• 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:
    Panel (1) for heat exchange and noise reduction for a propulsion unit, in particular an aircraft, the panel (1) comprising: - a perforated plate (2) comprising a plurality of through orifices (21), a honeycomb structure (3) comprising longitudinally oriented structural walls (32) covered by said perforated plate (2) and having cavities (31) between said walls (32) defining Helmoltz resonators, said through-holes ( 21) forming necks of said resonators, and - fluid circulation means (6), for example oil, at said perforated plate (2), characterized in that said fluid circulation means comprise channels (6) which are formed at least partly in thickened ends of said walls (32), on the side of said perforated plate (2), and / or at least partly in areas of the perforated plate (2) located in the longitudinal extension of said over-thickened ends.
    公开号:FR3041704A1
    申请号:FR1559154
    申请日:2015-09-29
    公开日:2017-03-31
    发明作者:Matthieu Leyko；Imane Ghazlane
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    Thermal exchange and noise reduction panel for a propulsion unit
    TECHNICAL AREA
    The present invention relates to a heat exchange panel and noise reduction for a propulsion system, in particular aircraft. It also relates to a propulsion assembly provided with said panel and a method of manufacturing said panel.
    STATE OF THE ART
    An aircraft turbomachine conventionally comprises, from upstream to downstream, in the direction of flow of the gases, at least one compressor module intended to compress an air flow, an annular combustion chamber in which the flow of compressed air is mixed with fuel and then burned, and at least one turbine module in which the flow of combustion gas is expanded to drive a turbine shaft.
    The turbomachine generally comprises at its upstream end a blower comprising a bladed wheel intended to compress a flow of air entering the turbomachine via a primary duct, this air flow dividing downstream of the blower into a primary supplying flow. the compressor module and intended to produce the aforementioned flow of combustion gas, and a secondary flow intended to flow into a secondary vein around the engine of the turbomachine and inside a nacelle.
    Furthermore, the turbomachine is provided with a fluid circulation system, for example oil which provides the dual task of lubricating the rotating parts and remove the calories released into the engine as heat. Current studies on the engines of the future show that the trend is to increase the overall temperature of the engine. As a result, the amount of calories to be evacuated in these applications is much greater than in the case of conventional engines.
    To cool the fluid, for example the oil, whose temperature must not exceed a predetermined temperature for reasons of efficiency, for example of the order of 200 ° C, different types of heat exchangers exist. Some of them use air as a cold source.
    The main current techniques of air / fluid exchanger used in the engines are: - a cooling block directly located in the secondary vein, - a cooling block supplied with air by means of a sample of air in the vein secondary, which involves the use of an air sampling scoop and an air outlet, - a cooling device in which metal heat conductive surfaces, in contact with the fluid to be cooled, are placed in the secondary vein where the air / metal interface serves as a heat evacuation zone, this device is generally decorated with fins to obtain the exchange surface necessary for cooling.
    The first two techniques have the disadvantage of generating significant pressure losses. As for the last technique, it supposes the presence of a large exchange surface, which is also constraining. In addition, the use of large exchange surfaces can lead to reduce the acoustic treatment surface, and thus to degrade the acoustics of the engine.
    Furthermore, in the context of the last technique mentioned above, the addition of heat exchange surfaces in the air flow is generally intrusive due in particular to the fins which project into the flow, which is penalizing in terms of aerodynamic performance. It is known, to avoid or at least limit the addition of heat exchange surfaces to the detriment of acoustic treatment surfaces in the secondary vein, to have means for circulating the liquid to be cooled in an acoustic attenuation panel.
    Current solutions in this sense, however, generally provide insufficient cooling of the fluid, or a drop in aerodynamic performance due to the intrusion of a large area of fins in the flow.
    The present invention aims to remedy these drawbacks, by proposing a heat exchange and noise reduction panel for a propulsion unit, in particular an aircraft, which incorporates in an optimized manner a fluid circulation system, in particular a oil, in an acoustic attenuation system.
    SUMMARY OF THE INVENTION The subject of the invention is therefore a heat exchange and noise reduction panel for a propulsion unit, in particular an aircraft, the panel comprising: a perforated plate comprising a plurality of through orifices; a cellular structure comprising structural walls of longitudinal orientation, covered by said perforated plate and comprising between said walls cavities which define Helmoltz resonators, said through-holes forming collars of said resonators, and fluid circulation means, for example oil, at said perforated plate.
    In the panel according to the invention, said fluid circulation means comprise channels which are formed at least partly in thickened ends of said walls, on the side of said perforated plate, and / or at least partly in zones of the perforated plate located in the longitudinal extension of said over-thickened ends.
    In the present application, Helmholtz resonator is understood to mean an acoustic system comprising a neck, generally of small size, connected to a cavity of larger size and capable of resonating.
    The neck provides communication between the sound waves to attenuate and the cavity. Once the system is optimized, the neck provides visco-thermal dissipation (rapid and alternating movements of sound waves through collars that dissipate the sound energy by friction). The tuning in frequency, that is to say the optimization which makes it possible to generate these maximum speeds at the frequencies to be attenuated, is done mainly via the volume of the resonant cavities, that is to say their dimensions and in particular their height. It should be noted that, given the thermal environment, local temperatures may be taken into account to optimize the system properly.
    Thus, advantageously, the specific arrangement of the channels makes it possible to effectively integrate the fluid circulation means in the acoustic treatment structure by ensuring a good cooling of the fluid and a good acoustic attenuation. In particular, it is possible to benefit from the depth of material that the walls offer to form a narrowing of the section of the cavities over part of their height, on the side of the perforated plate, so as to provide between the cavities of the material zones. thickened with flared section in and / or on which (by "on" is meant in the longitudinal extension of the thickened ends of the walls, ie in areas facing the thickened ends) can be created recesses forming the fluid circulation channels .
    The outer surface of the perforated plate, i.e. the surface of the plate located on the side opposite to the honeycomb structure, is typically intended to be swept by an air flow.
    The channels may be partly formed by grooves opening towards the outside of the honeycomb structure and made at least partly in the thickened ends of said walls.
    The honeycomb structure and at least a portion of the perforated plate can be formed in one piece.
    An inner layer of the perforated plate may be formed in one piece with the honeycomb structure, and the perforated plate may comprise a perforated outer layer which is fixed, for example by gluing or brazing, to said inner layer and which has aligned orifices. with those of said inner layer. In this case, the channels may be partly formed in the thickened ends of the walls and partly in parts of the lower layer and / or the upper layer located in a longitudinal extension of the thickened ends of the walls.
    The perforated plate may be formed by a perforated outer plate which is fixed, for example by gluing or soldering, to the honeycomb structure. In this case, the channels may be partly formed in the thickened ends of the walls and partly in portions of the outer perforated plate located in a longitudinal extension of the thickened ends of the walls.
    The perforated outer layer, or perforated outer plate, may include grooves that face the honeycomb structure and are configured to define at least a portion of said channels.
    The grooves forming the channels may be closed by inserts which are attached to the thickened ends of said walls, on the opposite side to said structure.
    The inserts may include inserts which are engaged in the channels and fixed to the perforated plate, for example by welding.
    Said perforated outer layer, or said perforated outer plate, may be made of a flexible material, preferably a heat-conducting material, and / or of a metallic material. The invention also relates to a propulsion unit comprising at least one panel described above. The invention also relates to a method of manufacturing a panel described above. The method comprises forming channels, at least in part in the thickened ends of said walls, on the side of said perforated plate, and / or at least partly in areas of the perforated plate located in the longitudinal extension of said over-thickened ends.
    The method may include forming the perforated plate and honeycomb structure in one piece, by additive manufacturing, and forming channels in the over-thickened ends of said walls during additive manufacturing.
    The method may comprise the steps of: - forming the perforated plate and the cellular structure in a single block, for example by machining a block of material, - by removing material from the channels on one side of the plate located on the opposite side to the honeycomb structure, and - relate or fix on said plate one or more closing elements of the channels.
    DESCRIPTION OF THE FIGURES The invention will be better understood and other details, characteristics and advantages of the invention will become apparent on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which: FIG. 1 is a general perspective view of a heat exchange panel and noise reduction according to the invention, in a monolayer configuration; FIG. 2 is a general perspective view of a heat exchange and noise reduction panel according to the invention, in a multilayer configuration; - Figure 3 is a partial cross-sectional view of a panel according to the invention, according to a first embodiment; FIG. 4A is a detail perspective view from above of the panel of FIG. 3; FIG. 4B is a detail perspective view from below of the panel of FIG. 3; FIGS. 5A and 5B are cross-sectional detail views illustrating two steps of manufacturing a fluid circulation channel in a panel of FIG. 3; FIGS. 6A and 6B are cross-sectional detail views illustrating two steps for manufacturing a fluid circulation channel in a heat exchange and noise reduction panel according to the invention, in accordance with a second embodiment of FIG. production ; FIGS. 7A and 7B are cross-sectional detail views illustrating two steps for manufacturing a fluid circulation channel in a heat exchange and noise reduction panel according to the invention, according to a third embodiment of FIG. production ; FIG. 8 is a cross-sectional detail view illustrating a step of manufacturing a fluid circulation channel in a heat exchange and noise reduction panel according to the invention, according to a variant of the third embodiment of FIG. production.
    DETAILED DESCRIPTION
    As illustrated in FIG. 1, a heat exchange and noise reduction panel 1 for a propulsion unit according to the invention comprises a perforated plate 2 comprising a plurality of through holes 21, a cellular structure 3 covered by the wall 2 and a support 4 on which is disposed the honeycomb structure 3. The support 4 may be for example an air intake casing or a fan casing of the turbomachine. The honeycomb structure 3 comprises cavities 31 which define Helmoltz resonators and into which the openings 21 which form collars of the resonators open. The honeycomb structure 3 is typically made of honeycomb, the walls 32 of the structure 3 delimiting cavities 31 of generally hexagonal shape. However, it is possible to envisage other polygonal geometrical structures formed by the walls 32. The walls 32, of longitudinal orientation, may extend substantially perpendicularly to the plate 2. The panel 1 also comprises fluid circulation means, typically the oil or a coolant, not visible in Figures 1 and 2, and which are located at the perforated plate 2. The outer surface of the perforated plate 2, that is to say the surface of the plate 2 located on the opposite side to the cellular structure 3, is intended to be scanned by a flow of air which will ensure the cooling of the fluid. The panel 1 heat exchange and noise reduction may advantageously be disposed within a nacelle of the propulsion unit, particularly in the secondary vein and in the air inlet.
    In panel 1, the principle of noise attenuation is based on the generation of vortexes induced by an acoustic wave 11 (FIG. 3). It is the vortices 5 which make it possible to attenuate the acoustic energy. They are generated alternately on the inside and outside of the orifices 21 by the wave induced overpressure / depression and on either side of the plate 2.
    In a variant illustrated in FIG. 2, the panel 1 may comprise several cellular layers 3, for example two alveolar layers 3.
    According to the invention, the fluid circulation means comprise channels which are at least partly formed in thickened ends of the walls and / or at least partly in areas of the perforated wall situated in the longitudinal extension of the over-extended ends. .
    Figure 3 illustrates a first embodiment of the oil circulation channels. In this embodiment, the walls 32 of the honeycomb structure 3 and the entire perforated plate 2 are formed in one piece, which has the advantage of making the assembly robust.
    The ends of the walls 32 located on the side of the plate 2 are over-thickened, for example by forming a chamfer 7 under the plate 2 and on each side of the walls 32. Each wall 32 can thus comprise at its end located on the side of the plate 2 a portion in which its thickness increases in the direction of the plate 2, preferably substantially symmetrically with respect to the longitudinal plane of symmetry of the wall 32. Each wall 32 may in particular comprise an upper portion of substantially isosceles trapezoidal section.
    Each channel 6 is then formed in this over-thickened portion and in the perforated plate 2, above the over-thickened portion, substantially in the longitudinal extension of the wall 32 of the cellular structure 3. The plane of symmetry of each channel 6 is advantageously confused with the plane of symmetry of the wall 32 opposite which it is located.
    This produces orifices 21 of small thickness, that is to say the smallest thickness that the plate 2, and a channel thickness 6 sufficiently large to be easily machinable and integrable. Inserts 8 are advantageously engaged in the channels 6, so as to close the channels 6. The inserts 8 are fixed to the plate 2, for example by a weld 9. Thanks to the arrangement of the channels 6 in the thickness of the plate 2, the channels 6 are located near the air flow, which ensures a good heat exchange between the air and the fluid.
    FIGS. 4A and 4B, in which the elements identical to those of FIG. 3 bear the same references, are respectively views from above and below of the upper part of the panel 1, according to the first embodiment.
    Figures 5A and 5B illustrate two steps of manufacturing a fluid circulation channel 6, according to the first embodiment. The entire plate 2 and the walls 32 of the acoustic attenuation layer may be formed in a single machined metal block, typically aluminum. Each acoustic cavity 31 can be hollowed out at its upper end by means of a conical cutter to create the chamfer 7 in which is integrated the channel 6 of fluid circulation. The channel 6 can also be created by milling, on the side of the surface of the plate 2 which is swept by a flow of air. An insert 8, for example in the form of a metal strip, is then housed in the upper part of the channel 6 to close it (FIG. 5A). The lamella 8 and its housing are chamfered on the top to leave the volume required for the weld bead 9. The weld 9 is then ground, for example by milling or grinding, to obtain a smooth surface (Figure 5B).
    In a second embodiment, as illustrated in FIGS. 6A and 6B, in addition to the perforated plate 2 belonging to the part formed with the honeycomb structure 3, a second perforated plate 2A is used which is fixed on the plate 2 , for example using an adhesive 10, or by soldering. The second perforated plate 2A can be made of a flexible material having a good heat exchange capacity and resistant to heat and oil in the case where the fluid used is oil. The assembly of the two perforated plates 2 and 2A forms an assembly considered as a single perforated plate, or overall perforated plate, comprising an inner layer 2 and an outer layer 2A. It is therefore considered that the inner layer of the overall perforated plate is formed in one piece with the honeycomb structure 3.
    The second plate 2A, that is to say the outer layer of the overall perforated plate, is provided with orifices 21A which are superimposed and aligned with the orifices 21 of the inner layer that constitutes the plate 2. The The collars of the Helmoltz resonators are thus formed both in the orifices 21 and in the orifices 21 A. Each channel 6 is formed in the over-thickened portion of the wall 32 and in the perforated plate 2, above the over-thickened portion, in the longitudinal extension of the wall 32.
    In this second embodiment, the fluid circulation channels 6 are created by milling and are closed in their upper part by the second plate 2A. It is therefore no longer necessary to use an insert as in the first embodiment, and the section of the channels 6 can thus be substantially increased without significantly increasing the thickness of the panel 1. It should be noted that, thanks to the When using the second plate 2A as the outer layer of the overall perforated plate, the thickness a of the inner layer constituted by the plate 2 situated above the cavities 31 can be reduced or even zero, while the overall perforated plate can a sufficient thickness.
    In a third embodiment, as illustrated in FIGS. 7A and 7B, a second perforated plate 2A is also used, ie an outer layer of the overall perforated plate, which is fixed on the inner layer. This second plate 2A is nevertheless thicker than in the second embodiment and further comprises grooves 6A configured to form part of the channels 6 of fluid circulation. The fluid circulation channels 6 thus comprise a portion 6B formed in the thickened end of the wall 32 and in the plate 2, in the longitudinal extension of the thickened end. They also comprise a portion 6A formed in the second plate 2A, in the longitudinal extension of the thickened end of the wall 32. The second plate 2A may be made of a lighter material than aluminum, which may be flexible, and nevertheless have good heat exchange capacity. Its greater thickness makes it possible to increase the length L of the orifices 21, 21A forming the necks of the resonators, as well as the passage section of the channels 6 of fluid circulation, all with a minimum of impact on the mass of the together. The greater length of the orifices 21,21A forming the necks of the resonators makes it possible, for a given frequency of a resonator, to reduce the bulk of the air cavity of the resonator. As in the second embodiment, the thickness a of the plate 2 situated above the cavities 31 can be reduced or even zero. FIG. 8 illustrates the case where the thickness a of the plate 2 is zero. In this case, the overall perforated plate is formed by a perforated outer plate 2A 'which is fixed, for example by gluing with an adhesive 10, or by brazing, on the thickened ends of the walls 32 of the outer structure 3. The outer plate 2A 'has grooves 6A configured to form all or part of the channels 6 of fluid circulation. It is possible or not to create grooves 6B forming another part of the fluid circulation channels in the flared portions of the walls 32.
    权利要求:
    Claims (13)
    [1" id="c-fr-0001]
    1. panel (1) heat exchange and noise reduction for a propulsion system, in particular an aircraft, the panel (1) comprising: - a perforated plate (2, 2A, 2A ') comprising a plurality of through openings (21), - a honeycomb structure (3) comprising longitudinally oriented structural walls (32) covered by said perforated plate (2,2A, 2A ') and having cavities (31) between said walls (32). ) which define Helmoltz resonators, said through-holes (21) forming necks of said resonators, and - fluid circulation means (6), for example oil, at said perforated plate (2, 2A, 2A '), characterized in that said fluid circulation means comprise channels (6) which are formed at least partly in thickened ends of said walls (32), on the side of said perforated plate (2, 2A, 2A'). ), and / or at least partly in areas of the plate rforée (2, 2A, 2A ') located in the longitudinal extension of said over-thickened ends.
    [2" id="c-fr-0002]
    2. Panel (1) according to claim 1, characterized in that the channels (6) are partly formed by grooves opening towards the outside of the honeycomb structure (3) and made at least partly in the ends. over-thickened said walls (32).
    [3" id="c-fr-0003]
    3. Panel (1) according to claim 1 or 2, characterized in that the honeycomb structure (3) and at least a portion of the perforated plate (2, 2A, 2A ') are formed in one piece.
    [4" id="c-fr-0004]
    4. Panel (1) according to claim 3, characterized in that an inner layer (2) of the perforated plate (2, 2A, 2A ') is formed in one piece with the honeycomb structure (3), and that the perforated plate (2, 2A, 2A ') further comprises a perforated outer layer (2A) which is fixed, for example by gluing or soldering, to said inner layer (2) and which has orifices (21 A) aligned with those (21) of said inner layer (2).
    [5" id="c-fr-0005]
    5. Panel (1) according to claim 1 or 2, characterized in that the perforated plate (2, 2A, 2A ') is formed by a perforated outer plate (2A') which is fixed, for example by gluing or brazing, on the honeycomb structure (3).
    [6" id="c-fr-0006]
    6. Panel (1) according to claim 4 or 5, characterized in that said perforated outer layer (2A), or said perforated outer plate (2A '), comprises grooves (6A) which face the honeycomb structure (3). ) and which are configured to define at least a portion of said channels (6).
    [7" id="c-fr-0007]
    7. Panel (1) according to claim 2, characterized in that the grooves forming the channels (6) are closed by inserts (8, 2A, 2A ') which are fixed on the thickened ends of said walls (32), on the opposite side to said structure (3).
    [8" id="c-fr-0008]
    8. Panel (1) according to claim 7, characterized in that the inserts comprise inserts (8) which are engaged in the channels (6) and fixed on the perforated plate (2), for example by welding.
    [9" id="c-fr-0009]
    9. Panel (1) according to one of claims 4 to 6, characterized in that said perforated outer layer (2A), or said perforated outer plate (2A '), is made of a flexible material, preferably thermally conductive and / or a metallic material.
    [10" id="c-fr-0010]
    10. Propulsive assembly, characterized in that it comprises at least one panel (1) according to one of claims 1 to 9.
    [11" id="c-fr-0011]
    11. A method of manufacturing a panel (1) according to claim 1, characterized in that it comprises the formation of channels (6), at least partly in the thickened ends of said walls (32), on the side of said perforated plate (2, 2A, 2A '), and / or at least partly in areas of the perforated plate (2, 2A, 2A') located in the longitudinal extension of said over-thickened ends.
    [12" id="c-fr-0012]
    12. The method of claim 11, characterized in that it comprises the formation of the perforated plate (2,2A, 2A ') and the honeycomb structure (3) in one piece by additive manufacturing, and the formation of the channels (6) in the over-thickened ends of said walls (32) during additive manufacturing.
    [13" id="c-fr-0013]
    13. The method of claim 11, characterized in that it comprises the steps of: - forming the perforated plate (2) and the cellular structure (3) of a single block, for example by machining a block of material, - by removing material from the channels (6) on a face of the plate (2) located on the opposite side to the honeycomb structure (3), and - reporting or fixing on said plate (2) one or more elements of closing (8, 2A) channels (6).
    类似技术:
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    同族专利:
    公开号 | 公开日
    US10794246B2|2020-10-06|
    GB201616570D0|2016-11-16|
    FR3041704B1|2017-11-03|
    US20170089238A1|2017-03-30|
    GB2544398B|2020-11-25|
    GB2544398A|2017-05-17|
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    法律状态:
    2016-09-02| PLFP| Fee payment|Year of fee payment: 2 |
    2017-03-31| PLSC| Publication of the preliminary search report|Effective date: 20170331 |
    2017-05-04| 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
    FR1559154A|FR3041704B1|2015-09-29|2015-09-29|THERMAL EXCHANGE AND NOISE REDUCTION PANEL FOR A PROPULSIVE ASSEMBLY|FR1559154A| FR3041704B1|2015-09-29|2015-09-29|THERMAL EXCHANGE AND NOISE REDUCTION PANEL FOR A PROPULSIVE ASSEMBLY|
    US15/279,005| US10794246B2|2015-09-29|2016-09-28|Heat-exchange and noise-reduction panel for a propulsion assembly|
    GB1616570.6A| GB2544398B|2015-09-29|2016-09-29|Heat-exchange and noise-reduction panel for a propulsion assembly|
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