• 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 support providing a complete connection between a degassing tube (3) and a turbine shaft (2), said support comprising a plurality of external contact surfaces (41a) intended to bear against the inner walls of the turbine shaft for securing the degassing tube relative thereto, characterized in that the different bearing surfaces are each bordered by at least one elastomer insert (41g) which contributes to the protection of the turbine shaft when the insertion of the support within it.
    公开号:FR3058480A1
    申请号:FR1660752
    申请日:2016-11-07
    公开日:2018-05-11
    发明作者:Noel Durand Didier；Daniel Delaporte Nicolas；Emmanuel LINQUETTE
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    GENERAL TECHNICAL AREA AND PRIOR ART
    The invention relates to a support ensuring a complete connection between a turbine shaft and a degassing tube of a turbojet engine.
    The lubrication function of the rolling elements of a turbojet engine is conventionally provided by an atmosphere with oil droplets in compartments containing these rolling elements. In order to ensure ventilation, a flow of gas passes through these enclosures and then passes through oil separators whose function is to separate the oils from the gases. The oils are captured by centrifugal effect to be then reinjected into the compartments of the rolling elements.
    The gas flow is evacuated via a degassing tube. This is located within the turbine shaft, concentrically to it. It is linked to it by one or more built-in links.
    An example of coupling is for example proposed in the patent application FR. 2,957,974 in the case of a turbine shaft with constant internal diameter.
    On certain turbomachinery, the internal diameter of the turbine shaft is subject to change. The installation is then ensured by two central support systems. The coupling elements are placed in such a way that they divide the degassing tube into three parts, thereby reducing the span length.
    Typically, these central support systems consist of a split support, a conical socket with thread and a nut. They are mounted blind in the turbine shaft and positioned before installing the degassing tube. The coupling is then carried out by expansion of the split support via the pressure of the screwed nut towards the conical surface, inducing an increase in the outside diameter of the support until a tight fit is obtained between the support and the turbine shaft.
    During the positioning of the support systems, it sometimes happens that scratches are caused on the internal surface of the turbine shaft. The wear and tear caused by the operating conditions of the turbine shaft causes cracks to form on these scratches. This degradation of the structure of the turbine shaft can lead to its rupture.
    OVERVIEW OF THE INVENTION
    A general aim of the invention is to overcome the drawbacks of the support systems of the state of the art.
    In particular, one of the aims of the invention is to prevent the degradation of the turbine shaft due to scratches.
    Another object of the invention is to facilitate the mounting of the support systems in the turbine shaft, thereby reducing the duration and incidentally the cost of the operations.
    Another aim is to facilitate the dismantling of the systems, thereby reducing the risk of degradation during maintenance operations.
    According to one aspect, the invention provides a split support ensuring a complete connection between a degassing tube and a turbine shaft, said support comprising a plurality of external contact surfaces intended to come to bear on the interior walls of the turbine shaft for securing the degassing tube with respect to it, characterized in that the different bearing surfaces are each bordered by at least one elastomer insert which contributes to the protection of the turbine shaft during the insertion of the support therein.
    In this way, the risks of metal / metal contact between the turbine shaft and the split support are limited.
    Such a support is advantageously supplemented by the following different characteristics taken alone or in combination:
    - It comprises a plurality of lateral extra thicknesses which extend on either side of the external contact surfaces and at the level of which elastomer inserts are arranged.
    - It comprises a plurality of dimples made in the lateral extra thicknesses, said dimples being intended to receive the inserts made of elastomer. The dimples thus ensure the axial and tangential setting of the elastomer inserts.
    - The contact surfaces which it comprises extending tangentially to a first virtual cylinder, the external edges of the recesses extend according to a second virtual cylinder concentric with the first and of smaller radius. In this way, the edges of the recesses do not generate any additional risk of contact between the support and the turbine shaft during the tilting or straightening of the support during mounting or dismounting of the latter.
    - The elastomer inserts can be mounted glued in the recesses. This option allows the inserts to be kept in the correct position during the various assembly or disassembly phases of the support systems.
    - The elastomer inserts can be fitted tight in the recesses. This option also allows the inserts to be kept in the correct position during different stages of assembly or disassembly of the support systems.
    The invention also provides a support system ensuring a complete connection between a degassing tube and a turbine shaft, said support system comprising such a support, a nut intended to exert an axial thrust force on said support by screwing on the portion threaded with a conical sleeve, said sleeve having a conical portion intended to transform the axial thrust into radial expansion of said support.
    It also offers a degassing tube and turbine shaft assembly secured by a support system comprising such a support.
    It also relates to a turbomachine comprising a degassing tube and turbine shaft assembly secured by a support system comprising such a support and more specifically a turbomachine comprising a shaft with an evolving internal diameter secured to a nominally internal cylindrical part concentric with a support system such support.
    PRESENTATION OF THE FIGURES
    Other characteristics and advantages of the invention will emerge from the description which follows, which is purely illustrative and not limiting, and should be read with reference to the appended figures in which:
    - Figure 1 shows a partial sectional view of a turbojet engine known from the prior art;
    - Figure 2 shows a sectional view of the central support systems and their positions relative to the turbine shaft and the degassing tube;
    - Figure 3 shows a partial sectional view of the degassing tube and a central support;
    - Figure 4 represents an isometric 3D modeling of the support system mounted on the degassing tube
    - Figure 5 shows a partial view of a 3D modeling of a split support, centered on a contact surface;
    - Figure 6 shows a partial sectional view of a split support, centered on a contact surface;
    - Figure 7 shows a partial sectional view of the turbine shaft and the degassing tube during assembly of a support system, as well as the tools used.
    DESCRIPTION OF ONE OR MORE MODES OF IMPLEMENTATION AND
    OF REALIZATION
    General
    With reference to FIG. 1, a turbojet engine T in accordance with an embodiment of the invention comprises, in a conventional manner, a low pressure compressor Cbp, a high pressure compressor Chp, a combustion chamber Cc, a high pressure turbine Thp, a low pressure turbine Tbp, and an exhaust nozzle Te.
    The turbine shaft 2 extends along an axis A which is the overall axis of the turbojet engine T. The concepts of longitudinal and radial in the following description will relate to this axis A. The concepts of upstream and downstream in the following description will relate to the direction of flow of the fluids in the degassing tube.
    The turbine shaft 2 is hollow.
    A degassing tube 3 extends within the turbine shaft 2. Its function is to guide downstream the flow of ventilation gas from the rolling elements.
    The degassing tube 3 extends along the axis of the turbojet engine, concentrically with the turbine shaft 2. It is hollow and symmetrical in revolution, and comprises a plurality of successive hollow sections: an upstream section 31, a central section 32 and a downstream section 33.
    The upstream section 31 has a plurality of holes intended to allow the evacuation of the gases in the degassing tube, while the downstream section 33 opens onto a gas evacuation mouth. These two upstream and downstream sections 31 and 33 have diameters which vary in their length. The central section 32 between the two is of constant diameter.
    Section assembly
    The upstream and downstream sections 31 and 33 are connected to the central section 32 and locked by clamping in the turbine shaft 2 by the assembly system 4 which is illustrated in FIGS. 2 and 3 in the case of the downstream section 33.
    With reference to FIG. 2, this assembly system 4 comprises a part 41 forming a central support, a conical sleeve 42 and a nut 43.
    The part 41 is a split annular part of the shaft support type. It has four lateral external contact surfaces 41a. These ranges 41a are distributed on four sides of the periphery of said piece 41 being two to two diametrically opposite.
    The internal annular surface of the part 41 has an upstream conical portion 41b which widens from downstream to upstream. It ends with a cylindrical downstream bearing 41c.
    Said socket 42 has a cylindrical interior shape. Its external surface presents, from upstream to downstream:
    a conical upstream portion 42a intended, during tightening, to cooperate in friction with the internal conical portion 41b of the part 41 forming a split support,
    a clearance groove 42g between the downstream end of the conical portion and the upstream end of a threaded portion 42b,
    a threaded portion 42b, which extends in the extension of said conical portion 42a, intended to cooperate with a nut 43,
    - a downstream end having notches 42d, intended to serve as an interface with a toothed rod 7 (detailed in FIG. 7 and in the mounting method) during the mounting phase of the support system 4.
    The nut 43 has a tapped internal surface 43t intended to interact with the threaded portion 42b of the conical sleeve 42, and an upstream surface 431 which exerts pressure against the downstream surface 411 of the split support 41 when the nut is tightened 43 on the conical sleeve 42.
    With reference to FIG. 3, the sections 32 and 33 of the degassing tube 3 are juxtaposed with a reinforced portion 5, supporting the force of the support system 4.
    This reinforced portion 5 comprises at its upstream 51 and downstream 53 ends a short centering for positioning the sections 32 and 33 of the degassing tube 3. The central part 52 of the reinforced portion 5 has two contact thicknesses 521 and 522 of revolution, configured to strengthen the structure of the degassing tube 3 where the clamping force of the sleeve 42 caused by the extension of the split support 41 will be applied. Between these two extra thicknesses is inserted an O-ring 54.
    The assembly of the support system 4 is therefore carried out by inserting the conical sleeve 42 into the split support 41 from upstream to downstream, until reaching an axial abutment position consequent to the conical surface contact between the two parts. . The nut 43 is then screwed onto the threaded portion 42b of the conical sleeve 42 from downstream to upstream. The assembly is secured in a configuration where the nut 43 makes a clamping force on the split support 41, thus keeping the latter in position axially and radially relative to the conical sleeve 42.
    Split center support
    Referring to Figure 4, the four contact surfaces 41a are separated in pairs by two long flats 411 and two short flats 41m diametrically symmetrical.
    In order to reduce the rotating masses, the downstream and upstream surfaces of the support 41 each have a toric groove 41t.
    Inserts 41g of elastomer are distributed on either side of the contact surfaces 41a.
    More specifically, an insert 41g is presented as a flat joint arc (ring of rectangular section), comprising two flat lateral surfaces, an internal surface with a radius of curvature less than the radius of curvature of the external surface and two flat ends. Each stop has a leave, facilitating the different stages of mounting the inserts 41g in the split support 41 and then of the support system 4 in the turbine shaft 2.
    The elastomer inserts 41g can be mounted in recesses 41f (detailed in FIG. 5) made on either side of each contact surface 41a. They then have an external arc length slightly greater than that of the contact spans 41a in order to cover the entire edge representing a risk during assembly.
    These inserts are for example made of an elastomeric material DMD5072 identical to that of the O-ring 54.
    Referring to Figure 5, the elastomer inserts 41g are mounted in recesses 41f machined in thickeners 41d around the contact surfaces 41a.
    The dimples 41f have a geometry similar to the elastomer inserts 41g, thereby comprising two flat side surfaces of a shape similar to the side surfaces of the inserts but of a smaller height, a curved bottom having a radius of curvature similar to the radius of curvature of the internal surface of one and two flat ends similar to those of the inserts.
    The elastomer inserts 41g can be mounted glued in the recesses 41f to ensure that they are held in position during certain handling steps.
    In another possible embodiment, the dimensions of the recesses 41f are smaller than the dimensions of the elastomer inserts 41g, so as to mount the inserts by clamping to ensure that they are held in position during certain handling steps.
    With reference to FIG. 6, the contact surfaces 41a have lateral thickenings 41d in which recesses 41f are machined intended to receive inserts made of elastomer 41g. The lateral extra thicknesses have dimensions greater than those of the inserts.
    The extra thicknesses are located on either side of each contact surface 41a and do not extend over the entire periphery of the split support 41, in a logic of mass limitation. Considering the lateral extra thicknesses 41d tangent internally to a virtual cylinder, the radius of this cylinder is less than that of the cylinder tangent externally to the contact surfaces 41a.
    In the same way, the external abutment edges 41h are tangent to a virtual cylinder having a radius less than the radius of the virtual cylinder tangent to the contact surfaces 41a.
    The radius of the virtual cylinder tangent to the contact surfaces 41a is less than the interior radius of the turbine shaft 2, corresponding to a mounting step before expansion of the split support 41. The radius of the external abutment edges 41h is less than the radius of the contact surfaces 41a to avoid generating an additional risk of damage to the turbine shaft 2 when the support system 4 is straightened.
    The geometry of the support 41 gives it particular advantages in the context of an evolving diameter shaft, however the coupling of the degassing tube in the shaft can be carried out in the same way if the internal diameter of the turbine shaft is constant. , as soon as it is greater than the diameter of the virtual cylinder tangent to the contact surfaces 41a (before expansion of the support 41).
    Mounting
    With reference to FIG. 7, in order to position the support system 4, it is inserted inclined into the turbine shaft 2 by its downstream end which has an internal diameter less than the internal diameter of its central portion . The width of the split support 41 at the level of the long flats is therefore less than the minimum internal diameter of the turbine shaft 2, thereby allowing its insertion into the turbine shaft 2.
    The support system 4 is then inserted on a support rod 6 designed for this application, itself inserted over the entire length of the turbine shaft from its upstream end. Said support rod 6 is equipped with a stop 61 for making an axial stop against the upstream surface of the turbine shaft 2.
    The support system 4 is then brought into position by sliding along said support rod 6, pushed by means of a toothed rod 7 whose teeth 71 come to match the notches 42d of the conical sleeve 42 and thus ensure its position tangential. Said toothed rod 7 is hollow and has an internal diameter greater than the diameter of the support rod 6, allowing the toothed rod 7 to slide around the rod 6 during the mounting of the support system 4.
    The nut 43 is then screwed onto the conical sleeve 42 by means of the toothed rod 7, causing the straightening then the expansion of the split support 41 until generating sufficient friction in contact with the turbine shaft 2 to ensure a complete connection. with the latter.
    These last two operations, during which the support system 4 is brought into position by sliding in the turbine shaft 2 then straightened and expanded by clamping on the conical sleeve 42, no longer present any risk of degradation of the internal surface of the turbine shaft 2, the elastomer inserts 41g now preventing metal / metal contact and eliminating any risk of degradation linked to this phenomenon. Operations can therefore be carried out more quickly and more reliably.
    The reinforced upstream portion 5 is then inserted into the upstream support 4, before screwing the nut 43 onto the conical sleeve 42 and generating a tightening force joining the reinforced portion 5 and the turbine shaft 2. The central section of the degassing tube 32 is then inserted, followed by the downstream support system according to the same method as the upstream support system.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Support ensuring a complete connection between a degassing tube (3) and a turbine shaft (2), said support comprising a plurality
    5 of external contact surfaces (41a) intended to come into abutment on the internal walls of the turbine shaft in order to secure the degassing tube with respect thereto, characterized in that the different surfaces are each bordered by at least one elastomer insert (41g) which contributes to the protection of the io turbine shaft during the insertion of the support therein.
    [2" id="c-fr-0002]
    2. Support according to claim 1, characterized in that it comprises a plurality of lateral thickeners (41d) which extend on either side of the external contact surfaces (41a) and at which the inserts are arranged elastomer (41g).
    15
    [3" id="c-fr-0003]
    3. Support according to the preceding claim, characterized in that it comprises a plurality of dimples (41f) made in the lateral extra thicknesses (41d), said dimples receiving the inserts made of elastomer (41g).
    [4" id="c-fr-0004]
    4. Support according to claim 3, characterized in that, the
    20 contact surfaces (41a) extending tangentially to a first virtual cylinder, the external edges (41h) of the recesses extend according to a second virtual cylinder concentric with the first and of smaller radius.
    [5" id="c-fr-0005]
    5. Support according to claim 3 or claim 4, characterized
    25 in that the elastomer inserts (41g) are mounted glued in the recesses (41f).
    [6" id="c-fr-0006]
    6. Support according to claim 3 or claim 4, characterized in that the elastomer inserts (41g) are mounted tight in the recesses (41f).
    [7" id="c-fr-0007]
    7. Support system ensuring a complete connection between a degassing tube (3) and a turbine shaft (2), said support system comprising a support as defined in one of claims 1 to 6, a nut (43) intended to exert an axial thrust force
    5 on said support by screwing onto the threaded portion of a conical sleeve (42), said sleeve having a conical portion intended to transform the axial thrust into radial expansion of said support.
    [8" id="c-fr-0008]
    8. degassing tube and turbine shaft assembly secured by a support system io (4) comprising a support as defined in one of claims 1 to 6.
    [9" id="c-fr-0009]
    9. Turbomachine comprising a degassing tube (3) and turbine shaft (2) assembly joined by a support system (4) comprising a support as defined in one of claims
    15 1 to 6.
    [10" id="c-fr-0010]
    10. Turbomachine comprising a shaft with an evolving internal diameter secured to a nominally cylindrical internal concentric part thanks to a support system (4) comprising a support as defined in one of claims 1 to 6.
    1/4 <CI
    2/4
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    同族专利:
    公开号 | 公开日
    FR3058480B1|2018-12-07|
    US20180128180A1|2018-05-10|
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    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    WO2002044538A2|2000-11-30|2002-06-06|Snecma Moteurs|Device for centring a tube in a turbine shaft|
    FR3008135A1|2013-07-08|2015-01-09|Snecma|CENTERING A WORKPIECE WITHIN A ROTOR SHAFT IN A TURBOMACHINE|
    WO2016121193A1|2015-01-26|2016-08-04|株式会社Ihi|Center vent tube aligning mechanism and center vent tube support device|JP2016138458A|2015-01-26|2016-08-04|株式会社Ihi|Center vent tube core adjustment mechanism and center bent tube supporting device|FR2957974B1|2010-03-26|2013-04-12|Snecma|TURBOREACTOR DEGASSING TUBE, METHOD OF MOUNTING SUCH TUBE AND TURBOREACTOR WITH SUCH A TUBE|US11162457B2|2017-08-11|2021-11-02|General Electric Company|Turbine fan system and method|
    FR3094031B1|2019-03-18|2021-05-14|Safran Aircraft Engines|SET FOR A TURBOMACHINE|
    法律状态:
    2017-10-19| PLFP| Fee payment|Year of fee payment: 2 |
    2018-05-11| PLSC| Publication of the preliminary search report|Effective date: 20180511 |
    2018-10-24| PLFP| Fee payment|Year of fee payment: 3 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 4 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 5 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1660752|2016-11-07|
    FR1660752A|FR3058480B1|2016-11-07|2016-11-07|SUPPORT PROVIDING A COMPLETE CONNECTION BETWEEN A TURBINE TREE AND A TURBOREACTOR DEGASSING TUBE|FR1660752A| FR3058480B1|2016-11-07|2016-11-07|SUPPORT PROVIDING A COMPLETE CONNECTION BETWEEN A TURBINE TREE AND A TURBOREACTOR DEGASSING TUBE|
    US15/803,271| US10302016B2|2016-11-07|2017-11-03|Support providing a complete connection between a turbine shaft and a degassing pipe of a turbojet|
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