• 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 turbomachine casing (10) having an annular ferrule (14) provided with an orifice (32) on the periphery of which is fixed a first end (38) of a bellows (34) elastically deformable in one direction. radial. A line pipe (18) is engaged with an annular clearance in the hole (32) of the wall (14) and in the bellows (34) and is attached to a second end (40) of the bellows (34) opposite to the first end (38).
    公开号:FR3041686A1
    申请号:FR1559304
    申请日:2015-09-30
    公开日:2017-03-31
    发明作者:Kevin Auber；Maelle Barsi-Palacio；Romain Dumas；Gauthier Cousin
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    DEVICE FOR SUPPORTING A PIPE IN A
    TURBOMACHINE
    The present invention relates to a turbomachine casing and a turbomachine comprising such a casing.
    Conventionally, the incoming air flow is divided into a primary annular air flow and a secondary annular air flow, the primary air flow flowing in a low pressure compressor, a high pressure compressor, a combustion chamber, a high pressure turbine and a low pressure turbine. The secondary air flow bypasses the engine and joins at the output of the turbomachine the flow of hot gases ejected by the turbine.
    Such a turbomachine comprises a turbine structural casing arranged at the outlet of the low pressure turbine. This downstream casing comprises an outer annular ferrule, an inner annular ferrule and an annular intermediate ferrule arranged between the inner and outer annular ferrules. The inner, intermediate and outer ring ferrules comprise arms extending substantially perpendicularly to the annular ferrules and serving for the passage of servitudes such as fluid circulation pipes. The inner annular shell and the intermediate ferrule together define the annular flow vein of the primary air flow. The annular annular ferrule and the outer annular ferrule together define the annular flow vein of the secondary air flow.
    In order to pass a pipe through an arm of the casing, the annular ferrules comprise orifices in which articulated joints are engaged, for example by means of ball joints. The pipe, for example formed of a plurality of tubes, successively passes through the ball joints of the inner, intermediate and outer ring ferrules and can thus pivot angularly with respect to the axis of the mounting hole of the ball joint, which allows the facilitate mounting of the tube in the inner, intermediate and outer shells.
    However, in operation, the outer annular ferrule and the intermediate annular ferrule move axially relative to each other under the effect of consecutive differential expansions of a higher temperature in the primary air vein than in the vein secondary air. The use of ball joints is insufficient to ensure the mechanical integrity of the rigid pipes. It is therefore necessary to use more flexible pipes which must nevertheless withstand high temperatures, which requires the use of thermally insulating materials which are expensive and makes assembly more complicated. The invention aims in particular to provide a simple, effective and economical solution to the problems of the prior art described above. For this purpose, it proposes a turbomachine casing comprising an annular ferrule provided with an orifice on the circumference of which is fixed a first end of a bellows elastically deformable in a radial direction, a tube being engaged with an annular clearance in the port of the wall and in the bellows and being attached to a second end of the bellows opposite the first end.
    In operation, the portion of the tube located near the first end of the bellows can thus move relative to the orifice of the passage of the tube and to the bellows due to the annular clearance of mounting the tube in the orifice and in the bellows . The elastic deformation capacity in the radial direction of the bellows makes it possible to give flexibility to the zone of connection of the tube to the bellows.
    According to another characteristic of the invention, the tube may be attached to a sealing member engaged inside the second end of the bellows. The connection of the tube with the bellows is thus performed by an intermediate piece.
    According to yet another characteristic of the invention, the member comprises an annular portion engaged sealingly inside a cylindrical wall of the second end of the bellows.
    The outer face of the annular portion may comprise an annular groove housing a seal, a clamping element clamping the cylindrical wall of the bellows on the annular portion of the member. The clamping member may be a tangent screw collar, for example.
    In practice, the first end of the bellows can be fixed to the ferrule by means of a radial flange. Fixing can be done by bolting for example.
    To ensure the deformation of the bellows in the radial direction, the latter may comprise annular corrugations extending along the axis of the bellows. The invention also relates to a casing in which the annular shell is an outer annular shell defining externally an annular flow vein of a secondary air flow, the bellows extending radially outwardly from the outer surface of said annular shell. outer ring ferrule.
    The tube can pass through a ball joint engaged in an orifice of an annular ferrule defining internally the secondary annular vein. The invention may also relate to a turbomachine, such as a turbojet, comprising a housing as described above, arranged downstream of a low pressure turbine. The invention will be better understood and other details, advantages and characteristics of the invention will appear on reading the following description given by way of non-limiting example, with reference to the accompanying drawings, in which: FIG. schematic sectional view of a downstream casing of a low pressure turbine; - Figure 2 is a schematic sectional view of the attachment of a tube in a bellows according to the invention; - Figure 3 is a schematic sectional view of the attachment of a tube in a bellows according to another embodiment of the invention; - Figure 4 is a schematic view of the embodiment of Figure 3 according to a cutting plane containing the axis of the bellows; FIG. 5 is a schematic perspective and isolated view of the bellows of FIG.
    Referring first to Figure 1 which shows an exhaust casing 10 arranged at the outlet of a low pressure turbine in a turbomachine. In a manner well known to those skilled in the art, the low pressure turbine corresponds to the last propulsion section of a turbojet engine. This exhaust casing 10 comprises a radially inner annular shroud 12 and a radially outer annular shroud 14 and an intermediate annular shroud 16 arranged radially between the inner annular shroud 12 and the outer annular shroud 14. The inner shroud 12 and the shroud intermediate 16 defines respectively internally and externally an annular flow stream of a primary air flow (arrow A). The intermediate ferrule and the outer ferrule respectively delimit internally and externally an annular flow vein of a secondary air flow (arrow B).
    The exhaust casing 10 comprises a plurality of arms 20 extending radially between the inner shell 12 and the outer shell 14 and allow the passage of easements. FIG. 1 shows a tube 18 for the passage of a fluid, such as, for example, oil, air or even fuel, arranged in a radial arm 20 of the exhaust casing 10. The tube 18 passes through each inner 12, intermediate 16 and outer 14 ferrules at an orifice formed in each of said ferrules. More particularly, a ball 22 is engaged in the orifice of the inner wall 12 and a ball 22 is engaged in the orifice of the intermediate wall 16. Each ball 22 comprises a concave outer surface 24 cooperating with a cylindrical wall 26 of the periphery the orifice and a substantially cylindrical central opening 28 in which is engaged the tube 18 of a pipe. Each ball 22 thus makes it possible to orient the tube 18 in the desired manner through the internal 12 and intermediate walls 16.
    According to the invention, the outer end portion 30 of the tube 18 is engaged in an orifice 32 of the outer annular ferrule 14. The orifice 32 of the outer ferrule 14 is dimensioned so that the tube 30 is inserted with an annular game in this one. Thus, the diameter of the orifice 32 is greater than the external diameter of the outer end portion 30 of the tube 18.
    As can be seen more clearly in FIG. 2, a sealing bellows 34 is mounted on the radially outer surface of the outer shell 14. This bellows 34 comprises a wall of revolution 36 which extends, in the example shown in FIGS. , cylindrical between a first end 38 and a second end 40. This wall 36 comprises annular corrugations extending along the axis of the bellows, which allows a deformation of the bellows in a radial direction, that is to say say perpendicular to the axis 42 of the bellows 34.
    The bellows 34 comprises, at a first end, a radial flange 44 extending radially relative to the axis 42 of the bellows 34. This annular flange 44 is fixed by bolting through the outer annular shell 14. As shown in FIG. 3, the first end 40 of the bellows 34 can also be fixed, for example by welding, to a plate 46 bolted to the outer annular shell 14.
    The second end 40 of the bellows 34 comprises a cylindrical wall 48 (FIGS. 2, 4 and 5). A member 50 is engaged inside this cylindrical wall 48. This member 50 comprises an annular portion 52 surrounding a substantially cylindrical tubular portion 54. The annular portion 52 comprises, on its radially outer face, an annular groove 56 of U-section in which is engaged an annular seal 58 such as for example an O-ring. As can be seen in FIGS. 2 and 4, the external surface of the annular portion 52 comes into contact with the radially internal surface of the cylindrical wall 48 of the bellows 34. It is understood that the depth of the annular groove 56 is less than the thickness of the gasket 58, measured in the radial direction, so as to guarantee a crushing thereof between the bottom wall of the groove 56 and the inner surface of the cylindrical wall 48.
    A first end of the tubular portion 54 of the member 50 is welded to the radially outer end of the tube 18. A second end of the tubular portion 54 is welded to another portion of the channel 60.
    As shown in FIG. 2, the tube 18 may be surrounded by a sheath 61 arranged with clearance vis-à-vis the periphery of the orifice 32 of the wall 14 and vis-à-vis the corrugated wall 36 of the bellows 34. The radially outer end of the bellows is attached to the member 50 by any suitable means. The sheath is also visible in FIG. 1, only around the portion of the tube 18 passing through the primary vein (arrow A).
    The cylindrical wall 48 of the second end 40 of the bellows 34 comprises open slots 62. A clamping member 64 is mounted around the cylindrical wall 48 and clamped thereto, the slots 62 ensuring a radial contraction of the cylindrical wall 48. In the embodiments shown in the figures, the clamping member 64 is a collar. tangent screw.
    In the embodiment of Figures 3 and 4, the member 50 comprises an annular recess 66 formed at the junction between the tubular portion 54 and the annular portion 52 and opening towards the second end of the tubular portion 54.
    In operation, the intermediate annular ferrule 16 and the inner ferrule 14 undergo a greater expansion than the outer ferrule 14, due to the circulation of the hot gases from the combustion chamber, which leads to a displacement of the inner ferrules 12 and intermediate 16 relative to the outer shell 14. According to the invention, the pipe 18 of the pipe is engaged with an annular clearance in the orifice 32 of the outer annular shell 14 and in the bellows 34 and is fixed on the tubular part 54 of the member 50, which avoids constraining the tube 18 on the periphery of the orifice 32 and thus allows it to move axially, the tube 18 being held in displacement by the bellows 34 elastically deformable in the radial direction.
    权利要求:
    Claims (9)
    [1" id="c-fr-0001]
    A turbomachine casing (10) having an annular ferrule (14) provided with an orifice (32) on the periphery of which is fixed a first end (38) of a bellows (34) elastically deformable in a radial direction; tube (18) being engaged with an annular clearance in the orifice (32) of the wall (14) and in the bellows (34) and being attached to a second end (40) of the bellows (34) opposite the first end (38).
    [2" id="c-fr-0002]
    2. The housing of claim 1, wherein the tube (18) is attached to a member (50) engaged sealingly within the second end (40) of the bellows (34).
    [3" id="c-fr-0003]
    3. Housing according to claim 2, wherein the member (50) comprises an annular portion (52) sealingly engaged within a cylindrical wall (48) of the second end (40) of the bellows (34). .
    [4" id="c-fr-0004]
    The housing of claim 3, wherein the outer face of the annular portion (52) comprises an annular groove (56) housing a seal (58), a clamping member (64) clamping the cylindrical wall (48). ) of the bellows (34) on the annular portion (52) of the member (50).
    [5" id="c-fr-0005]
    5. Housing according to one of claims 1 to 4, wherein the first end (38) of the bellows (34) comprises a radial flange (44) for attachment to the annular shell (14).
    [6" id="c-fr-0006]
    6. Carter according to claim 5, wherein the bellows (34) comprises a wall of revolution (36) having annular corrugations extending along the axis (42) of the bellows (34).
    [7" id="c-fr-0007]
    7. Carter according to one of the preceding claims, wherein the annular shell is an outer annular shell (14) defining externally an annular flow stream of a secondary air flow, the bellows (34) extending radially. outwardly from the outer surface of said outer annular shell (14).
    [8" id="c-fr-0008]
    8. The housing of claim 7, wherein the tube (18) passes through a ball joint (22) engaged in an orifice of an annular ferrule (16) internally defining the secondary annular vein.
    [9" id="c-fr-0009]
    9. Turbomachine, such as a turbojet, comprising a housing according to one of claims 7 or 8 arranged downstream of a low pressure turbine.
    类似技术:
    公开号 | 公开日 | 专利标题
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    同族专利:
    公开号 | 公开日
    FR3041686B1|2018-08-31|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP1331364A2|2001-12-18|2003-07-30|General Electric Company|Flexible coupling of a service tube to a dual shell bearing housing|
    US20050199445A1|2004-03-09|2005-09-15|Honeywell International Inc.|Apparatus and method for bearing lubrication in turbine engines|
    US20060123796A1|2004-12-13|2006-06-15|Honeywell International Inc.|Secondary flow, high pressure turbine module cooling air system for recuperated gas turbine engines|
    US20130312260A1|2012-05-23|2013-11-28|Solar Turbines Incorporated|Method and device for modifying a secondary air system in a gas turbine engine|EP3597867A1|2018-07-17|2020-01-22|United Technologies Corporation|Sealing configuration using a bellows to reduce air leakage|
    EP3597868A1|2018-07-17|2020-01-22|United Technologies Corporation|Sealing configuration using a boot seal to reduce air leakage|
    WO2021058882A1|2019-09-27|2021-04-01|Safran Aircraft Engines|Aircraft turbine engine|
    法律状态:
    2016-09-08| PLFP| Fee payment|Year of fee payment: 2 |
    2017-03-31| PLSC| Search report ready|Effective date: 20170331 |
    2017-05-15| PLFP| Fee payment|Year of fee payment: 3 |
    2018-08-22| PLFP| Fee payment|Year of fee payment: 4 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2019-08-20| PLFP| Fee payment|Year of fee payment: 5 |
    2020-08-19| PLFP| Fee payment|Year of fee payment: 6 |
    2021-08-19| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1559304|2015-09-30|
    FR1559304A|FR3041686B1|2015-09-30|2015-09-30|DEVICE FOR SUPPORTING A PIPING IN A TURBOMACHINE|FR1559304A| FR3041686B1|2015-09-30|2015-09-30|DEVICE FOR SUPPORTING A PIPING IN A TURBOMACHINE|
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