• 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 present invention relates to a turbomachine bearing support (1) comprising: - a tapered part (10) having an upstream end configured to be fixed to the inter-turbine casing (60) and a downstream end bearing an inner ring (15); - a downstream part (20) comprising an outer shroud (31) and an inner shroud (21) the inner ring (15), the outer shroud (31) and the inner shroud (21) together defining three concentric skins; the turbomachine bearing support (1) being constituted by at least two casting parts fixed to one another during assembly, the first (100) of these parts defining the frustoconical part (10) and the inner ring (15 ) and being adapted to support the bearing (5), the second part (200) defining the downstream part (20) and being adapted to seal the lubrication chamber (27).
    公开号:FR3053728A1
    申请号:FR1656534
    申请日:2016-07-07
    公开日:2018-01-12
    发明作者:Dimitri Marquie
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    (57) The present invention relates to a bearing support (f) for a turbomachine comprising:
    - a frustoconical part (10) having an upstream end configured to be fixed to the inter-turbine casing (60) and a downstream end carrying an inner ring (15);
    - A downstream part (20) comprising an outer ferrule (31) and an inner ferrule (21) the inner ring (15), the outer ferrule (31) and the inner ferrule (21) together defining three concentric skins;
    the bearing support (1) of a turbomachine being constituted by at least two casting parts fixed to each other during assembly, the first (100) of these parts defining the frustoconical part (10) and the inner ring (15 ) and being adapted to support the bearing (5), the second part (200) defining the downstream part (20) and being adapted to seal the lubrication chamber (27).

    Two-piece bearing support
    FIELD OF THE INVENTION
    The present invention relates to the field of turbine engine bearing supports, such as a turbojet.
    STATE OF THE ART
    A turbomachine comprises, from upstream to downstream in the direction of gas flow, a compressor, a combustion chamber and a turbine. The role of the compressor is to increase the pressure of the air supplied to the combustion chamber.
    The role of the turbine is to drive the compressor in rotation by taking part of the pressure energy from the hot gases leaving the combustion chamber and transforming it into mechanical energy.
    The compressor and the turbine consist of a first set of fixed parts constituting the stator and a second set of parts, capable of being rotated relative to the stator, constituting the rotor. The rotor is integrally connected to a rotating shaft.
    Rotation of the rotor relative to the stator is made possible by means of a bearing, the bearing being a mechanical member supporting and guiding the rotation of the rotor shaft. The bearing support supports and guides the rotor in rotation.
    Referring to Figure 1, a bearing support 1 comprises a frustoconical part 10 having an upstream end 11 configured to be fixed to the casing, and a downstream end 12 configured to cooperate with the bearing.
    The frustoconical part 10 has an inner ring 15 configured to be fixed on the outer ring of the bearing.
    A bearing support 1 has an outer ferrule 31 and an inner ferrule 21.
    With reference to FIG. 2, the frustoconical part 10 has one or more oil recovery conduits 28 opening into the lubrication chamber 27.
    With reference to FIG. 3, the frusto-conical part 10 has a bypass pipe 38 (also called a drain) opening into the bypass enclosure 37.
    The structure of such a bearing support 1 has a complexity which poses many difficulties in its manufacture by foundry and its control.
    In particular, the structure of such a bearing support 1 has a triple skin, formed by the inner ring 15, the inner ferrule 21 and the outer ferrule 31.
    The presence of this triple skin does not allow sufficiently homogeneous cooling after manufacture by foundry of the bearing support 1. This results in metallurgical defects and therefore significant retouching rates.
    In addition, a CIC treatment (hot compaction), which is a very expensive vacuum heat treatment, is essential to limit metallurgical defects.
    Many critical machining operations in terms of tolerance must also be carried out on the part. The reject rate of the part is important because each machining operation constitutes a risk of mutilating the part.
    The cost of manufacturing a bearing support 1 according to the prior art is therefore significant, which is all the more problematic since the scrap rate of the part is also significant.
    STATEMENT OF THE INVENTION
    The invention overcomes at least one of the aforementioned drawbacks by proposing a turbojet bearing support having a geometry allowing the manufacture of the bearing support in two parts, one of the parts being the frustoconical part and the other the downstream part.
    To this end, the invention proposes a turbomachine bearing support adapted to support a rotor bearing, the bearing support comprising:
    - a frustoconical part having an upstream end configured to be fixed to the inter-turbine casing and a downstream end carrying an inner ring;
    - a downstream part comprising an outer ferrule and an inner ferrule which extend from the frustoconical part, the inner ferrule defining with the bearing a lubrication chamber, the inner ferrule and the outer ferrule defining between them a bypass enclosure; the zone of the frustoconical part from which the ferrules extend being located upstream of the inner ring;
    the inner ring, the outer ring and the inner ring together defining three concentric skins in the same area of the bearing support;
    the turbomachine bearing support being characterized in that it consists of at least two parts fixed to each other during mounting, the first of these parts defining the frustoconical part and the inner ring and being adapted to support the bearing, the second part defining the downstream part and being adapted to cooperate with the bearing to ensure the tightness of the lubrication chamber, the second part being attached and fixed to the first part at the level of the outer ferrule and the inner ferrule .
    The fact of manufacturing the downstream part independently of the frustoconical part makes it possible to solve the problems linked to cooling after casting and simplifies industrialization.
    Compliance monitoring is also simplified.
    In addition, if one of the manufactured parts has a defect, it can be replaced without the other part being sent for disposal, even though it has no defect.
    The first part being of simple design, it can be made in one piece by foundry without any particular difficulty, which makes it possible to guarantee the necessary mechanical solidity.
    The second part is more complex to manufacture than the first part, but its solidity is less sensitive than that of the first part because it does not have a mechanical role of force transmission. It can therefore be manufactured by manufacturing methods which are easier to implement even if they do not make it possible to guarantee the same mechanical solidity to the part produced as the foundry.
    The invention is advantageously supplemented by the following characteristics, taken individually or in any of their technically possible combinations.
    The bearing support further comprises an oil recovery conduit opening into the lubrication chamber and passing through the frustoconical part, said oil recovery conduit passing through the outer shell and the inner shell to open into the lubrication chamber at the level of the second part which defines the downstream part.
    The oil recovery pipe projects externally from the second part which defines the downstream part.
    The bearing support also comprises a bypass duct opening into the bypass enclosure and passing through the frustoconical part, said bypass conduit passing through the outer shell to open into the bypass enclosure at the level of the second part which defines the part downstream.
    The bypass pipe projects externally from the second part which defines the downstream part.
    The inner ferrule is fixed to the frustoconical part by bolting.
    The outer shell is fixed to the frustoconical part by shrinking.
    The invention also relates to a turbomachine comprising a bearing support as described above.
    The invention also relates to a method of manufacturing a bearing support as described above, comprising steps of:
    - a) manufacture by foundry of a first part forming the frustoconical part and the inner ring,
    - b) manufacture of a second part forming the downstream part,
    - c) fixing of the second added part on the first part.
    Step c) includes steps to:
    - fixing of the inner ring to the frustoconical part;
    - fixing of the outer ring to the frustoconical part.
    The inner ferrule is fixed to the frustoconical part by shrinking.
    The outer shell is fixed to the frustoconical part by bolting.
    DESCRIPTION OF THE FIGURES
    Other objectives, characteristics and advantages will emerge from the detailed description which follows with reference to the drawings given by way of illustration and not limitation, including:
    - Figures 1, 2 and 3 are views in radial half-section of a bearing support according to the prior art, Figure 1 being a sectional view at the level of no boss, Figure 2 a sectional view at the level of the duct of the oil return duct, and FIG. 3 a sectional view at the level of the drain;
    - Figure 4 is a view in radial half-section of a bearing support according to the invention in a turbomachine;
    - Figure 5 is a view in radial half-section of the downstream part of a bearing support according to the invention;
    - Figure 6 is a view in radial half-section of the bearing support of Figure 5 with the conduit of the oil return conduit and the drain;
    - Figure 7 is a front view of a bearing support according to the invention;
    - Figure 8 is a side view of a bearing support according to the invention.
    DETAILED DESCRIPTION OF THE INVENTION
    In the following text, the terms downstream and upstream are defined with respect to the direction of flow A of the flow in the turbomachine.
    As illustrated in FIG. 4, the compressor and the turbine consist of a first set of fixed parts constituting the stator 60 and a second set of parts, capable of being rotated relative to the stator 60, constituting the rotor 70 The rotor 70 is integrally connected to a rotating shaft 80.
    The rotation of the rotor 70 relative to the stator 60 is made possible by means of a bearing 5, the bearing 5 being a mechanical member supporting and guiding the rotation of the rotor shaft 80.
    The bearing 5 comprises an inner ring of the bearing 51 fixed to the rotor 70 and an outer ring of the bearing 52 fixed to the stator 60 by means of a bearing support 1.
    A bearing 50 is disposed between the inner ring of the bearing 51 and the outer ring of the bearing 52 thus allowing the rotation of the inner ring of the bearing 51 relative to the outer ring of the bearing 52. The bearing 50 is for example of the ball type , with cylindrical rollers or tapered rollers.
    The bearing support 1 supports and guides the rotor 70 in rotation.
    Referring to Figures 4 to 8, the bearing support 1 is a part having a symmetry about the axis A of the turbojet.
    The bearing support 1 comprises at least:
    - A first part 100 defining a frustoconical part 10 and an inner ring 15;
    - a second part 200 defining a downstream part 20.
    The first part 100 is adapted to support the bearing 5.
    The frustoconical part 10 extends by widening upstream.
    The frustoconical part 10 having an upstream end 11 configured to be fixed to the stator, in this case to the inter turbine casing 60, and a downstream end carrying an inner ring 15 configured to cooperate with the outer ring 52 of the bearing 5. The inner ring 15 extends at the downstream end of the frustoconical part 11 towards the interior thereof.
    The frustoconical part 10 has an upstream flange 16 configured to be fixed to a ferrule carrying a sealing girder 17 cooperating with the outer ring of the bearing 52.
    Referring to Figure 5, the frustoconical part 10 has at its downstream end but upstream of the inner ring 15 an outer ring 16 and an inner ring 17. The outer ring 16 extends around the inner ring 17. The ring outer 16 extends from the frustoconical part 10 at a distance from the inner ring 15 of between 10% and 30% of the distance between the upstream end and the downstream end of the frustoconical part 10. The inner ferrule 17 extends from the frustoconical part 10 at a distance from the inner ring 15 of between 5% and 15% of the distance between the upstream end and the downstream end of the frustoconical part 10.
    The length of the outer shell 16 of the frustoconical portion 10 is less than 10% of that of the outer shroud 31 of the downstream portion 20. The length of the inner ferrule 17 of the frustoconical portion 10 is less than 10% of that of the inner shell 21 of the downstream part 20.
    Holes 18 are formed in the frustoconical part 10 between the outer shell 16 and the interior shell 17.
    Other orifices 19 are formed in the frustoconical part 10 between the inner ring 17 and the inner ring 15.
    The second part 200 is adapted to cooperate with the rotor 70 to seal the lubrication chamber 27.
    The downstream part 12 comprises an outer shroud 31 and an inner shroud 21 having a symmetry about the axis A of the turbojet engine.
    The outer ferrule 31 surrounds the inner ferrule 21.
    The inner ferrule 21 is configured to cooperate with the inner ring of the bearing 51 to define with it a lubrication chamber 27. For this purpose, the inner ferrule 21 carries at its downstream end on its internal surface a sealing tendril 26. This the latter cooperates with the inner ring of the bearing 51 to form a sealing system ensuring the sealing of the lubrication chamber 27.
    The outer shroud 31 is configured to cooperate with the rotor 70 to define a bypass enclosure 37. The bypass enclosure 37 makes it possible to seal the lubrication chamber 27. For this purpose, the outer shroud 31 carries to its downstream end on its internal surface a sealing spin 36. The latter cooperates with the rotor 70 to form a sealing system ensuring the sealing of the bypass enclosure 37.
    The first part 100 and the second part 200 are two parts fixed to each other during assembly. The first part 100 is preferably a foundry part. The second part 200 is preferably a foundry part but can also be a part obtained by laser fusion or a mechanically welded or mechanically brazed assembly of sheets and / or forged components.
    The second part 200 is attached to the first part 100 at the level of the outer shroud 31 and the inner shroud 21. For this purpose, the outer shroud 31 and the inner shroud 21 are fixed to the frustoconical part 10. The area of the frustoconical part 10 to which the ferrules 21, 31 are fixed is located upstream of the inner ring 15.
    The internal ferrule 21 is preferably fixed to the frustoconical part 10 10 by a hooped connection 7.
    To this end, with reference to FIG. 5, the downstream end of the inner ring 17 of the frustoconical part 10 has a shape complementary to the upstream end of the inner ring 21 of the downstream part 20, so as to allow tight fitting of the downstream end of the inner ring 17 of the frustoconical part 10 in the upstream end of the inner ring 21 of the downstream part
    20.
    The assembly can be carried out by heating the inner shroud 21, cooling the inner shroud 17 or by a combination of the two.
    An annular seal 75 positioned between, on the one hand, the inner shroud 20 of the frustoconical part 10 and, on the other hand, the inner shroud 21 of the downstream portion 20, ensures the radial sealing of the chamber lubrication 27.
    The seal is said to be radial because it is ensured by radial compression between the inner shell 17 of the frustoconical part 10 and the internal shell 21 of the downstream part 20.
    The radial seal is more reliable than an axial seal, which is necessary here because the seal of the lubrication chamber 27 is sensitive and in particular more sensitive than that of the bypass enclosure 37.
    ίο
    The outer ferrule 31 is preferably fixed to the frustoconical part 10 by a bolted connection 6. The fact that the outer ferrule 31 is fixed to the frustoconical part 10 by a bolted connection 6 makes it possible to limit the hyperstatism by making it possible to limit the stresses on assembly, which does not remove a degree of mobility of a part several times.
    The outer shell 31 could alternatively be fixed by hooping.
    Referring to Figure 5, the outer ferrule 31 has an annular flange 62 which extends from the upstream end of the outer ferrule 31 externally radially with respect thereto.
    The outer shell 16 of the frusto-conical part 10 also carries an annular flange 61 which extends from the downstream end of the outer shell 16 of the frusto-conical part 10 externally radially with respect thereto.
    The bolted connection 6 comprises bolts 63, each bolt consisting of a threaded screw, and a tightening nut. Each bolt 63 passes through, on the one hand, the annular flange 62 of the outer shroud 31 of the downstream part 20 and, on the other hand, the annular flange 62 of the outer shroud 16 of the frustoconical part 10, so as to create a complete, rigid and removable connection between parts 100 and 200.
    An annular seal 75 positioned between, on the one hand, the annular flange 62 of the outer shroud 31 of the downstream part 20 and on the other hand the annular flange 61 of the outer shroud 16 of the frustoconical part 10, ensures the axial sealing of the bypass enclosure 37.
    Sealing is said to be axial because it is ensured by axial compression between the annular flange 62 of the outer shroud 31 of the downstream part 20 and the annular flange 61 of the outer shroud 16 of the frustoconical part 10.
    The axial seal is less reliable than a radial seal, but it is sufficient here because the seal of the bypass enclosure 37 is less sensitive and in particular less sensitive than that of the lubrication chamber 27. In addition, the axial sealing, allows, in combination with the hoop connection 7, to limit hyperstatism, as explained above.
    Referring to Figure 6, the frustoconical part 10 has one or more 5 oil recovery duct (s) 28 opening into the lubrication chamber
    27. The oil recovery pipes 28 allow ventilation and pressure equalization in the oil chamber. They allow the recovery of excess oil accumulated in the lubrication chamber 27.
    The frusto-conical part 10 also has one or more bypass conduits 38 (also called a drain) opening into the bypass enclosure 37. The bypass conduits 38 allow the recovery of the oil which could have been introduced into the bypass enclosure 37.
    As illustrated in FIGS. 7 and 8, the frustoconical part 10 has an orifice 13 suitable for the passage of the oil recovery conduit 38 and of the oil recovery conduit 28. The frustoconical part 10 can also have two separate orifices, one suitable for the passage of the oil recovery pipe and the other for the passage of the oil recovery pipe
    28.
    The oil recovery conduit 28 opens into the lubrication chamber 27 by passing through the frustoconical part 10 at the orifice 13. The oil recovery conduit 28 passes through the outer shroud 31 and the inner shroud 21 to open into the lubrication chamber 27 at the level of the second part which defines the downstream part 20.
    The oil recovery duct 28 protrudes externally from the second part which defines the downstream part 20.
    The bypass duct 38 opening into the bypass enclosure 37 at the downstream part 20 by crossing the frustoconical part 10 at the orifice 13. The bypass duct 38 crosses the outer ring 31 to open into the enclosure bypass 37 at the second part 200 which defines the downstream part 20.
    The lubrication chamber 27 makes it possible to contain the oil injected at the level of the bearing 5.
    The lubrication chamber 27 is under overpressure relative to atmospheric pressure. This overpressure produced by the compressor of the turbomachine allows the lubrication liquid such as oil which is introduced into the lubrication chamber 27 to remain confined in this lubrication chamber 27 due to the pressure difference.
    A recovery pump makes it possible, via the oil recovery conduit 28, to recover the lubrication liquid mixed with the air and to convey it to a lubrication liquid-air separator, after having cooled it in an appropriate cooling device. At the outlet of the separator, the lubrication liquid is returned to the tank, while the air is discharged directly outside through an exhaust port.
    The bypass duct 38 projects externally from the second part which defines the downstream part 20.
    The bearing support can in particular be manufactured according to a process comprising the following steps.
    at)
    b)
    c) manufacturing the first part 100, manufacturing the second part 200, fixing the first part 100 to the second part 200.
    Step a) of manufacturing the first part 100 is preferably done by one-piece foundry. Indeed, the first part 100 transmits the forces from the bearing to the inter-turbine casing, its mechanical strength is therefore crucial. The one-piece foundry guarantees the necessary mechanical solidity.
    The second part 200 is more complex to manufacture than the first part 100, but its solidity is less sensitive than that of the first part because it does not have a mechanical role of force transmission. Step b) for manufacturing the second part 200 can also be manufactured by laser fusion, or not be manufactured in one piece but with fittings of sheet metal parts or forgings welded or brazed. These manufacturing processes are easier to implement even if they do not guarantee the same mechanical strength to the manufactured part.
    Step c) is carried out by positioning the downstream part 20 relative to the frustoconical part 10 so as to pass the oil recovery conduit 28 and the bypass conduit 38 into the orifice 13 of the frustoconical part 10, then by fixing the inner ferrule 21 and the outer ferrule 31 on the frustoconical part 10.
    The inner shell 21 is preferably fixed to the frustoconical part 10 by bolting.
    The outer shell 31 is preferably fixed to the frustoconical part 10 by shrinking.
    权利要求:
    Claims (12)
    [1" id="c-fr-0001]
    1. A bearing support (1) for a turbomachine adapted to support a bearing (5) of a rotor (70), the bearing support (1) comprising:
    - a frustoconical part (10) having an upstream end configured to be fixed to the inter-turbine casing (60) and a downstream end carrying an inner ring (15);
    - a downstream part (20) comprising an external ferrule (31) and an internal ferrule (21) which extend from the frustoconical part (10), the internal ferrule (21) defining with the bearing (5) a chamber lubrication (27), the inner ring (21) and the outer ring (31) defining between them a bypass enclosure (37);
    the zone of the frustoconical part from which the ferrules (21, 31) extend being located upstream of the inner ring (15); the inner ring (15), the outer ferrule (31) and the inner ferrule (21) together defining three concentric skins in the same area of the bearing support (1);
    the bearing support (1) of a turbomachine being characterized in that it consists of at least two parts fixed to each other during assembly, the first (100) of these parts defining the frustoconical part (10) and the inner ring (15) and being adapted to support the bearing (5), the second part (200) defining the downstream part (20) and being adapted to cooperate with the bearing (5) to seal the chamber lubrication (27), the second part (200) being attached and fixed to the first part (100) at the level of the outer ring (31) and the inner ring (21).
    [2" id="c-fr-0002]
    2. bearing support (1) according to the preceding claim, further comprising an oil recovery conduit (28) opening into the lubrication chamber (27) and passing through the frustoconical part (10), said recovery conduit oil (28) passing through the outer ring (31) and the inner ring (21) to open into the lubrication chamber (27) at the level of the second part (200) which defines the downstream part (20).
    [3" id="c-fr-0003]
    3. bearing support (1) according to the preceding claim, wherein the oil recovery duct (28) projects externally from the second part (200) which defines the downstream part (20).
    [4" id="c-fr-0004]
    4. bearing support (1) according to one of the preceding claims, further comprising a bypass duct (38) opening into the bypass enclosure (37) and passing through the frustoconical part (10), said bypass duct ( 38) passing through the outer ring (31) to open into the bypass enclosure (37) at the level of the second part (200) which defines the downstream part (20).
    [5" id="c-fr-0005]
    5. bearing support (1) according to the preceding claim, wherein the bypass duct (38) projects externally from the second part (200) which defines the downstream part (20).
    [6" id="c-fr-0006]
    6. Bearing support (1) according to one of the preceding claims, in which the inner ferrule (21) is fixed to the frustoconical part (10) by bolting.
    [7" id="c-fr-0007]
    7. Bearing support (1) according to one of the preceding claims, in which the outer shell (31) is fixed to the frustoconical part (10) by shrinking.
    [8" id="c-fr-0008]
    8. Turbomachine, in particular turbojet engine, comprising a bearing support (1) according to one of the preceding claims.
    [9" id="c-fr-0009]
    9. Method of manufacturing a bearing support (1) according to one of claims 1 to 7, comprising steps of:
    - a) foundry fabrication of a first part (100) forming the part
    5 frustoconical (10) and the inner ring (15),
    - b) manufacturing a second part (200) forming the downstream part (20),
    - c) fixing the second part (200) attached to the first part (100).
    [10" id="c-fr-0010]
    10. Method of manufacturing a bearing support (1) according to the preceding claim, in which step c) comprises steps of:
    - fixing of the inner ferrule (21) to the frustoconical part (10);
    - fixing of the outer ring (31) to the frustoconical part (10).
    15
    [11" id="c-fr-0011]
    11. Method of manufacturing a bearing support (1) according to the preceding claim, in which the inner ferrule (21) is fixed to the frustoconical part (10) by shrinking.
    [12" id="c-fr-0012]
    12. Method of manufacturing a bearing support (1) according to one of claims 10 or 11, in which the outer shell (31) is fixed to the frustoconical part (10) by bolting.
    1/5
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    同族专利:
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    FR3053728B1|2022-01-21|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP1340902A2|2002-03-01|2003-09-03|General Electric Company|Gas turbine with frame supporting counter rotating low pressure turbine rotors|
    US20040168443A1|2003-02-27|2004-09-02|Moniz Thomas Ory|Methods and apparatus for assembling gas turbine engines|
    EP2090764A1|2008-02-13|2009-08-19|Snecma|Oil recovery device|
    EP2192275A2|2008-11-28|2010-06-02|Pratt & Whitney Canada Corp.|Mid turbine frame system for gas turbine engine|
    WO2014058455A1|2012-10-09|2014-04-17|United Technologies Corporation|Bearing support stiffness control|WO2019180375A1|2018-03-23|2019-09-26|Safran Aircraft Engines|Turbojet bearing support produced by additive manufacturing|
    FR3089547A1|2018-12-06|2020-06-12|Safran Aircraft Engines|Improved bearing support|
    FR3107550A1|2020-02-24|2021-08-27|Safran Aircraft Engines|MOUNTING PROCESS OF AN AIRCRAFT TURBOMACHINE MODULE|
    法律状态:
    2017-04-28| PLFP| Fee payment|Year of fee payment: 2 |
    2018-01-12| PLSC| Publication of the preliminary search report|Effective date: 20180112 |
    2018-06-21| PLFP| Fee payment|Year of fee payment: 3 |
    2020-06-23| PLFP| Fee payment|Year of fee payment: 5 |
    2021-06-23| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1656534|2016-07-07|
    FR1656534A|FR3053728B1|2016-07-07|2016-07-07|TWO-PIECE BEARING SUPPORT|FR1656534A| FR3053728B1|2016-07-07|2016-07-07|TWO-PIECE BEARING SUPPORT|
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