of the second conduit.
    They are offset radially inwards relative to the lubricant inlets 41.
    The discharge outlets 45 are each oriented in a discharge direction Y 5 -Y 5 which is slightly inclined relative to the axis XX of the lubrication and cooling device 4, so that the lubricant is sprayed axially at the opposite of the rolling elements 29. The evacuation outlets 45 are configured to evacuate lubricant which has made it possible to cool the bearing 10 and which is not used to lubricate the bearing 10.
    Still with reference to FIGS. 2 and 3, the lubrication outlets 43 are spaced from each other symmetrically around the axis X-X of the device. They pass through the front of the wall 82 of the second conduit, towards the bearing 10.
    The lubrication outlets 43 are located axially between the inlets 41 and the outlet outlets 45. They are offset radially inwards relative to the inlets 41 and the outlet outlets 45.
    The lubrication outlets 43 are each oriented in a lubrication direction Y 3 -Y 3 which is slightly inclined relative to the axis XX of the lubrication and cooling device 4, so that the lubricant is sprayed onto the sides of the rolling elements 29. The lubrication outlets 43 are configured to spray lubricant from the second conduit 80 towards the bearing 10 to lubricate the bearing 10.
    The operation of the lubrication and cooling device 40 according to the first embodiment is described below.
    An inlet flow 101a flows through the inlet conduit 51 towards the common inlet 41 of lubricant. The flow of lubricant passing through the common inlet 41 flows along the transverse direction Yi-Yi of the first conduit towards the rear end 61b, forming a cooling flow 104a. A majority of the lubricant is then ejected through the discharge outlet 45 according to a discharge flow 105a. The rest of the lubricant circulates in the second conduit 80 in the direction of the lubrication outlet 43 where it is ejected towards the bearing 10 according to a lubrication flow 107a.
    Referring to Figure 4, the first embodiment differs from the first embodiment in that the tubular wall 62 of the first conduit 60 comprises cooling elements 64 which protrude inside the first conduit 60 towards the transverse axis Yi-Yi of the first conduit. The cooling elements 64 are spaced from each other along the circumferential direction of the first conduit 60. They are axially spaced from each other between the first end 61a and the second end 61b of the first conduit.
    These cooling elements 64 take in particular the form of cooling fins. They are configured to increase the heat exchanges between the lubricant in the first conduit 60 and the outer ring 20.
    Referring to Figure 5, the second embodiment differs from the first embodiment in that the tubular wall 62 of the first conduit 60 includes reinforcements 66 which protrude inside the first conduit 60 towards the transverse axis Yi-Yi of the first conduit. The reinforcements 66 are spaced from each other along the circumferential direction of the first conduit 60. They are axially spaced from each other axially between the first end 61a and the second end 61b of the first conduit.
    These reinforcements 66 take in particular the form of bridges which extend along the diameters of the first conduit 60. They are configured to increase the mechanical resistance of the lubrication and cooling device 40.
    The second embodiment is shown with reference to FIGS. 5 and 6. The assembly 4 according to the second embodiment is distinguished from that of the first embodiment by the structure of the support 50 and by that of the lubrication and cooling device. 42.
    With reference to FIG. 6, the support 50 comprises the supply duct 51 and an outlet duct 57. The supply duct 51 is similar in shape to that of the first embodiment, being offset towards the rear by compared to that of the first embodiment to lead to the common entrances 41.
    The outlet conduit 57 extends from the radially internal surface S 2 to the radially external surface Si. It serves to evacuate the lubricant used to cool the outer ring 20 from the assembly 4.
    The outlet conduit 57 comprises an outlet cavity 55 is located near the radially inner surface S 2 and which forms a reserve of lubricant for the lubrication and cooling device 42.
    Referring mainly to FIG. 6, the lubrication and cooling device 42 according to the second embodiment differs from that of the first embodiment by the position of the common inlet 41 and by the position of the discharge outlet. 45. The first conduit 60 is located axially between the lubrication outlet 43 and the evacuation outlet 45.
    The common input 41 is offset backwards with respect to that of the first embodiment. The common inlet 41 is located near the second transverse end 61b of the first conduit, instead of being near its first transverse end 61a. In other words, the common inlet 41 is located near the junction of the first conduit 60 and the second conduit 80. The inlet 41 is configured to divide the flow of lubricant which passes through it into a transit flow 106 in the second conduit 80 and in a cooling flow 104b.
    The discharge outlet 45 is offset forward and upward relative to that of the first embodiment. The discharge outlet 45 is oriented substantially radially outward in the direction Y5-Y5, that is to say in a direction opposite to the bearing 10.
    The operation of the lubrication and cooling device 42 according to the second embodiment is described below.
    An inlet flow 101b flows through the inlet conduit 51 towards the common inlet 41 of lubricant. The flow of lubricant passing through the common inlet 41 is divided from the inlet 41 into a transit stream 106 in the second duct and a cooling stream 104b flowing in the first duct 60.
    All of the lubricant in the second conduit 80 is ejected through the lubrication outlet 43 according to a lubrication flow 107b. All of the lubricant in the first conduit 60 is ejected through the discharge outlet 45 in the outlet conduit 57 radially outward from the assembly 4 according to a discharge stream 105b.
    The first conduit 60 makes it possible to effectively cool the bearing 10, by limiting the quantity of lubricant injected into the bearing 10. The second conduit 80 makes it possible to lubricate the bearing 10. The lubrication and cooling device 40, 42 effectively cools and lubricates the bearing 10, while increasing the efficiency of bearing 10.
    In the first embodiment, the lubricant circulating in the second conduit 80, that is to say the lubrication flow 107a, circulated in the first conduit 60. It therefore served to cool the outer ring 20 in the first duct 60 and the cooling flow 104a is greater. The lubricant injected into the bearing 10 nevertheless has a higher temperature. The lubricant injected for lubrication also has a lower viscosity.
    In the second embodiment, the lubricant circulating in the second conduit 80, that is to say the transit flow 106, did not circulate in the first conduit 60. It therefore did not heat up by contact thermal with the outer ring 20. The lubricant injected into the bearing 10 has a lower temperature, which promotes heat exchange inside the bearing 10. The lubricant has a higher viscosity. It therefore tends to lubricate the bearing 10 more.
    The assembly 4 according to the first embodiment is preferred when the temperature of the lubricant is low compared to that of the bearing 10. The assembly 4 according to the second embodiment is preferred when the temperature of the lubricant entering the lubrication device and cooling 40, 42 is higher.
    Of course, various modifications can be made by those skilled in the art to the invention which has just been described without departing from the scope of the description of the invention.
    The structure of the turbomachine 1 can vary. It can also be a turboprop or a turboshaft.
    In general, the axis X-X of the lubrication and cooling device is substantially parallel with the axis 3 of the turbomachine. According to an alternative embodiment, it is strictly parallel to the axis 3 of the turbomachine.
    As a variant, the lubrication and cooling device 40, 42 5 comprises a heat transfer layer between the wall 62 of the first conduit 60 and the outer ring 20.
    The lubrication and cooling device 40, 42 can be fixed to the support 50 directly rather than by the outer ring 20.
    In another variant, the lubrication device 40, 42 is in one piece 10 with the support 50.
    The shape of the lubrication and cooling device 40, 42 may vary. In particular, the second conduit can be inclined at an angle different from 90 ° relative to the first conduit 60.
    The number, distribution and orientation of the inlets 41, the lubrication outlets 43 and the outlets 45 can vary. The lubrication and cooling device 40, 42 can have more inlets than lubrication outlets 43.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Lubrication and cooling device (40, 42) for a bearing (10, 11, 12, 13, 14, 16, 18) of a turbomachine, at least partially annular around an axis (XX) of the lubrication device and cooling, characterized in that the device (40, 42) comprises:
    a first conduit (60) configured to be in thermal contact with an outer ring (20) of the bearing at least partially surrounding the outer ring (20), a second conduit (80) inclined relative to the first conduit (60) and connected fluidically to the first conduit (60), the first conduit (60) being configured to circulate lubricant to cool the outer ring (20), to a lubricant discharge outlet (45) configured to discharge lubricant in the direction (Y4 -Y4, Y5-Y5) opposite the bearing (10, 11, 12, 13.14, 16.18), the second conduit (80) being configured to eject lubricant through a lubrication outlet (43) towards the bearing (10, 11, 12, 13,14, 16, 18) to lubricate the bearing (10, 11, 12, 13,14, 16, 18).
    [2" id="c-fr-0002]
    2. Lubrication and cooling device (40, 42) according to the preceding claim, comprising a common inlet (41) of lubricant for supplying the first conduit (60) and the second conduit (80) with lubricant.
    [3" id="c-fr-0003]
    3. Lubrication and cooling device (40, 42) according to the preceding claim, wherein the first conduit (60) is located axially between the lubrication outlet (43) and the common inlet (41) of lubricant or between the lubrication outlet (43) and the discharge outlet (45).
    [4" id="c-fr-0004]
    4. Lubrication and cooling device (40, 42) according to any one of the preceding claims, comprising a lubricant inlet (41) which is located near a first transverse end (61a) of the first conduit, the first conduit (60) comprising the discharge outlet (45) which is located at a second transverse end (61b) of the first conduit which is opposite to the first end (61a).
    [5" id="c-fr-0005]
    5. Lubrication and cooling device (40, 42) according to any one of the preceding claims, in which the lubrication outlet (43) is oriented so as to spray lubricant onto a side of a rolling element (29) , preferably substantially axially, and / or wherein the discharge outlet (45) is preferably oriented substantially axially or substantially radially.
    [6" id="c-fr-0006]
    6. Lubrication and cooling device (40, 42) according to any one of the preceding claims, in which the lubrication and cooling device (4) comprises a plurality of lubricant inlets (41), a plurality of outlets discharge (45) and / or a plurality of lubrication outlets (43), which are spaced around the axis (XX) of the lubrication and cooling device, the lubricant inlets (41), the outlets discharge (45) and / or the lubrication outlets (43) being preferably distributed symmetrically around the axis (XX) of the lubrication and cooling device.
    [7" id="c-fr-0007]
    7. Lubrication and cooling device (40, 42) according to any one of the preceding claims, in which the first conduit (60) is oriented substantially axially, the second conduit (80) being oriented substantially radially inward, relative to the axis (XX) of the lubrication and cooling device.
    [8" id="c-fr-0008]
    8. Lubrication and cooling device (40, 42) according to any one of the preceding claims, in which the lubrication and cooling device (40, 42) is annular, the first conduit (60) being configured to be at thermal contact of the outer ring (20) at least over the majority of the circumferential length of the outer ring (20), the second conduit (80) preferably forming a circumferential edge of the lubrication and cooling device (40, 42) .
    [9" id="c-fr-0009]
    9. Lubrication and cooling device according to any one of the preceding claims, in which an internal wall (62) of the first duct comprising at least one cooling element (64) projecting in the first duct (60) and configured to increase the heat exchange between the lubricant in the first conduit (60) and the outer ring (20), and / or in which the inner wall (62) of the first conduit and / or an inner wall (82) of the second conduit comprise at least one reinforcement (66) configured to increase the mechanical resistance of the lubrication and cooling device (40, 42).
    [10" id="c-fr-0010]
    10. An assembly for a turbomachine comprising a fixed bearing support (50), the bearing (10, 11, 12, 13, 14, 16, 18) which comprises an outer ring (20), and a lubrication and cooling device ( 40, 42) according to any one of the preceding claims, the lubrication and cooling device (40, 42) at least partially surrounding the outer ring (20) and being located radially between the bearing (10, 11, 12, 13 , 14, 16, 18) and the support (50).
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    同族专利:
    公开号 | 公开日
    WO2019058051A1|2019-03-28|
    EP3649326A1|2020-05-13|
    US20200256209A1|2020-08-13|
    FR3071548B1|2021-09-10|
    EP3649326B1|2021-07-28|
    CN111094702A|2020-05-01|
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    FR2949246A1|2009-08-20|2011-02-25|Snecma|Bearing i.e. rolling bearing, lubrication and cooling device for e.g. jet engine of airplane, has nozzles supplied with oil by conduits of annular element, where rotation of shaft carrying annular element induces supply pressure of nozzles|
    DE102009051307A1|2009-10-29|2011-05-05|Bosch Mahle Turbo Systems Gmbh & Co. Kg|Charging device, particularly exhaust gas turbocharger, comprises shaft mounted over two roller bearings, where two roller bearings are arranged in cartridge or socket|
    JP2011169356A|2010-02-17|2011-09-01|Ntn Corp|Rolling bearing device with lubricating function, and method for setting crush allowance of seal member|
    JP2014047812A|2012-08-30|2014-03-17|Jtekt Corp|Lubrication device for rolling bearing|
    US8262344B2|2008-04-02|2012-09-11|Hamilton Sundstrand Corporation|Thermal management system for a gas turbine engine|
    DE102008020067A1|2008-04-22|2009-10-29|Schaeffler Kg|Bearing arrangement with a double row rolling bearing, turbocharger and method for supplying a lubricant to the rows of rolling elements of a double row rolling bearing|
    GB2521420A|2013-12-19|2015-06-24|Ford Global Tech Llc|A turbocharger lubricant cooler|
    FR3027628B1|2014-10-28|2019-07-12|Safran Aircraft Engines|LUBRICATING OIL RECOVERY COVER FOR TURBOMACHINE EQUIPMENT|GB201800777D0|2018-01-18|2018-03-07|Rolls Royce Plc|Gas turbine engine oil circulation|
    FR3101684B1|2019-10-08|2022-03-04|Safran Trans Systems|Improved lubricating and cooling device for aircraft turbine engine bearings|
    US11268573B2|2020-03-25|2022-03-08|Pratt & Whitney Canada Corp.|Bearing housing oil intake to supply dual bearing structure|
    法律状态:
    2019-03-29| PLSC| Search report ready|Effective date: 20190329 |
    2019-08-20| PLFP| Fee payment|Year of fee payment: 3 |
    2020-08-19| PLFP| Fee payment|Year of fee payment: 4 |
    2021-08-19| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1758792A|FR3071548B1|2017-09-22|2017-09-22|TURBOMACHINE BEARING LUBRICATION AND COOLING DEVICE|
    FR1758792|2017-09-22|FR1758792A| FR3071548B1|2017-09-22|2017-09-22|TURBOMACHINE BEARING LUBRICATION AND COOLING DEVICE|
    CN201880060033.1A| CN111094702A|2017-09-22|2018-09-19|Device for lubricating and cooling a rolling bearing of a turbomachine|
    EP18796703.9A| EP3649326B1|2017-09-22|2018-09-19|Device for lubricating and cooling a bearing for turbomachine|
    US16/648,051| US20200256209A1|2017-09-22|2018-09-19|Device for lubricating and cooling a turbomachine bearing|
    PCT/FR2018/052284| WO2019058051A1|2017-09-22|2018-09-19|Device for lubricating and cooling a turbomachine rolling bearing|
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