• 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 an assembly (20) for an aircraft turbomachine comprising a fan casing (14) having an inner surface (14b), at least one acoustic panel (26) fixed by means of fixing means ( 48, 54) on the inner surface of the fan casing, and at least one circumferential stiffener (40) of the fan casing (14). According to the invention, the fastening means (48, 54) connect the fan casing (14) to the stiffener (40) integrated in the acoustic panel (26).
    公开号:FR3033839A1
    申请号:FR1552132
    申请日:2015-03-16
    公开日:2016-09-23
    发明作者:Cedric Zaccardi；Gwenael Sebastien Francois Marion
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD The present invention relates to the field of aircraft turbomachines, and more particularly to that of a crankcase. DESCRIPTION OF THE PREFERRED EMBODIMENTS OF AIRCRAFT TURBOMACHINE COMPRISING A BLOWER HOUSING EQUIPPED WITH AN ACOUSTIC COATING INTEGRATING A BLOWER HOUSING STIFFENER blower and its environment.
    [0002] The invention applies in particular to aircraft turbojets, preferably double-flow and double-body aircraft. STATE OF THE PRIOR ART On aircraft turbomachines, the fan casing defines an air inlet duct and is arranged facing the tops of the vanes of the fan, as is known for example from document WO2012 / 164204. On its inner surface, the fan casing usually carries acoustic panels, allowing sound waves to be absorbed. On its outer surface, this housing carries various equipment such as pipes, harnesses, housings, etc. This equipment is intended to be covered by a nacelle surrounding the turbomachine. In addition, to improve the modal strength and avoid the appearance of undesirable vibration modes, the fan casing is conventionally equipped with circumferential stiffeners, to have stiffeners extending longitudinally over all or part of the circumference of the housing. These circumferential stiffeners are fixed on the outer surface of the fan casing, or made in one piece with the latter. Their implementation is therefore constrained by the presence of equipment arranged on the same external surface. In other words, the presence of the equipment conditions the axial positioning of the stiffeners on the housing, as well as the axial and circumferential positioning of the fasteners of these stiffeners on the housing. The implantation of the circumferential stiffeners is also constrained by the fixing screws of the flanges located at the ends of the casing, the flanges serving to connect this casing to the adjacent elements of the turbomachine. In some cases, the implantation of the stiffeners may also be constrained by the presence of the means for fixing the acoustic panels on the casing. Overall, these constraints on the implantation of the circumferential stiffeners do not allow a perfect optimization of the modal behavior of the fan casing. In addition, the presence of the housing flanges prevents the implementation of stiffeners in one piece, on 3600. This would indeed lead to an impossibility of mounting the stiffeners on the outer surface of the housing, because of the position of the flanges projecting radially outwards. Finally, by being positioned around the fan casing, the circumferential stiffeners have a large diameter, directly impacting the overall mass of the assembly.
    [0003] There is therefore a need for optimization of the assembly comprising the fan casing, its acoustic panels and its circumferential stiffeners, and the fittings of the casing equipment. SUMMARY OF THE INVENTION To at least partially meet this need, the invention relates to an assembly for an aircraft turbomachine comprising a fan casing having an inner surface, at least one acoustic panel fixed using means fixing on said inner surface of the fan casing, as well as at least one circumferential stiffener of the fan casing. According to the invention, said fixing means connect the fan casing to the stiffener integrated to said acoustic panel.
    [0004] The invention is thus advantageous in that it provides to use a stiffener not only to provide the stiffening function of the fan casing, but also to contribute to the fixing of an acoustic panel on the same casing. By coupling these two functions, it is no longer necessary to provide additional means for fixing the acoustic panel on the housing, since this fixing is obtained directly by fixing the stiffener on the same housing. It follows advantageously in mass gain for the assembly according to the invention. Furthermore, the fact that the stiffener is located inside the casing, and no longer on the outer surface thereof, leads to a reduction in its diameter which also contributes to a reduction in the overall mass of the casing. together. The internal position of the stiffener also makes it possible to overcome the implantation problems encountered in the prior art, since the axial position of the stiffener is not constrained by the equipment of the housing or by the fixing screws of the flanges. casing. The axial and circumferential positioning of the fasteners of these stiffeners is also freer. This contributes overall to obtain a better modal behavior of the fan casing. In addition, since the stiffener is arranged on the side of the inner surface of the fan casing, it may be envisaged to make it in one piece on 3600, without this entailing installation problems.
    [0005] The invention preferably has at least one of the following optional features, taken singly or in combination. Said acoustic panel comprises an outer skin and / or an inner skin, and a preferably honeycomb panel core. Said panel core comprises a first portion and a second portion axially separated from each other by said circumferential stiffener. Alternatively, the stiffener to be placed at an axial end of the panel, without departing from the scope of the invention. In this case, the core of the panel could then be preferably sandwiched between two stiffeners arranged at the two axial ends of the acoustic panel, or the core could be sandwiched between a stiffener and a skin.
    [0006] Said circumferential stiffener is attached to the outer skin and / or the inner skin of the acoustic panel, and / or said circumferential stiffener is made integral with the outer skin and / or the inner skin of the acoustic panel. These two alternatives are combinable, for example by providing that the stiffener is attached to the outer skin and made in one piece with the inner skin, or vice versa. In case of realization of a single piece, it is the sole or the heel of the stiffener which forms part of the skin concerned. The solution is then called "integrated stiffener", as opposed to the other so-called "stiffener reported" solution, in which the stiffener is attached to the skin or skins for example by gluing and / or screws, rivets, etc. In this regard, it is noted that said circumferential stiffener comprises in effect a sole, a stiffener core, and preferably a heel. Preferably, said fixing means pass through the heel of said circumferential stiffener, and / or said fixing means comprise inserts housed in the core of the stiffener. Said fastening means may be circumferentially distributed regularly or unevenly along the stiffener, depending on the needs encountered and so as to counteract the most harmful vibration modes as effectively as possible. As indicative examples, the stiffener has a cross-section in the overall form of I, U, L, T, S, Z or other forms may nevertheless be envisaged, without departing from the scope of the invention.
    [0007] Preferably, the assembly comprises at least one equipment attached to the fan casing with the aid of said fixing means. Advantageously, it is no longer necessary to provide specific / additional fixing means for the integration of this / these equipment on the fan casing. This generates a gain on the overall mass of the whole.
    [0008] Finally, the stiffener and the acoustic panel in which the stiffener is integrated extend substantially in the same angular sector, preferably between 30 and 360 °. Alternatively, these two elements integrated into each other could extend according to different angular sectors. The invention also relates to an aircraft turbine engine 25 comprising an assembly as described above, the turbomachine being preferably a turbojet. Other advantages and features of the invention will become apparent in the detailed non-limiting description below.
    [0009] BRIEF DESCRIPTION OF THE DRAWINGS This description will be made with reference to the appended drawings among which; - Figure 1 shows a schematic perspective view of a turbomachine comprising an assembly according to the invention; FIG. 2 represents an axial half-sectional view of the assembly, according to a preferred embodiment of the invention; - Figure 3 shows an enlarged view of a portion of the assembly shown in the previous figure; FIG. 4 shows a view similar to that of FIG. 3, according to another preferred embodiment; - Figure 5 shows a view similar to that of Figure 3, according to yet another preferred embodiment; - Figure 6 shows a view similar to that of Figure 3, according to yet another preferred embodiment; Figure 7a is a developed view of the stiffener flange of the assembly shown in Figure 5; and - Figure 7b is a view similar to that of Figure 7a, according to another embodiment. DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS Referring firstly to FIG. 1, there is shown a turbomachine 1 for an aircraft, of the turbofan and double-body turbojet type. The turbojet engine 1 comprises, from front to rear with reference to a thrust direction 2 generated by the turbojet, a fan 4, a group of compressors 6, a combustion chamber 8 and a group of turbines 10. These elements Conventional turbofan engines are centered on a longitudinal axis 12, and surrounded by a housing, in particular a fan casing 14 surrounding the fan 4 rotatable about the axis 12.
    [0010] The fan casing 14, located at the front of the turbojet engine, belongs to an assembly 20 which is the subject of the invention, and a preferred embodiment of which will now be described with reference to FIGS. 2 and 3. casing 14 may be metallic or made of composite fiber-matrix material, generally organic matrix-fibers. It is a structural element of the turbojet, centered on the axis 12 and taking the general shape of a ring. At its front end, the casing 14 comprises a first connecting flange 22 intended for example for assembling the air intake structure. Similarly, the fan casing 14 has a second connecting flange 24 for assembling an outer shell of an intermediate casing. The two flanges 22, 24 protrude radially outwards. On the outer surface 14a of the fan casing, it is generally intended to arrange equipment (not shown in Figures 2 and 3), for example of the type pipes, harnesses, housings, etc.. On the inner surface 14b, the fan casing 14 carries one or more acoustic panels for the absorption of sound waves. In the example shown, there is provided a first acoustic panel 26 located at the front of the housing, and a second acoustic panel 26 located at the rear of the same housing. Each of the two panels for example extends continuously over 360 °, to form an acoustic protection shell. Alternatively, each panel could extend 360 ° by end-to-end joining a plurality of panel angular sectors in the circumferential direction 28. According to yet another alternative, the interior surface could be only partially covered in the direction circumferentially, by providing a plurality of angular sectors of a panel circumferentially spaced apart from one another. For the sake of simplification of the writing, thereafter, it will be considered that each acoustic panel 26 extends continuously 360 °, although the invention can be implemented for all the configurations described above. . Between the two acoustic panels 26 spaced axially from one another, the inner surface 14b is coated with an abradable layer 30 located radially opposite the apices of the blades 32 of the blower 4.
    [0011] The two acoustic panels 26 are made identically or similarly. Therefore, only one of them will now be described, with reference to FIG. 3. The panel 26 has an outer skin 34 pressed against the inner surface 14b of the housing 14. It also has an inner skin 36 located radially inwardly relative to the outer skin 34. Between the two concentric skins, the panel 26 has a panel core 38, preferably made using a honeycomb structure. The two skins 34, 36 are preferably made of organic fiber-matrix composite material, for example using glass and / or carbon fibers. One of the peculiarities of the invention resides in the integration, within acoustic panel 26, of one or more circumferential stiffeners 40 for reinforcing the fan casing to improve its modal hold and to prevent the appearance of modes. undesirable vibration. To simplify the drafting, it will subsequently be considered that each panel 26 comprises a single stiffener 40, extending in the same angular sector as that of the panel to which it is integrated, namely here over 360 °. In the preferred embodiment of Figures 2 and 3, the circumferential stiffener 40 extends in a transverse plane of the assembly 20, being centered on the axis of the housing 14. Nevertheless, in addition to extending according to the circumferential direction 28, the stiffener 40 could also travel with an axial component so as to exit a transverse plane, and form for example a helix or define zigzags. This possible evolution of the stiffener 40 in the axial direction is selected according to the needs encountered. The stiffener 40 is here sandwiched between the two skins 34, 36, in the same way 25 as the core 38 of the panel which it separates into two distinct parts 38a, 38b axially spaced from one another. Preferably, the first portion 38a and the second portion 38b of the core 38 are each in contact with the stiffener 40, which is thus protected by this core 38. A particular cut of the songs of the core 38 in honeycomb provides a complementarity of shape with that of the stiffener 40, which comprises a sole 42, a stiffener core 44, and a heel 46. More specifically, the stiffener 40 has a transverse section in the general shape of I, the ends respectively forming the sole 42 and the heel 46. The sole 42 bears against the outer skin 34 of the panel, and fixed thereto by means of an adhesive and / or screws or similar elements . In the same way, the heel 46 is in abutment with the inner skin 36 of the panel, and secured thereto by means of glue and / or screws or the like. For the connection of the acoustic panel 26 to the inner surface 14b of the fan casing 14, the stiffener 40 is cleverly used. Because of its integration with the panel 26, the fixing of the stiffener 40 on the casing 14 simultaneously ensures the fixing of the panel 26 on the same housing. To do this, there are provided fastening means, for example elements 48 of the type screws, bolts or similar elements. These fasteners 48 are oriented substantially radially and each pass through the fan casing 14, the outer skin 34 and the flange 42 of the stiffener. By way of example, several points of attachment of the stiffener 40 are provided along the latter, each fixing point 50 being obtained by means of two elements 48 arranged on either side of the web of stiffener 44. In an alternative shown in Figure 4, possibly combinable with the embodiment just described, the fixing means comprise inserts 54 housed in the core 44 of the stiffener. The core 44 may be locally over-thickened to allow the housing of each insert 54, which cooperates with a fastener 48 of the screw type, whose head is supported on the outer surface 14a of the fan casing. In the alternative shown in FIG. 5, only the shape of the circumferential stiffener 40 changes, namely that it has a Z-shaped cross section, with the two branches of the Z substantially perpendicular to the core 44. This shape cross section is also referred to as "double L". The aforementioned two branches of the Z thus constitute respectively the sole 42 and the heel 46 of the stiffener 40, the sole 42 remaining the part of this stiffener which cooperates with the fastening elements 48.
    [0012] Referring again to this FIG. 5, it is noted that the fastening elements 48 can also be used simultaneously for the fastening of one or more equipment, arranged on the outer surface 14a of the casing 14. To do this, the elements of FIG. fastening 48 pass through a mounting plate of the equipment, which allows the latter 5 not to require additional fastening means. This feature offered by the invention allows a gain in terms of costs and number of parts of the assembly 20, and therefore also generates a saving in weight. In the embodiments of Figures 2 to 5, the stiffener 40 is said reported to the panel 26 due to the attachment of the sole 42 and the heel 46 on the skins 34, 36, respectively. Another type of design is nevertheless conceivable, in which the stiffener 40 is made in one piece with the skins 34, 36 of the panel. This configuration, called "integrated" and shown schematically in Figure 6, may be considered for metal elements but is particularly advantageous when the skins 34, 36 and the stiffener 40 are made of composite material. In such a case, the sole 42 of the stiffener 40 is an integral part of the outer skin 34 of the panel, while the heel 46 is an integral part of the inner skin 36 of the same panel. In other words, coking can be envisaged for these elements 34, 40, 36 of composite material. In this embodiment in particular, the fastening elements 48 may be replaced by glue for connecting the outer skin 34 to the inner surface 14b of the casing 14. A mixed solution using the glue and the fasteners 48 screw type can also be considered. Moreover, it is noted whatever the embodiment envisaged, the acoustic panels can be initially bonded to the inner surface 14b of the fan casing 14. In all the preferred embodiments, the fastening means 48 of the stiffener 40 on the housing 14 may be distributed circumferentially in a regular manner, as has been shown schematically in Figure 7a corresponding to a view of the stiffener 40 developed on a plane. The attachment points 50 are spaced two hours apart, for example at 12, 2h, 4h, and so on. in a time reference centered on the longitudinal axis of the turbojet engine.
    [0013] Nevertheless, the freedom of positioning of the attachment points 50 makes it possible to distribute them in a non-regular manner, if this proves to be beneficial for improving the modal vibration behavior of the casing 14. Also, in the schematic representation of FIG. 7b, the fixing points 50 are arranged non-regularly, for example at 12h, 2h, 4h, 5h, 9h and 10h. Of course, various modifications may be made by those skilled in the art to the invention which has just been described, solely by way of non-limiting examples. 10
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. An assembly (20) for an aircraft turbine engine (1) comprising a fan casing (14) having an inner surface (14b), at least one acoustic panel (26) fixed by means of fixing means (48, 54) on said inner surface of the fan casing, as well as at least one circumferential stiffener (40) of the fan casing (14), characterized in that said fixing means (48, 54) connect the fan casing (14) to stiffener (40) integrated with said acoustic panel (26).
    [0002]
    2. An assembly according to claim 1, characterized in that said acoustic panel (26) comprises an outer skin (34) and / or an inner skin (36), and a panel core (38) preferably nesting of bees.
    [0003]
    3. An assembly according to claim 2, characterized in that said panel core (38) comprises a first portion (38a) and a second portion (38b) axially separated from each other by said circumferential stiffener (40).
    [0004]
    4. An assembly according to claim 2 or claim 3, characterized in that said circumferential stiffener (40) is attached to the outer skin (34) and / or to the inner skin (36) of the acoustic panel, and / or in that said circumferential stiffener (40) is integral with the outer skin (34) and / or the inner skin (36) of the acoustic panel.
    [0005]
    5. An assembly according to any one of the preceding claims, characterized in that said circumferential stiffener (40) comprises a sole (42), a stiffener core (44), and preferably a heel (46).
    [0006]
    6. An assembly according to claim 5, characterized in that said fixing means (48, 54) pass through the heel (42) of said circumferential stiffener (40), 3033839 12 and / or in that said fixing means (48, 54 ) comprise inserts (54) housed in the core (44) of the stiffener.
    [0007]
    7. An assembly according to any one of the preceding claims, characterized in that said securing means (48,54) are distributed circumferentially evenly along the circumferential stiffener (40).
    [0008]
    8. Assembly according to any one of the preceding claims, characterized in that it comprises at least one equipment attached to the fan casing 10 (14) by means of said fixing means (48, 54).
    [0009]
    9. An assembly according to any one of the preceding claims, characterized in that the circumferential stiffener (40) and the acoustic panel (26) in which the stiffener is integrated extend substantially in the same angular sector, preferably included between 30 and 360 °.
    [0010]
    10. An aircraft turbomachine (1) comprising an assembly (20) according to any one of the preceding claims. 20
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    同族专利:
    公开号 | 公开日
    WO2016146924A1|2016-09-22|
    US20180066581A1|2018-03-08|
    US10233837B2|2019-03-19|
    CN107407206A|2017-11-28|
    CN107407206B|2019-07-09|
    EP3271563A1|2018-01-24|
    FR3033839B1|2018-09-28|
    EP3271563B1|2018-12-26|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    GB2452476A|2007-07-19|2009-03-11|Assystem Uk Ltd|Acoustic liner for gas turbine engine manufactured by an additive fabrication process|
    WO2010012900A2|2008-07-30|2010-02-04|Aircelle|Acoustic attenuation panel for aircraft engine nacelle|
    FR2974225A1|2011-04-15|2012-10-19|Snecma|Acoustic panel type noise insulating structure for use in inner wall of nacelle of turboshaft engine of aircraft, has notch formed on part of circumference of insert, and damping interface provided between body and insert|
    WO2014068261A1|2012-11-05|2014-05-08|Snecma|Turbomachine casing|
    FR2903732B1|2006-07-12|2008-09-12|Airbus France Sas|AIR INTAKE FOR AIRCRAFT TURBOKER.|
    GB0813483D0|2008-07-24|2008-08-27|Rolls Royce Plc|Gas turbine engine nacelle|
    FR2935017B1|2008-08-13|2012-11-02|Snecma|INTERNAL WALL OF A TURBOMACHINE NACELLE|
    FR2975735A1|2011-05-27|2012-11-30|Snecma|TURBOMACHINE BLOWER CASING AND METHOD FOR MANUFACTURING THE SAME|
    FR2978735A1|2011-08-05|2013-02-08|Airbus Operations Sas|CONNECTION DEVICE PARTICULARLY ADAPTED TO ENSURE THE CONNECTION BETWEEN AN AIR INLET AND A MOTORIZATION OF AN AIRCRAFT NACELLE|
    FR3026134B1|2014-09-18|2019-07-19|Safran Nacelles|DEVICE FOR FIXING AN AIR INLET ON A BLOWER HOUSING OF AN AIRCRAFT TURBOJET AIRCRAFT|
    US10174675B2|2015-12-30|2019-01-08|General Electric Company|Acoustic liner for gas turbine engine components|
    US20170234160A1|2016-02-11|2017-08-17|General Electric Company|Aircraft engine with an impact panel|
    US10473030B2|2017-03-07|2019-11-12|Rolls-Royce Corporation|Acoustic panel of turbine engine|FR3064682B1|2017-03-31|2019-06-14|Safran Aircraft Engines|INTERMEDIATE CASE FOR AIRCRAFT TURBOMACHINE COMPRISING A LUBRICANT PASSING BIT CONNECTED TO A CARTER BOLT BY A CONNECTING PART|
    FR3070624B1|2017-09-06|2019-09-13|Safran Aircraft Engines|CARRIER IN COMPOSITE MATERIAL WITH A STRINGING GEOMETRY|
    FR3085299B1|2018-09-05|2021-04-16|Safran Aircraft Engines|COMPOSITE MATERIAL HOUSING WITH INTEGRATED STRENGTHENING|
    FR3092136B1|2019-01-29|2021-10-22|Safran Aircraft Engines|BLOWER HOUSING FOR AN AIRCRAFT TURBOMACHINE|
    FR3100834A1|2019-09-12|2021-03-19|Safran Aircraft Engines|TURBOMACHINE ACOUSTIC ANNULAR VIROLE AND ASSOCIATED MANUFACTURING PROCESS|
    法律状态:
    2016-02-24| PLFP| Fee payment|Year of fee payment: 2 |
    2016-09-23| PLSC| Publication of the preliminary search report|Effective date: 20160923 |
    2017-03-15| PLFP| Fee payment|Year of fee payment: 3 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2018-02-20| PLFP| Fee payment|Year of fee payment: 4 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 6 |
    2021-02-19| PLFP| Fee payment|Year of fee payment: 7 |
    2022-02-21| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1552132|2015-03-16|
    FR1552132A|FR3033839B1|2015-03-16|2015-03-16|AIRCRAFT TURBOMACHINE ASSEMBLY COMPRISING A BLOWER HOUSING EQUIPPED WITH AN ACOUSTIC COATING INTEGRATING A BLOWER HOUSING STIFFENER|FR1552132A| FR3033839B1|2015-03-16|2015-03-16|AIRCRAFT TURBOMACHINE ASSEMBLY COMPRISING A BLOWER HOUSING EQUIPPED WITH AN ACOUSTIC COATING INTEGRATING A BLOWER HOUSING STIFFENER|
    EP16715012.7A| EP3271563B1|2015-03-16|2016-03-14|Assembly for an aircraft turbine engine comprising a fan casing equipped with an acoustic liner incorporating a fan casing stiffener|
    PCT/FR2016/050556| WO2016146924A1|2015-03-16|2016-03-14|Assembly for an aircraft turbine engine comprising a fan casing equipped with an acoustic liner incorporating a fan casing stiffener|
    CN201680014520.5A| CN107407206B|2015-03-16|2016-03-14|Aircraft turbine engine component and aircraft turbine engine including the component|
    US15/558,853| US10233837B2|2015-03-16|2016-03-14|Assembly for an aircraft turbine engine comprising a fan casing equipped with an acoustic liner incorporating a fan casing stiffener|
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