• 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:
    An acoustic coating (22; 22 ') has a honeycomb layer (38) disposed between a first panel (40; 40') and a permeable panel (42; 42 ') and comprises a set of multiple sinuous walls ( 96; 96 ') spaced from one another. The adjacent sinuous walls (96a, 96b) partially define a first region (102; 102 ') carried by the first panel (40; 40') and a second opposite region (104; 104 ') carried by the permeable panel (42; 42 '). The first and second regions (102, 104; 102 ', 104') are offset such that the median distance extending between the regions (102, 104; 102 ', 104') and centered between adjacent walls (96, 104 ') 96 ') is greater than a distance measured directly between the panels (40, 42; 40', 42 '), allowing the design of thinner acoustic coatings (22; 22'). The regions (102, 104; 102 ', 104') and adjacent walls (96; 96 ') further define a cell (46; 46') having a constricted portion (106) communicating between an end portion (108; ) and an input portion (1 10) so that the constricted portion (106) creates a frequency offset.
    公开号:FR3019775A1
    申请号:FR1553061
    申请日:2015-04-09
    公开日:2015-10-16
    发明作者:Christian Soria；Jose S Alonso-Miralles；Hwa-Wan Kwan
    申请人:Rohr Inc；
    IPC主号:
    专利说明:

    [0001] Background of the Invention [0001] The present disclosure relates to an acoustic coating and more particularly to a passive acoustic honeycomb coating for attenuating noise emitted by, for example, a gas turbine engine. [0002] A gas turbine engine may comprise an acoustic coating to attenuate the noise generated during operation of the engine. A typical acoustic coating comprises a honeycomb core connected between a solid protective sheet and a perforated protective sheet. This honeycomb core contains many resonant cavities. The honeycomb core may have a height that tunes the resonant cavities to a specific target frequency of the noise to be attenuated. [0003] New aircraft engine designs have to comply with increasing restrictions imposed on noise emissions at airports by many government regulators. As a result, recent trends in aircraft engine design have highlighted the need for acoustic coatings that provide soundproofing, such as acoustic absorption of tonal and wideband noise at relatively lower frequencies, while occupying substantially the same space or less space than previous coatings. There is therefore a technological need for an acoustic soundproofing panel with a reduced thickness of acoustic coating. SUMMARY [0004] An acoustic coating, according to a non-limiting embodiment of the present disclosure, comprises a panel; a permeable panel spaced from the first panel; a set of multiple sinuous walls spaced apart from each other; and wherein each of the respective sinuous walls extends between the panel and the permeable panel. Moreover, in the embodiment already mentioned, the panel is non-permeable. Alternatively or complementary thereto, in the embodiment already mentioned, the coating comprises a set of multiple walls spaced from each other; and wherein each of the respective walls passes through a set of multiple sinuous walls and extends between the panel and the permeable panel. Alternatively or in addition to this, in the embodiment already mentioned, a cell is defined between the first and second adjacent walls of the set of multiple walls, between the first and second adjacent sinuous walls of the wall. set of multiple walls, and between a first region of the panel and a second region of the permeable panel. Alternatively or complementary thereto, in the embodiment already mentioned, the first and second regions are shifted along the respective panels. Alternatively or complementary thereto, in the embodiment already mentioned, the first and second regions are spaced apart from each other along the respective panels. Alternatively or complementary thereto, in the embodiment already mentioned, the second region comprises a perforation. Alternatively or in addition to this, in the embodiment already mentioned, the cell has a first portion partially defined by the first region, a second portion partially defined by the second region, and a constricted portion communicating with fluidly between the first and second parts and partially defined between the first and second sinuous walls. Alternatively or complementary thereto, in the embodiment already mentioned, each wall of the set of multiple sinuous walls extends laterally from the panel to the permeable panel and provides a sinuous cross-sectional profile. A coating for a turbofan engine according to another embodiment, not limiting, comprises a honeycomb layer having a set of multiple walls spaced from each other, each wall having a first curved portion and a Second part opposite curve; a first panel disposed substantially concentrically with respect to an axis of the motor and including a first region defined between adjacent walls of the plurality of multiple walls; a perforated panel radially spaced inwardly of the first panel, and including a second region defined between adjacent walls of the plurality of multiple walls; and wherein the first region is opposite and offset from the second region. In addition to the embodiment already mentioned, the coating comprises a cell having an end portion, a constricted portion, and an inlet portion with the constricted portion fluidly communicating between the end portion and the end portion. entrance part; and wherein the end portion is partially defined by the first region and the adjacent walls, the constricted portion is defined between the adjacent walls, and the inlet portion is defined between the adjacent walls and the second region. Alternatively or complementary thereto, in the embodiment already mentioned, the adjacent walls generally overlap at the constricted portion during an observation in a direction substantially perpendicular to the perforated panel. Alternatively or complementary thereto, in the embodiment already cited, a median distance extending through the cell and from the first panel to the perforated panel is greater than a distance measured directly between the first panel and the perforated panel. [0017] Alternatively or in addition to this, in the embodiment already cited, the first panel is solid, and a hole in the perforated panel communicates fluidly with the input portion. Alternatively or complementary to it, in the embodiment already mentioned, the multiple walls are substantially identical to each other. The features and elements already mentioned may be associated within 10 different combinations and non-exclusive, unless otherwise expressly stated. These features and elements, as well as their operation, will appear more clearly in light of the following description and accompanying diagrams. It should be understood, however, that the following description and figures are intended to serve as examples and are not limiting. BRIEF DESCRIPTION OF THE DRAWINGS [0020] Various features will become apparent to those skilled in the art from the following detailed description of the disclosed non-limiting embodiments. The diagrams accompanying the detailed description may be briefly described as follows: [0021] FIG. 1 shows a partial cross-section of a turbofan engine comprising an acoustic coating according to the present disclosure; [0022] FIG. 2 is a partial perspective view of the acoustic coating with portions removed to display the detail; [0023] FIG. 3 represents a cross section of the acoustic coating; [0024] FIG. 4 shows a cross section of the acoustic coating along line 4-4 of FIG. 3; [0025] FIG. 5 shows a cross section of the second embodiment of the acoustic coating; and [0026] FIG. 6 shows a cross section of the acoustic coating along the line 6-6 of FIG. 5. DETAILED DESCRIPTION [0027] Referring to FIG. 1, a turbojet engine 20 is illustrated as an example of an application using an acoustic liner 22 according to the present disclosure. The motor 20 is centered about an axis A, and comprises a suction hood of the nacelle 24, a ventilation section 26 downstream of the suction hood 24, an annular air bypass flow path 28 downstream of the ventilation section 26 and defined between the inner and outer radial walls 30, 32, a motor body 34 located radially inward of the inner wall 30, and an ejection nozzle 36 located downstream of the body 34. The acoustic coating 22 may be carried by the wall oriented radially towards the inside of the suction hood 24, the inner and / or outer walls 30, 32 and / or the ejection nozzle 36 to eliminate the noise in the respective neighborhoods. It is further contemplated and understood that acoustic coating 22 may be used in any other application where noise suppression is desirable. Referring to FIGs. 2 to 4, the acoustic coating 22 may have a honeycomb layer 38 sandwiched between two panels 40, 42. The panel 40 may be a base or support panel that is generally solid and impervious. The panel 42 may be a membrane that is permeable and can be perforated by having a set of multiple holes or perforations 44, with at least one hole or perforation communicating with one of the cells of the multiple cell assembly 46 in the honeycomb layer 38. Alternatively, the panel 42 may be configured as a crosslinked layer, a combination of a perforated layer and a crosslinked layer, a screen or other type of membrane permitting the passage air. The panels 40 and 42 may be regularly spaced from each other and have substantially a flat surface; or, depending on the application, the panels 40 and 42 may be cylindrical in shape and spaced apart from one another around, for example, the axis of the motor A. Although currently illustrated in the form of an acoustic coating having a single degree of freedom (a resonance), it is further contemplated and understood that the panel 40 may also be permeable and lined with another sound-absorbing or honeycomb layer to produce a multilayer acoustic coating . Furthermore, with regard to the application of the turbojet engine 20 (see FIG 1), the permeable panel 42 of the acoustic coating 22 is a perforated panel having a first face 86 which partially defines the cell 46 and an opposite face 88 which can define a passage of air in or around the engine. For example, the face 88 may be generally cylindrical and may define, at least partially, an intake passage 90 of the suction hood 24. Alternatively, the face 88 may define, at least partially, the flow path Bypass 28 and / or exhaust channel 92 of the ejection nozzle 36. It will be appreciated by those skilled in the art that the physical dimensions of the acoustic coating 22 may be modified or configured to suppress the bandwidths corresponding to the resonance frequencies targeted without giving up the benefits of the novelties of this disclosure. For example, the coating 22 may be configured to suppress the bandwidths corresponding to the relatively high frequencies emitted by a turbine section of the motor body 34, or to suppress the bandwidths corresponding to the lower frequencies emitted by a section of the combustion chamber. of the motor body 34. The honeycomb layer 38 may comprise a set of first multiple walls 94 which are spaced from each other, and a set of second multiple walls 96 also spaced from each other and passing through. the plurality of first multiple walls 94 thereby defining an array or array of cells 46. Referring to FIG. 2, the first walls 94 may extend longitudinally (at least partially, or mainly), along a y-coordinate, and the second walls 96 may extend longitudinally (at least partially, or mainly), along 'an x coordinate. The panels 40, 42 may each extend primarily in the respective x-y coordinate planes, and the walls 94, 96 may extend laterally and at least partially between the panels 40, 42 in a z coordinate axis. The first walls 94 may have substantially a flat surface, parallel to each other and disposed substantially perpendicular to the panels 40, 42. The second walls 96 pass laterally to retain the panels 40, 42 and may be generally identical and redirected , or sinuous, in the lateral direction. In other words, a cross-sectional profile of the wall 96 taken in the x-z plane resembles a sinuous profile having opposite curved portions 98, 100 (ie, dug in substantially opposite directions). The cells 46 may thus be in a sinuous shape, each cell being defined by adjacent serpentine walls 96, adjacent walls 94 intersecting walls 96, and regions 102,104 opposite the respective panels 40, 42. Each region 102, 104 may be of orthogonal and / or substantially square shape with an outer perimeter generally defined by the joining walls 94, 96. Due to the opposed curved portions 98, 100, the opposite regions 102, 104 are offset from each other substantially in the axis x coordinate. The curved portions 98, 100 may have a constricted or progressive curvature, or any type of redirection less than ninety degrees. In other words, as the serpentine wall 96 passes substantially in a positive direction of z coordinate, the wall is redirected (at least partially) in a x coordinate axis at the second curved portion 100, and is then redirected again in the substantially positive direction of coordinate z at the first curved portion 98. Each curved portion 98, 100 may have an angular range (ie a redirection angle) of approximately forty five degrees to ninety degrees. Each cell 46 has a constricted portion 106 communicating between an end portion 108 and an inlet portion 110 which communicates with the hole 44. The end portion 108 is partially defined by the region 102 of the panel 40 and has a flow section surface generally equal to, or slightly smaller than, the area of the region 102. Similarly, the inlet portion 110 is partially defined by the region 104 of the face 86 of the panel 42 and has a surface of the flow which is generally equal to, or slightly less than, the area of the region 104. The constricted portion 106 has a substantially smaller flow area than the flow sections of the end and inlet portions 108, 110. This constriction modifies the dynamics of the cavity to produce a frequency shift in the resonances (and / or antiresonances), which could be adapted to certain target frequencies depending on the amplitude of the constriction and its location along the axis of the cavity. An axis of each cell 46 has a median distance or length (see arrow 112) which is greater than a z-coordinate distance (see arrow 114) between the two panels 40, 42. The larger the offset is between the regions 102, 104, the greater the median distance 112 is large. As illustrated in FIG. 3, this offset may be such that the regions 102, 104 are spaced from each other along the x-coordinate axis. When the regions 102, 104 are spaced apart, the adjacent sinuous walls 96 overlap each other. In other words, a cross-sectional profile of the acoustic coating 22 taken along a plane yz and through a central point 116 of the constricted portion 106 will illustrate a first sinuous wall 96a located below a second adjacent sinuous wall 96b (see FIG. 4). More precisely, during a radially directed observation, the adjacent sinuous walls 96 overlap each other. Because the adjacent sinuous walls 96a, 96b overlap one and the other, it is the same for the adjacent cells 46. More precisely, and taking into account the set of multiple cells 46 having adjacent cells 46a, 46b, 46c aligned along the x-coordinate axis, and when observing the cross-sectional profile in the yz plane via the central point 116, the constricted portion 106 of the cell 46b is between the 110 of the cell 46a and the end portion 108 of the cell 46c. However, the sinuous wall 96a is located therebetween and it partially defines the constricted portion 106 of the cell 46b and the input portion 110 of the cell 46a, and the sinuous wall 96b is located therebetween and defines partially the constricted portion 106 of the cell 46b and the end portion 108 of the cell 46c. The median distance 112 is the effective distance that dictates which frequency ranges can be suppressed. As a general rule, by increasing the distance 112, the acoustic coating 22 can suppress lower frequency ranges. The sinuous walls 96 thus fulfill two advantageous functions; on the one hand, the constricted portion 106 creates a frequency shift, and on the other hand, increasing the median distance 112 allows the removal of lower frequency ranges than the much thicker acoustic coatings usually required. The axis 112 generally extends through the central point 116 of the constricted portion 106. Each central point 116 of each cell 46 may be substantially in a common x-y plane. The central point 116 may or may not be centered between the panels 40, 42. Generally, the placement of this central point 116 relative to the panels 40, 42 is one of the many ways to adapt the acoustic coating 22 to a specific application.
    [0002] In principle, when the central point 116 is centered between the panels 40, 42, an antiresonance cell is configured or shifted to lower frequencies. If the center point 116 is located closer to the panel 42 (or membrane), a first cell resonance is shifted to a lower frequency and the antiresonance can not be changed. If the center point 116 is moved to the back panel 40, a second cell resonance may be modified, but the first resonance and antiresonance of the cell may remain about the same.
    [0003] 100371 The acoustic coating 22 can be made of all types of materials depending on a particular application, including metals, composites and ceramics. For example, if the acoustic coating 22 is applied to the ejection nozzle 36 of the turbojet engine 20, a ceramic coating may be desirable to withstand high temperature exposure. The coating can be manufactured using any combination of known manufacturing techniques; the most complex coatings can be made using, at least partially, a method of manufacturing additives.
    [0004] 100381 Referring to FIGs. 5 and 6, a second nonlimiting embodiment of the present disclosure is illustrated, in which elements identical to the first embodiment have the same identification numbers, with the exception of the addition of a symbol. main. In the second embodiment, an acoustic coating 22 'has a matrix of cells 46', each being defined longitudinally by walls 94 ', 96' and an end region 102 'carried by a panel 40' and a input region 104 'carried by a front panel 42'. The walls 96 'may be generally sinuous in shape, but the adjacent walls 96' can not overlap each other. In other words, the regions 102 ', 104' can be shifted from each other in the x-coordinate axis, but they can not be spaced from each other with respect to the same axis.
    [0005] 100391 For greater certainty, relative position terms such as "forward", "backward", "superior", "lower", "above", "below" and similar terms 25 refer to the normal operating position and should not be considered as otherwise limiting qualifiers. It is also accepted that the reference numbers identify corresponding or similar elements across several schemes. It should be understood that although a particular component arrangement is described in the illustrated embodiment, other arrangements may also be of interest. Although particular step sequences may be presented and described, it is understood that the steps may be performed in any order, separate or combined, unless otherwise indicated, benefiting from the present disclosure. The above description is given by way of example rather than defined by the described limits. Various non-limiting embodiments are disclosed; however, those skilled in the art will understandably appreciate, in light of the foregoing teachings, that various modifications and variations will fall within the scope of this disclosure.
    权利要求:
    Claims (15)
    [0001]
    REVENDICATIONS1. Acoustic coating (22; 22 ') comprising: a panel (40; 40'); a permeable panel (42; 42 ') spaced from the first panel (40; 40'); and a set of multiple sinuous walls (96; 96 ') spaced from each other, wherein each of the respective sinuous walls (96; 96') extends between the panel (40; 40 ') and the permeable panel (42; 42 ').
    [0002]
    Acoustic coating (22; 22 ') according to claim 1, wherein the panel (40; 40') is non-permeable.
    [0003]
    The acoustic coating (22; 22 ') of claim 1 or 2 further comprising a plurality of spaced apart multiple walls (94; 94') in which each respective wall (94; assembly of multiple sinuous walls (96; 96 ') and extends between the panel (40; 40') and the permeable panel (42; 42 ').
    [0004]
    An acoustic coating (22; 22 ') according to claim 3, wherein a cell (46; 46') is defined between the first and second adjacent walls of the plurality of multiple walls (94; first and second sinuous walls (96a; 96b) of the plurality of multiple sinuous walls (96; 96 '), and between a first region (102; 102') of the panel (40; 40 ') and a second region ( 104; 104 ') of the permeable panel (42; 42').
    [0005]
    An acoustic coating (22; 22 ') according to claim 4, wherein the first and second regions (102, 104; 102', 104 ') are offset from one another along the respective panels (40). , 42, 40 ', 42').
    [0006]
    Acoustic coating (22; 22 ') according to claim 4 or 5, wherein the first and second regions (102, 104; 102', 104 ') are spaced apart from one another along the respective panels. (40, 42, 40 ', 42').
    [0007]
    An acoustic coating (22; 22 ') according to claim 4, 5 or 6, wherein the second region (104; 104') comprises a perforation (44; 44 ').
    [0008]
    An acoustic coating (22; 22 ') according to any one of claims 4 to 7, wherein the cell (46; 46') has a first portion (108) partially defined by the first region (102; 102 '), a second portion (110) partially defined by the second region (104; 104'), and a constricted portion (106) fluidly communicating between the first and second portions (108, 110) and partially defined between first and second sinuous walls (96a, 96b).
    [0009]
    An acoustic coating (22; 22 ') according to any one of the preceding claims, wherein each wall of the set of multiple sinuous walls (96; 96') extends laterally of the panel (40; 40; ') to the permeable panel (42; 42') and comprises a sinuous cross sectional profile.
    [0010]
    10. A coating (22; 22 ') for a dual flow turbojet (20) comprising: a honeycomb layer (38) having a plurality of spaced apart multiple walls (96; 96'), each wall; (96; 96 ') having a first curved portion (98) and a second opposed curved portion (100); A first panel (40; 40 ') disposed substantially concentrically with respect to an axis of the motor (A) and including a first region (102; 102') defined between adjacent walls (96a, 96b) of the assembly multiple walls (96; 96 '); anda perforated panel (42; 42 ') spaced radially inward of the first panel (40; 40'), and comprising a second region (104; 104 ') defined between adjacent walls (96a, 96b) of the set of multiple walls (96; 96 '), wherein the first region is opposite and offset from the second region (104; 104').
    [0011]
    The acoustic coating (22; 22 ') of claim 10, further comprising a cell (46; 46') having an end portion (108), a constricted portion (106), and an inlet portion (106); 110) with the constricted portion (106) fluidly communicating between the first and second portions and partially defined between the end portion (108) and the inlet portion (110), wherein the end portion (108) ) is partially defined by the first region (102; 102 ') and the adjacent walls (96a, 96b), the constricted portion (106) is defined between the adjacent walls (96a, 96b), and the inlet portion (110b); ) is defined between the adjacent walls (96a, 96b) and the second region (104; 104 ').
    [0012]
    The acoustic coating (22; 22 ') according to claim 11, wherein the adjacent walls (96a, 96b) generally overlap at the constricted portion (106) when viewed in a direction substantially perpendicular to the perforated panel. (42; 42 ').
    [0013]
    An acoustic coating (22; 22 ') according to claim 11 or 12, wherein a median distance extending through the cell (46; 46') and from the first panel (40; 40 ') to the perforated panel (42; 42 ') is greater than a distance measured directly between the first panel (40; 40') and the perforated panel (42; 42 ').
    [0014]
    An acoustic coating (22; 22 ') according to claim 11, 12 or 13, wherein the first panel (40; 40') is solid, and a hole (44; 44 ') in the perforated panel (42; ') communicates fluidly with the input portion (110).
    [0015]
    Acoustic coating (22; 22 ') according to any one of claims 10 to 14, wherein the multiple walls (96; 96') are substantially identical to each other.
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    法律状态:
    2016-03-22| PLFP| Fee payment|Year of fee payment: 2 |
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    US14/251,226|US9476359B2|2014-04-11|2014-04-11|Acoustic liner|
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