• 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:
    Carter (1), in particular exhaust, for a turbomachine, comprising: - an inner hub (5); an outer shell (6) extending around the hub (5); - At least one radial tubular arm (8) connecting said hub (5) to said shell (6), said arm (8) having an internal passage through a member (11) easements; said servitude element (11) having an elongated shape and being configured to be mounted in said cavity in a direction substantially parallel to an axis of elongation of said element (11), said element (11) comprising at least one cushioning damper inside said cavity; characterized in that said at least one damper is configured to deform in a plane passing through said axis of elongation of said member (11).
    公开号:FR3050229A1
    申请号:FR1653392
    申请日:2016-04-18
    公开日:2017-10-20
    发明作者:Benoit Argemiro Matthieu Debray；Gregory Ghosarossian-Prillieux；Guillaume Sevi；Patrick Sultana；Guy Vieillefond
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    TURBOMACHINE EXHAUST CASE
    TECHNICAL AREA
    The present invention relates to a casing, in particular an exhaust, of an aircraft turbine engine.
    STATE OF THE ART
    In known manner, a turbomachine exhaust casing comprises an inner hub and an outer shell extending around the hub. The shell is configured to define with the hub an annular flow stream of a gas flow and is rigidly connected to the hub by substantially radial arms relative to a longitudinal axis of the turbomachine.
    An exhaust casing is mounted downstream (with reference to the flow of gases in the turbomachine) of a turbine and the flow of gas passing through the exhaust casing is thus the flow of exhaust gas exiting the turbine.
    A turbomachine may comprise other similar casings such as an intermediate casing or an inter-turbine casing better known under its English designation TVF for "Turbine Vane Frame". An intermediate casing is interposed between a low pressure compressor and a high pressure compressor of the turbomachine, and is therefore traversed by a flow of gas leaving the low pressure compressor and intended to supply the high pressure compressor.
    In the traditional way, the arms of the casing allow the passage of servitude elements so as not to disturb the flow of the flow inside the vein, such arms being tubular and each comprising an internal cavity for the passage of the elements. easements.
    An easement element may comprise for example one or more air ducts and / or one or more oil ducts and / or one or more electric cables, etc. In general, each of the servitude elements makes it possible to connect at least one first device located radially inside the vein with at least one second device located radially outside the crankcase vein.
    On high-power engines, an easement element comprises a longitudinal body defining an axis of elongation and at least one cushioning damper inside the cavity, this damper notably making it possible to prevent the element of servitudes from returns to resonance, and thus does not degrade, when subjected to the various vibratory stresses generated by the operating turbine engine.
    It is known to use two shock absorbers mounted head to tail, each in the form of a curved blade, flexible, and delimited laterally by flanks. Each blade comprises, on the one hand, a portion attached to the body of the element, and on the other hand, a free portion. Each blade is positioned flat on the servitude element, it extends along a transverse axis perpendicular to the axis of elongation of the element and is configured to deform in a plane perpendicular to the axis elongation. The service element is configured to be mounted in the cavity in a direction substantially parallel to the axis of elongation of the element. During its assembly, the free portions are constrained so that the latter each exert on a wall delimiting the cavity a return force necessary for the dampers to fully perform their function.
    The assembly / disassembly of the element of easements presents some difficulties.
    Firstly, during the introduction of the element of easements in the cavity, the sharp edges present on the sides of the dampers come into contact with the wall of the cavity and thus oppose its introduction. The operator is then obliged to operate by a movement back and forth and / or excessive force the risk of damaging the dampers and / or the wall of the cavity, and to the detriment of productivity.
    The assembly is all the more critical because the free portions each exert a return force on the wall of the cavity.
    Secondly, as a result of the assembly and the difficulties encountered mentioned above, it is generally impossible to dismantle the service element to perform, for example, a maintenance operation without considerably damaging the dampers and / or the wall of the cavity. . The object of the present invention is therefore to optimize the assembly and disassembly of the service element in a housing of the aforementioned type.
    SUMMARY OF THE INVENTION The invention proposes for this purpose a housing, in particular exhaust, for a turbomachine, comprising: an inner hub; an outer shell extending around the hub; at least one radial tubular arm connecting said hub to said shell, said arm having an internal cavity for the passage of a service element; said service member having an elongate shape and being configured to be mounted in said cavity in a direction substantially parallel to an axis of elongation of said member, said member having at least one timing damper within said cavity; characterized in that said at least one damper is configured to deform in a plane passing through said axis of elongation of said member.
    Firstly, the damper insulates the element of servitudes with respect to the vibrations generated by the turbomachine, and in other words prevents the element of servitudes from resonating, and thus does not degrade, when it is subjected to different vibratory stresses generated by the turbomachine in operation.
    Second, the fact that the damper is configured to deform in a plane passing through the axis of elongation of the element makes it possible to mount (reciprocally dismantle) the element of easements smoothly while limiting the necessary efforts assembly (reciprocally dismantling). Consequently, mounting (reciprocating the disassembly) of the service element does not degrade the dampers and / or the wall of the cavity. Thus, the various elements of easements can be quickly disassembled and reassembled for example a maintenance operation.
    The casing according to the invention may comprise one or more of the following features, taken separately from each other or in combination with each other: said damper has an elongated shape along said axis of elongation of said element; said plane is at least partially perpendicular to said damper; said element is mounted in said cavity by an orifice made in said ferrule; said damper comprises a base fixed to the element and a free leg and configured to deform in said plane passing through said axis of elongation of said element; - The tab comprises a curved portion concavity facing the element; said portion comprises a convexly concave outer face turned towards the element; - Said portion is between an upper portion and a lower portion curved concavity facing outwardly; - The element comprises a second damper mounted opposite and symmetrically with respect to the first damper; the element comprises several stages of dampers. The invention has for its second object a turbomachine comprising a casing as described above.
    DESCRIPTION OF THE FIGURES The invention will be better understood and other details, characteristics and advantages of the invention will emerge more clearly on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which: Figure 1 is a detail sectional view of a turbomachine comprising a housing according to the invention; - Figure 2 is a front view of the housing of Figure 1; FIG. 3 is a perspective view of an easement element; - Figure 4 is a detailed perspective view of a damper of the service element; FIG. 5 is a front detail view of the service element; - Figure 6 is a sectional view of the service element along a plane VI-VI of Figure 5; - Figure 7 is a perspective view illustrating the mounting of the service element in a cavity of an arm of the housing; - Figure 8 is a schematic representation of the service element when mounted in the housing cavity of the housing.
    DETAILED DESCRIPTION
    FIG. 1 shows a casing 1 of a turbomachine 2 with a double flow, and more precisely an exhaust casing 1 situated between a low-pressure turbine 3 and a nozzle 4 for ejecting the combustion gases coming from the turbine 3 .
    As shown in FIG. 2, the exhaust casing 1 comprises an inner hub 5 and an outer shell 6 extending around the hub 5. The shell 6 is configured to define, with the hub 5, an annular flow stream 7 the flow of combustion gas and being rigidly connected to the hub 5 by substantially radial arms 8 with respect to a longitudinal axis X of the turbomachine.
    The illustrated embodiment is in no way limiting, the turbomachine may comprise other casings having a similar structure, and thus the casing could be for example an intermediate casing located between a low pressure compressor and a high pressure compressor (not visible in Figure 1).
    The housing 1 comprises at least one tubular arm 8 having an internal cavity 9 delimited by a wall 10, this cavity 9 allowing the passage of an element 11 of servitudes (Figure 8).
    More specifically, the cavity 9 opens on both the ferrule 6 via an orifice 12 (Figure 7) but also on the hub 5. The passage of the elements 11 easements in the arms 8 has the advantage of not interfering with the flow of the gas flow inside the vein 7, and in other words limit the pressure drops.
    An element 11 of servitudes connects at least one first equipment located radially inside the vein 7 to at least one second equipment located radially outside the vein 7. Such an element 11 may comprise for example one or more conduits air and / or one or more oil pipes and / or one or more electrical cables, etc.
    An element 11 easements generally has an elongated shape and comprises a body 13 delimited at each end by an interface 14 for connection with the corresponding equipment, the body 13 defining an axis A elongation.
    According to the embodiment shown in figures, the body 13 is tubular and of oblong cross section, the body 13 thus comprising two rounded sides 15 and two flanks 16 planes. The axis A of elongation corresponds for example to the axis of symmetry of the body 13. A plane B is defined as being the plane parallel to the flanks 16 planes and passing through each of the vertices of the flanks 15 rounded (Figure 6).
    According to an alternative embodiment, the body 13 may have a circular, rectangular, square cross section, etc. The element 11 of servitudes comprises at least one cushioning cushion 17 inside the cavity 9, the damper 17 being configured to deform in a plane passing through the axis A of elongation of the element 11 ( or passing substantially through the axis A of elongation of the element 11). The damper 17 makes it possible in particular to prevent the element 11 of servitudes from coming into resonance, and thus does not degrade, when it is subjected to the different vibratory stresses generated by the turbomachine 2 in operation.
    According to the embodiment shown in the figures, the element 11 of servitudes comprises two dampers 17 positioned at mid-height of the body 13 and facing one another symmetrically along the plane B of the body 13.
    According to an alternative embodiment not shown, the element 11 of servitudes comprises several stages of dampers 17 positioned at different heights of the body 13, and for example two stages of dampers 17.
    As can be seen in FIG. 5 in particular, a damper 17 comprises a base 18 fixed to the body 13, and a lug 19 projecting from the base 18, which is free and configured to deform in a plane passing through the axis A d elongation of the element 11 when it is externally stressed.
    More precisely, according to the embodiment illustrated in the figures, the damper 17 is in the form of a curved blade having in cross section a rectangular profile and extending along the axis A of elongation. The damper 17 is for example obtained from a cutting operation in a sheet and then a folding operation to give it its final shape. The damper 17 is for example made of nickel-based alloy but this example is in no way limiting.
    As illustrated in FIG. 5, the thickness of the damper 17 is G, the thickness C is for example between 0.5 mm and 2 mm, and is advantageously 0.7 mm.
    In the rest of the description, the terms "lower" and "upper" are defined relative to the orientation of the damper 17 in the figures.
    The base 18 is flat, of substantially square shape, and is fixed on a flat flank 16 of the body 13 of the element 11. The base 18 is for example fixed on the flat side 16 by brazing or welding. Advantageously, the base 18 may comprise an opening 24 (for example circular) to increase the brazed or welded surface, and in other words the strength of the assembly.
    According to an alternative embodiment, the base 18 is for example fixed to the sidewall 16 plane by screwing, bolting, riveting, latching, etc.
    As illustrated in FIGS. 5 and 6, D is the length of the base 18 of the damper 17 and E is the width of the base 18 of the damper 17.
    The length D is for example between 10 mm and 50 mm, and is advantageously 25 mm.
    The width E is, for example, between 10 mm and the width of the flat side 16, and is advantageously of the width of the flat side 16.
    The tab 19 is flexible and configured to deform in a plane passing through the axis A of elongation and perpendicular to the base 18 of the damper 17 (or plane B). Specifically, the tab 19 (Figure 5) comprises: an upper portion, curved, concavity facing outwardly, and in other words in a direction opposite to the body 13 an intermediate portion 21, curved, concavity turned towards the body 13, and a lower portion, curved, concavity facing outward, and in other words in a direction opposite to the body 13.
    The tab 19 thus comprises a point of inflection greater than the boundary between the upper portion and the intermediate portion 21, and a point of inflection lower than the boundary between the intermediate portion 21 and the lower portion 22. The lower portion 22 bears on the flat side 16. The fact that the lower portion 22 bears on the body 13 allows in particular to guide and control the lug 19 when it deforms while avoiding the presence of a sharp edge capable of degrading the body 13 of the element 11.
    As illustrated in FIGS. 5 and 6, F is the maximum distance between the intermediate portion 21 and the flat flank 16, measured perpendicularly to the plane flank 16, when the element 11 of servitudes is not mounted (damper 17 resting). G is the length, projected on the flat side 16 delimited on the one hand by the base border 18 / upper portion and on the other hand by the point of contact of the lower portion 22 on the flat side 16, when the element 11 easements is not mounted (damper 17 at rest). We denote H the width of the tab 19.
    The distance F is for example between 5 mm and 30 mm, and is advantageously 10 mm. The length G is for example between 20 mm and 100 mm, and is advantageously 80 mm. The width F1 is for example between 5 mm and the width of the flat side 16, and is advantageously of the width of the flat side 16.
    The dimensional and geometrical characteristics associated with the lug 19 allow it to deform smoothly and without opposing resistance, during assembly (reciprocally during disassembly) of the element 11 of servitudes, and more specifically when that it is in contact with the wall 10 of the cavity 9.
    As illustrated in FIG. 6, the intermediate portion 21 of the lug 19 comprises a convex outer face 23, and more precisely a concavity facing the body 13. This geometric characteristic makes it possible to limit the contact surfaces (and to eliminate the sharp edges in sliding contact) with the wall 10 of the cavity 9 during assembly (reciprocally disassembly), and in other words reduce the forces required for mounting (reciprocally disassembly) of the element 11 easements.
    As illustrated in FIG. 7, in the direction of the arrow, the element 11 of servitudes is mounted in the cavity 9 through the orifice 12 of the outer shell 6 in a direction substantially parallel to the axis A lengthening body 13 when the element 11 is in the mounted position.
    As illustrated in FIG. 8, during assembly, the dampers 17 penetrate into the cavity 9 via the lower portions 22 of the arms 8. The arms 8 are constrained to deform due to the dimensional characteristics of the cavity 9, and more precisely the distance F decreases and the length G increases. At the end of the mounting of the element 11 easements, the tabs 19 of the dampers 17 are constrained (state constrained or deformed).
    During disassembly, the element 11 of servitudes is extracted from the cavity 9 through the orifice 12. The dampers 17 exit the cavity 9 via the bases 18. At the end of the extraction of the dampers 17, these The last ones recover substantially their initial shape (state of repose or not deformed).
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    1. Carter (1), in particular exhaust, for a turbomachine (2), comprising: an inner hub (5); an outer shell (6) extending around the hub (5); at least one radial tubular arm (8) connecting said hub (5) to said shell (6), said arm (8) having an internal cavity (9) for the passage of a service element (11); said element (11) of servitudes having an elongate shape and being configured to be mounted in said cavity (9) in a direction substantially parallel to an axis (A) of elongation of said element (11), said element (11) comprising at at least one cushioning cushion (17) within said cavity (9); characterized in that said at least one damper (17) is configured to deform in a plane passing through said axis (A) of elongation of said member (11).
    [2" id="c-fr-0002]
    2. Carter (1) according to claim 1, characterized in that said damper (17) has an elongated shape along said axis (A) of elongation of said element (11).
    [3" id="c-fr-0003]
    3. Carter (1) according to one of the preceding claims, characterized in that said plane is at least partially perpendicular to said damper (17).
    [4" id="c-fr-0004]
    4. Carter (1) according to one of the preceding claims, characterized in that said element (11) is mounted in said cavity (9) by an orifice (12) formed in said shell (6).
    [5" id="c-fr-0005]
    5. Carter (1) according to one of the preceding claims, characterized in that said damper (17) comprises a base (18) fixed to the element (11) and a lug (19) free and configured to deform in said plane passing through said axis (A) of elongation of said element (11).
    [6" id="c-fr-0006]
    6. Carter (1) according to claim 5, characterized in that the tab (19) comprises a portion (21) curved concavity facing the element (11).
    [7" id="c-fr-0007]
    7. Carter (1) according to claim 6, characterized in that said portion (21) comprises an outer face (23) curved concavity facing the element (11).
    [8" id="c-fr-0008]
    8. Carter (1) according to claim 7, characterized in that said portion (21) is between an upper portion (20) and a portion (22) curved lower concavity facing outwardly.
    [9" id="c-fr-0009]
    9. Carter (1) according to one of the preceding claims, characterized in that the element (11) comprises a second damper (17) mounted facing and symmetrically with respect to the first damper (17) and its axis of elongation (A).
    [10" id="c-fr-0010]
    10. Carter (1) according to one of the preceding claims, characterized in that the element (11) comprises several stages of dampers (17).
    [11" id="c-fr-0011]
    11. Turbomachine (2) comprising a housing (1) according to one of the preceding claims.
    类似技术:
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    同族专利:
    公开号 | 公开日
    FR3050229B1|2018-04-27|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20050199445A1|2004-03-09|2005-09-15|Honeywell International Inc.|Apparatus and method for bearing lubrication in turbine engines|
    WO2013162982A1|2012-04-27|2013-10-31|General Electric Company|Half-spoolie metal seal integral with tube|
    WO2014114653A2|2013-01-22|2014-07-31|Siemens Aktiengesellschaft|Gas turbine outer case active ambient cooling including air exhaust into sub-ambient cavity|
    EP2840231A1|2013-08-23|2015-02-25|Siemens Aktiengesellschaft|Turbine blade with a hollow turbine blade|EP3461997A1|2017-09-29|2019-04-03|United Technologies Corporation|Apparatus, corresponding gas turbine engine and method of assembling|
    EP3517737A1|2018-01-26|2019-07-31|MTU Aero Engines GmbH|Damper for damping vibrations of a tube in a hollow strut of a gas turbine engine and hub strut case with such a damper|
    FR3093128A1|2019-02-25|2020-08-28|Safran Aircraft Engines|Turbomachine housing|
    FR3093130A1|2019-02-27|2020-08-28|Safran Aircraft Engines|Retaining elements for a tubing.|
    EP3712391A1|2019-03-22|2020-09-23|United Technologies Corporation|Strut dampening assembly and method of making same|
    法律状态:
    2017-04-06| PLFP| Fee payment|Year of fee payment: 2 |
    2017-10-20| PLSC| Search report ready|Effective date: 20171020 |
    2018-03-22| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2019-03-25| PLFP| Fee payment|Year of fee payment: 4 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 5 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1653392|2016-04-18|
    FR1653392A|FR3050229B1|2016-04-18|2016-04-18|TURBOMACHINE EXHAUST CASE|FR1653392A| FR3050229B1|2016-04-18|2016-04-18|TURBOMACHINE EXHAUST CASE|
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