• 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) for a turbomachine, comprising: - an inner hub (5); an outer shell (6); - At least one tubular arm (8) connecting the hub (5) to the ferrule (6), the arm (8) having a passage cavity of a member (12) servitudes, the cavity being delimited by walls; the element (12) of servitudes being configured to be mounted in the cavity in a direction parallel to an axis of elongation (A) of the element (12), the element (12) comprising at least one damper (18 ) wedging inside the cavity; characterized in that the damper (18) is formed in one piece, and is configured to deform in at least one deformation plane passing through the axis of elongation (A) of the member (12), and bear against the walls of the cavity when the element (12) is mounted in the cavity.
    公开号:FR3051854A1
    申请号:FR1654851
    申请日:2016-05-30
    公开日:2017-12-01
    发明作者:Reda Mohamed Oudyi；Damien Clement Didier Cordier
    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 and often with casings of large diameters, an element of servitudes comprises a longitudinal body defining an axis of elongation and at least one cushioning damper inside the cavity, this damper allowing in particular to to prevent the element of servitudes from coming into resonance, and thus does not degrade, when it is subjected to the different vibratory stresses generated by the operating turbomachine.
    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 transverse plane perpendicular to the axis of 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 laterally the cavity a return force necessary for the dampers can fully perform their function.
    The assembly / disassembly of the element of easements presents some difficulties.
    Firstly, during the introduction of the service element in the cavity, the sharp edges present on the sides of the dampers come into contact with the side walls of the cavity and thus oppose its introduction. The operator is then obliged to operate by a movement back and forth and / or to excessively force the risk of damaging the dampers and / or the walls of the cavity, and at the expense of productivity.
    The assembly is all the more critical because the free portions each exert a return force on the side walls 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 side walls 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 the hub to the ferrule, the arm having an internal passage through a servitude element, this cavity being delimited by primary and secondary side walls facing one another; the service member having an elongated shape and being configured to be mounted in the cavity in a direction substantially parallel to an axis of elongation of the member, the member having at least one cushioning damper within the cavity; characterized in that the damper is formed in one piece, and is configured to deform in at least one deformation plane passing through the axis of elongation of the element, and bear against the primary walls and secondary of the cavity when the element is mounted in the cavity.
    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, the mounting (reciprocally dismantling) of the service element does not degrade the dampers and / or the walls of the cavity. Thus, the various elements of easements can be quickly disassembled and reassembled for example a maintenance operation.
    The housing according to the invention may comprise one or more of the following features, taken separately from each other or in combination with each other: the damper comprises an inner ring fixed to the element and at least two flexible blades diametrically opposed protruding from the inner ring along the axis of elongation, the blades being configured to deform in the deformation plane; the plane of deformation of the damper is substantially coincident with each of the median planes of the two blades; each blade is convexly curved towards the element in a plane perpendicular to the axis of elongation; each blade comprises a curved portion concavity facing the element in the plane of deformation; - The outer ends of the blades are integral with an outer ring fixed on the element, coaxial with the inner ring, and integral with the damper; the element is mounted in the cavity by an orifice made in the ferrule; the damper comprises several blades evenly distributed around the axis of elongation; the element comprises several 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 partial perspective view of the housing comprising an arm into which is introduced a service element comprising a damper according to a first embodiment; FIG. 3 is a perspective view of the service element of FIG. 2; FIG. 4 is a detailed perspective view of the damper of FIGS. 2 and 3; FIG. 5 is a partial perspective view of the casing comprising an arm in which is introduced a service element comprising a damper according to a second embodiment; FIG. 6 is a perspective view of the service element of FIG. 5; - Figure 7 is a perspective view of detail of the damper of Figures 5 and 6; - Figure 8 is a detailed sectional view of the housing arm of Figures 2 and 5; FIG. 9 is a detailed perspective view of the insertion / removal orifice of the service elements of FIGS. 3 and 6; - Figure 10 is a perspective view illustrating the assembly / disassembly of the service element illustrated in Figures 5 to 7 in a cavity of the housing arm.
    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 partially 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 stream 7 of flow of the flue gas stream and is rigidly connected to the hub 5 by arms 8 substantially radial with respect to a longitudinal axis X of the turbomachine 2.
    The embodiment illustrated is in no way limiting, the turbomachine 2 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 (no visible in Figure 1).
    By convention, in the present application, the terms "internal" and "external", "inside" and "outside", "lower" and "upper" are defined radially with respect to the longitudinal axis X of the turbomachine 2 (of the central axis towards the periphery of the motor casings).
    The casing 1 comprises at least one tubular arm 8 having an internal cavity 9 delimited by primary and secondary side walls 10, 11 facing one another (FIG. 8), this cavity 9 allowing the passage of an element 12 of easements.
    More specifically, the cavity 9 opens on both the ferrule 6 via an orifice 13 (Figure 9) but also on the hub 5. The passage of the elements 12 of servitudes 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 12 of servitudes connects at least a first equipment located radially inside the vein 7 to at least a second equipment located radially outside the vein 7. Such an element 12 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 12 of servitudes generally has an elongate shape and comprises a body 14 delimited at each end by a connector 15, 16 for connection with the corresponding equipment, the body 14 defining an axis of elongation A.
    By convention, in the present application, the term "transverse plane", any plane perpendicular to the axis of elongation A of the element 12 easements.
    According to the embodiments shown in figures, the body 14 is tubular and of circular cross section (in a transverse plane), the axis of elongation A corresponding to the axis of revolution of the body 14. The body 14 is delimited by an internal connector and an external angled connector 16 delimited by a cylindrical cap 17 coaxial with the body 14.
    According to an alternative embodiment, the body 14 may have an oblong, rectangular, square cross section, etc. The element 12 of servitudes comprises at least one damper 18 for wedging inside the cavity 9. The damper 18 is formed in one piece, and is configured firstly to deform in at least one plane deformation P passing through the axis of elongation A of the element 12 (or passing substantially through the axis of elongation A of the element 12), and secondly bear against the walls 10, 11 primary and secondary of the cavity 9 when the element 12 is mounted in the cavity 9. The damper 18 serves in particular to prevent the element 12 easements from resonating, and thus does not degrade, when it is subjected to the different vibratory stresses generated by the turbomachine 2 in operation.
    According to an alternative embodiment not shown, the element 12 of servitudes comprises several dampers 18 positioned radially at different heights of the body 14, and for example two dampers 18. The damper 18 comprises an inner ring 19 fixed to the element 12 and at least two diametrically opposed flexible blades 20 projecting from the inner ring 19 along the axis of elongation A in the direction of the shell 6, the blades 20 being configured to deform in a deformation plane P passing through the axis d elongation A of the element 12, when these are externally biased. The damper 18 is for example made of nickel-based alloy but this example is in no way limiting.
    According to the embodiments illustrated in the figures, the damper 18 comprises six flexible blades 20 of substantially equal dimensions. The blades 20 are angularly evenly distributed and diametrically opposed in pairs, the blades 20 being spaced apart from each other in a regular manner. Each pair of diametrically opposed blades is configured to deform in a deformation plane P passing through the axis of elongation A of the element 12 and by each of the median planes of the two blades 20.
    Advantageously, as illustrated in FIG. 8, when the element 12 is mounted in the cavity 9, two diametrically opposed blades 20 bear against the primary and secondary walls 10, 11 of the cavity 9, the deformation plane P. of these blades 20 being substantially perpendicular to the walls 10, 11 of the cavity 9.
    The fact of having a sufficient number of blades angularly distributed regularly, and in this case greater than four, makes it possible to overcome the need to precisely orient the element of servitudes during its assembly / disassembly. .
    The inner ring 19 is cylindrical and coaxial with the axis of elongation A of the element 12. The inner ring 19 is fixed on the body 14 of the element 12, for example by soldering or welding. In the case where the element 12 of servitude comprises a heat insulating layer surrounding the body 14, the damper 18 can be directly attached to the heat insulating layer.
    Advantageously, the base may comprise an opening (for example circular) and / or tongues to increase the brazed or welded surface, and in other words the strength of the assembly.
    According to an alternative embodiment, the base is for example fixed to the body 14 by screwing, bolting, riveting, latching, etc.
    Each blade 20 is in cross-section (in a transverse plane) substantially rectangular, the transverse dimensions of each of the blades 20 being substantially constant along the axis of elongation A of the element 12.
    The blades 20 are curved concavity turned towards the element 12 in a plane perpendicular to the axis of elongation A (and in other words a transverse plane). This geometric feature makes it possible to limit the contact surfaces (and to eliminate sharp edges in sliding contact) with the primary and secondary walls 10, 11 of the cavity 9 during assembly (reciprocally dismantling), and in other words to reduce the necessary efforts. the assembly (reciprocally disassembly) of the element 12 easements.
    Each blade 20 comprises a concavely curved bearing portion 21 facing the element 12 in its associated deformation plane P. This geometric feature contributes to the flexibility of the blade 20.
    According to the first embodiment illustrated in Figures 2 to 4, the outer ends of the blades 20 are integral with an outer ring 22 opposite to the inner ring 19 along the axis of elongation A and substantially coaxial with the latter, this external ring 22 being fixed on the element 12 and integral with the shock absorber 18.
    More specifically, the outer ring 22 is cylindrical and fixed to the body 14 of the element 12, for example by brazing or welding, in the same manner as the inner ring 19. The support portion 21 of each blade 20 is between an inner portion 23 and an outer portion 24, curved, concavity facing outwardly (and in other words in a direction opposite to the body 14). The inner and outer portions 23, 24 are respectively connected to the inner ring 19 and to the outer ring 22. Each blade 20 thus has a point of inflexion lower than the boundary between the inner portion 23 and the support portion 21, and a point of inflection greater than the boundary between the bearing portion 21 and the outer portion 24.
    According to the second embodiment illustrated in Figures 5 to 7, the outer ends of the blades 20 are free and each have two leaves 25 so as to avoid sharp edges. Each blade 20 comprises an inner portion 23, curved, concavity facing outwardly (and in other words in a direction opposite to the body 14). The inner portion 23 thus makes it possible to bind the inner ring 19 and the support portion 21, each blade 20 thus having a point of inflection at the boundary between the inner portion 23 and the bearing portion 21. By way of comparison with the first embodiment (illustrated in FIGS. 2 to 4), the damper 18 according to the second embodiment (illustrated in FIGS. 5 to 7) is of equal size more flexible, and in other words less steep. The choice of the structure of the damper 18 is a function of the vibratory stresses.
    The dimensional and geometric characteristics associated with the blades 20 are chosen so that they deform smoothly and without opposing resistance, during assembly (reciprocally during disassembly) of the element 12 while ensuring its rigging and its damping in the cavity 9.
    As illustrated in Figure 9, the opening 13 of introduction / withdrawal of the element 12 easements is oblong and formed in a cylindrical boss 26 projecting from the ferrule 6 to the outside of the housing 1. The orifice 13 comprises a cylindrical counterbore 27 delimited by a shoulder 28 and intended to receive the cap 17 of the external connector 16.
    As illustrated in FIG. 10, in the direction of the arrow 29, the element 12 of servitudes is mounted in the cavity 9 through the orifice 13 of the outer shell 6 in a direction substantially parallel to the axis of lengthening A of the body 14.
    More specifically, during assembly of the element 12 of easements, the damper 18 enters the cavity 9 through the orifice 13 via the inner ring 19. Following the introduction of the inner ring 19, the blades 20 are constrained to deform due to the dimensional characteristics of the orifice 13 and the cavity 9. The final positioning of the element 12 is done by mounting the the complete line which corresponds to all the elements connected to each other from one equipment to another. At the end of the mounting of the element 12 easements, the blades 20 of the damper 18 are constrained, and in other words these blades 20 exert restoring forces immobilizing the element 12 of servitudes in the cavity 9 while allowing its damping when the turbomachine 2 is in operation.
    As illustrated in FIG. 10, in the direction of the arrow 30, the element 12 of servitudes is removed from the cavity 9 through the orifice 13 in a direction substantially parallel to the axis of elongation A of FIG. body 14. At the end of the extraction of the damper 18, the latter substantially returns to its original shape.
    权利要求:
    Claims (10)
    [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 the hub (5) to the ferrule (6), the arm (8) having an internal cavity (9) for the passage of a servitude element (12), this cavity (9) ) being delimited by primary and secondary lateral walls (10, 11) facing one another; the element (12) of servitudes having an elongated shape and being configured to be mounted in the cavity (9) in a direction substantially parallel to an axis of elongation (A) of the element (12), the element ( 12) comprising at least one cushioning cushion (18) inside the cavity (9); characterized in that the damper (18) is formed in one piece, and is configured to deform in at least one deformation plane (P) passing through the elongation axis (A) of the element ( 12), and bear against the primary and secondary walls (10, 11) of the cavity (9) when the element (12) is mounted in the cavity (9).
    [2" id="c-fr-0002]
    2. Carter (1) according to claim 1, characterized in that the damper (18) comprises an inner ring (19) fixed to the element (12) and at least two diametrically opposed flexible blades (20) protruding from the ring (19) internal along the axis of elongation (A), the blades (20) being configured to deform in the deformation plane (P).
    [3" id="c-fr-0003]
    3. Carter (1) according to claim 2, characterized in that the deformation plane (P) of the damper (18) is substantially coincident with each of the median planes of the two blades (20).
    [4" id="c-fr-0004]
    4. Carter (1) according to one of claims 2 or 3, characterized in that each blade (20) is curved concavity facing the element (12) in a plane perpendicular to the axis of elongation (A ).
    [5" id="c-fr-0005]
    5. Carter (1) according to one of claims 2 to 4, characterized in that each blade (20) comprises a portion (21) curved concavity facing the element (12) in the deformation plane (P) .
    [6" id="c-fr-0006]
    6. Carter (1) according to one of claims 2 to 5, characterized in that the outer ends of the blades (20) are integral with an outer ring (22) fixed on the element (12), coaxial with the ring (19) internal, and material coming with the damper (18).
    [7" id="c-fr-0007]
    7. Carter (1) according to one of the preceding claims, characterized in that the element (12) is mounted in the cavity (9) by an orifice (13) formed in the shell (6).
    [8" id="c-fr-0008]
    8. Carter (1) according to one of the preceding claims, characterized in that the damper (18) comprises a plurality of blades (20) evenly distributed about the axis of elongation (A).
    [9" id="c-fr-0009]
    9. Carter (1) according to one of the preceding claims, characterized in that the element (12) comprises several dampers (18).
    [10" id="c-fr-0010]
    10. 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
    FR3051854B1|2018-05-18|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    GB1218021A|1967-05-11|1971-01-06|Rolls Royce|Improvements in flow directing blades|
    EP0342087A1|1988-05-11|1989-11-15|Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma"|Turbo machine having an entry stator grill with built-in oil passage tubes|
    EP1149982A2|2000-04-11|2001-10-31|General Electric Company|A method of joining a vane cavity insert to a nozzle segment of a gas turbine|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|
    FR3093130A1|2019-02-27|2020-08-28|Safran Aircraft Engines|Retaining elements for a tubing.|
    法律状态:
    2017-04-28| PLFP| Fee payment|Year of fee payment: 2 |
    2017-12-01| PLSC| Search report ready|Effective date: 20171201 |
    2018-04-23| 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 |
    2019-04-19| PLFP| Fee payment|Year of fee payment: 4 |
    2020-04-22| PLFP| Fee payment|Year of fee payment: 5 |
    2021-04-21| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1654851A|FR3051854B1|2016-05-30|2016-05-30|TURBOMACHINE EXHAUST CASE|
    FR1654851|2016-05-30|FR1654851A| FR3051854B1|2016-05-30|2016-05-30|TURBOMACHINE EXHAUST CASE|
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