CN114909223A - Aeroengine sound lining device and aeroengine - Google Patents
Aeroengine sound lining device and aeroengine Download PDFInfo
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- CN114909223A CN114909223A CN202110171435.2A CN202110171435A CN114909223A CN 114909223 A CN114909223 A CN 114909223A CN 202110171435 A CN202110171435 A CN 202110171435A CN 114909223 A CN114909223 A CN 114909223A
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- honeycomb
- honeycomb layer
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- aero
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- 239000011148 porous material Substances 0.000 claims abstract description 20
- 230000000149 penetrating effect Effects 0.000 claims abstract description 4
- 239000006262 metallic foam Substances 0.000 claims description 7
- 230000008030 elimination Effects 0.000 abstract description 4
- 238000003379 elimination reaction Methods 0.000 abstract description 4
- 238000010586 diagram Methods 0.000 description 2
- 239000006260 foam Substances 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000002238 attenuated effect Effects 0.000 description 1
- 230000001413 cellular effect Effects 0.000 description 1
- 230000002596 correlated effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000030279 gene silencing Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/24—Heat or noise insulation
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
The invention discloses an aero-engine sound lining device and an aero-engine, relates to the field of aero-engines, and aims to optimize the noise elimination performance of the aero-engine sound lining device. The aero-engine acoustic liner device comprises a pore plate, a back plate and a honeycomb layer assembly. The pore plate is provided with a through hole penetrating through the thickness direction of the pore plate. The back plate and the orifice plate are arranged in parallel and at intervals. The honeycomb layer assembly is arranged between the pore plate and the back plate and comprises at least two honeycomb layers, and the two adjacent honeycomb layers are connected in series, in parallel or in series-parallel. According to the technical scheme, because the two adjacent honeycomb layers are connected in series, in parallel or in series-parallel, a richer impedance model is constructed, and noise can be well reduced in both the frequency range and the amplitude. With a determined thickness of the aircraft engine acoustic liner device, noise reduction over a wider frequency band can be achieved.
Description
Technical Field
The invention relates to the field of aero-engines, in particular to an aero-engine acoustic liner device and an aero-engine.
Background
For large duct high speed turbofan engines, the fan/compressor noise is greatest. The noise is divided into discrete and broadband noise, wherein rotor/stator interference noise is an important component of the fan/compressor discrete noise.
To reduce fan noise, one of the most effective approaches is to apply an acoustic liner to the wall of the inlet duct. The acoustic liner is composed of a plurality of resonant cavity structures, and the concept of acoustic impedance is commonly used in research to represent the macroscopic characteristic of sound absorption. Due to the introduction of acoustic impedance, the design of the acoustic liner in engineering practice has been developed greatly.
In the related art, the acoustic liner includes a perforated plate, a honeycomb structure, and a back solid wall. The acoustic liner can be viewed as a plurality of helmholtz resonators arranged in a pattern. The pressure fluctuation at the mouth of the resonant cavity excited by the sound waves forms pressure fluctuation accompanied with sound disturbance on the whole surface and inside of the sound lining, so that the sound energy can be converted into internal energy to be consumed.
The inventor finds that at least the following problems exist in the prior art: in the prior art, the noise elimination and reduction frequency of the acoustic liner is narrow, and the noise reduction requirement of a large-duct-ratio high-rotating-speed turbofan engine cannot be met.
Disclosure of Invention
The invention provides an aero-engine sound liner device and an aero-engine, which are used for optimizing the noise elimination performance of the aero-engine sound liner device.
The embodiment of the invention provides an aeroengine acoustic lining device, which comprises:
the pore plate is provided with a through hole penetrating through the thickness direction of the pore plate;
the back plate is parallel to the pore plate and is arranged at intervals; and
the honeycomb layer assembly is arranged between the pore plate and the back plate and comprises at least two honeycomb layers, and the adjacent two honeycomb layers are connected in series, in parallel or in series-parallel.
In some embodiments, the cellular layer comprises:
the first end of the first honeycomb layer is fixedly connected with the pore plate; and
the first end of the second honeycomb layer is fixedly connected with the second end of the first honeycomb layer, and the second end of the second honeycomb layer is fixedly connected with the back plate; wherein an opening size of each of the honeycomb cells of the second end of the second honeycomb layer is larger than an opening size of each of the honeycomb cells of the first end of the second honeycomb layer.
In some embodiments, the opening size of each cell hole of the second end of the second honeycomb layer is 2 to 4 times the opening size of each cell hole of the first end of the second honeycomb layer.
In some embodiments, each cell hole of the second cell layer is connected with each cell hole of the first cell layer in a one-to-one correspondence.
In some embodiments, the honeycomb pores of the second honeycomb layer are provided with a metal foam.
In some embodiments, the aircraft engine acoustic liner apparatus further comprises:
and the third honeycomb layer is positioned on the same layer as the second honeycomb layer, part of honeycomb holes of the first honeycomb layer are connected with the second honeycomb layer, and gaps between the adjacent second honeycomb layers are used as the third honeycomb layer.
In some embodiments, L1 ═ L2; wherein L1 is a sum of a size of an opening of a first end of each cell of the third cell layer and a size of an opening of a first end of each cell of the second cell layer, and L2 is a sum of a size of an opening of a second end of each cell of the third cell layer and a size of an opening of a second end of each cell of the second cell layer.
In some embodiments, the first end of the third honeycomb layer is coplanar with the first end of the second honeycomb layer.
In some embodiments, the second end of the third honeycomb layer is coplanar with the second end of the second honeycomb layer.
In some embodiments, the third honeycomb layer has metal foam disposed within the honeycomb cells.
The embodiment of the invention also provides an aeroengine which comprises the aeroengine sound liner device provided by any technical scheme of the invention.
According to the aircraft engine acoustic lining device provided by the technical scheme, because the two adjacent honeycomb layers are connected in series, in parallel or in series-parallel, a richer impedance model is constructed, and noise can be well reduced in the frequency range and the amplitude. With a defined thickness of the aircraft engine acoustic liner device, a noise reduction over a wider frequency band can be achieved.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without limiting the invention. In the drawings:
FIG. 1 is a schematic diagram of a layered structure of an aircraft engine acoustic liner apparatus according to an embodiment of the present invention;
FIG. 2 is a schematic perspective view of an acoustic lining device for an aircraft engine according to an embodiment of the present invention;
FIG. 3 is a schematic top view of a honeycomb layer of an aircraft engine acoustic liner apparatus provided in accordance with an embodiment of the present invention;
fig. 4 is a schematic diagram illustrating a noise reduction principle of an aircraft engine acoustic liner device according to an embodiment of the present invention.
Detailed Description
The technical solution provided by the present invention is explained in more detail with reference to fig. 1 to 4.
Referring to fig. 1 and 2, an embodiment of the invention provides an aircraft engine acoustic lining device, which is a sound attenuation structure and is laid on a wall surface of a part to be attenuated. The aeroengine acoustic lining device comprises a pore plate 1, a back plate 2 and a honeycomb layer assembly 3.
The orifice plate 1 is provided with a through hole penetrating through its thickness direction. The orifice plate 1 is, for example, a flat plate having a plurality of through holes formed therein at a predetermined perforation rate. The orifice plate 1 and the back plate 2 are correspondingly consistent in size, and the edges of the two are aligned. The back plate 2 is not provided with openings, i.e. the sound waves do not diffuse out of the holes in the back plate 2. The through holes of the orifice plate 1 and the holes of the honeycomb layer assembly 3 together form acoustic impedance for noise reduction.
The back plate 2 is arranged parallel to and spaced from the orifice plate 1. The distance between the back plate 2 and the orifice plate 1 is determined by the overall thickness of the aircraft engine acoustic liner device. In the case where the thickness of the acoustic liner device for an aircraft engine is determined, the thicknesses of the back plate 2 and the orifice plate 1 may be set as needed.
The honeycomb layer assembly 3 is arranged between the pore plate 1 and the back plate 2, the honeycomb layer assembly 3 comprises at least two honeycomb layers, and the two adjacent honeycomb layers are connected in series, in parallel or in series-parallel. The number of honeycomb layers included in the honeycomb layer assembly 3 is positively correlated with the thickness of the aero-engine acoustic liner device. The larger the thickness of the aero-engine acoustic liner device is, the larger the number of layers that the honeycomb layer assembly 3 can be provided.
The silencing process is as follows: noise enters the honeycomb layer assembly 3 through the holes on the hole plate 1, and pressure fluctuation at the mouth of the resonant cavity excited by sound waves forms pressure fluctuation accompanying sound disturbance on the whole surface and inside of the acoustic lining, so that sound energy can be converted into internal energy to be consumed. Because two adjacent honeycomb layers are connected in series, in parallel or in series-parallel, a richer impedance model is constructed, and noise can be reduced well in both frequency range and amplitude. With a determined thickness of the aircraft engine acoustic liner device, noise reduction over a wider frequency band can be achieved.
In some embodiments, the honeycomb layer includes a first honeycomb layer 31 and a second honeycomb layer 32. The first end of the first honeycomb layer 31 is fixedly connected with the orifice plate 1, for example, by gluing. Each of the cell holes of the first honeycomb layer 31 has a regular hexagonal shape, for example. The first end of the second honeycomb layer 32 is fixedly connected with the second end of the first honeycomb layer 31, and the second end of the second honeycomb layer 32 is fixedly connected with the back plate 2; wherein the opening size of each honeycomb cell of the second end of the second honeycomb layer 32 is larger than the opening size of each honeycomb cell of the first end of the second honeycomb layer 32, and the opening size of the honeycomb cell refers to the side length of the regular hexagon of the honeycomb cell. Taking the direction shown in fig. 1 as an example, "up" indicates the upper side shown in fig. 1, i.e., the side where the first end of the first honeycomb layer 31 and the first end of the second honeycomb layer 32 are located. The "lower" indicates the lower side shown in fig. 1, i.e., the side where the second end of the first honeycomb layer 31 and the second end of the second honeycomb layer 32 are located. The vertical direction shown in fig. 1 is the thickness direction of the acoustic liner apparatus for an aircraft engine. The first and second ends of the first honeycomb layer 31 are the same size. The first end of the second honeycomb layer 32 is small in size, and the second end of the second honeycomb layer is large in size, namely, the second honeycomb layer 32 is a honeycomb layer with variable size in the thickness direction of the aeroengine acoustic lining device.
In some embodiments, the opening size of each cell of the second end of the second honeycomb layer 32 is 2 to 4 times the opening size of each cell of the first end of the second honeycomb layer 32. The second honeycomb layer 32 has a small upper end and a large lower end.
In some embodiments, each cell of the second cell layer 32 is connected to each cell of the first cell layer 31 in a one-to-one correspondence. The single honeycomb holes of the second honeycomb layer 32 are connected with the single honeycomb holes of the first honeycomb layer 31 one-to-one, and the noise reduction principle is that the single honeycomb holes of the second honeycomb layer 32 and the single honeycomb holes of the first honeycomb layer 31 form a plurality of helmholtz resonant cavities connected in series, namely, a first acoustic impedance model is formed, and because the honeycomb holes of the second honeycomb layer 32 are larger in volume, the noise can be well reduced in frequency range and amplitude.
In some embodiments, the metal foam is disposed within the cell pores of the second honeycomb layer 32. And the foam metal is arranged, so that the noise reduction frequency range can be further widened.
In some embodiments, the aero-engine acoustic liner device further includes a third honeycomb layer 33, the third honeycomb layer 33 and the second honeycomb layer 32 are located on the same layer, and after some of the honeycomb holes of the first honeycomb layer 31 are connected with the second honeycomb layer 32, gaps naturally formed between adjacent second honeycomb layers 32 serve as the third honeycomb layer 33.
The single honeycomb holes of the third honeycomb layer 33 are simultaneously connected with the adjacent honeycomb holes of the first honeycomb layer 31, and the noise reduction principle is as follows: a plurality of adjacent honeycomb holes of the first honeycomb layer 31 form a helmholtz resonant cavity connected in parallel, and then form a helmholtz resonant cavity connected in series with a single honeycomb hole of the third honeycomb layer 33, that is, a second acoustic impedance model is formed. The whole resonant cavity is provided with the Helmholtz resonant cavities which are connected in parallel and the Helmholtz resonant cavities which are connected in series, so that the noise can be well reduced in the frequency range and the amplitude.
In some embodiments, L1 ═ L2; where L1 is the sum of the opening size of the first end of each cell of the third cell layer 33 and the opening size of the first end of each cell of the second cell layer 32, and L2 is the sum of the opening size of the second end of each cell of the third cell layer 33 and the opening size of the second end of each cell of the second cell layer 32. The size setting enables the uniform and regular multilayer sheet structure of the integral structure of the acoustic liner device of the aircraft engine to be convenient to install and arrange.
In some embodiments, the first end of the third honeycomb layer 33 is coplanar with the first end of the second honeycomb layer 32. In some embodiments, the second end of the third honeycomb layer 33 is coplanar with the second end of the second honeycomb layer 32. The third honeycomb layer 33 and the second honeycomb layer 32 are integrally formed into a honeycomb layer with both ends having the same size, and the third honeycomb layer 33 and the second honeycomb layer 32 are integrally formed and installed between the first honeycomb layer 31 and the back plate 2.
According to the technical scheme, the third honeycomb layer 33 and the second honeycomb layer 32 respectively form different impedance models with the first honeycomb layer 31, the aero-engine acoustic liner device simultaneously has two different impedance models, the noise reduction effect of the aero-engine acoustic liner device is greatly enhanced, and noise elimination in a wider frequency band is realized.
In some embodiments, the metal foam 4 is disposed in the cell pores of the third honeycomb layer 33. The foam metal 4 is a porous medium material and has numerous through micropores which are connected together and combined together like a plurality of resonant cavities with different combinations, so that a wider resonant frequency range can be formed, and the noise reduction frequency range is further widened. In some embodiments, the metal foam 4 fills all or part of the cell pores of the third cell layer 33, for example, so as to provide better noise reduction.
The embodiment of the invention also provides an aircraft engine which comprises the aircraft engine acoustic liner device provided by any technical scheme of the invention.
In the description of the present invention, it is to be understood that the terms "central", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be considered as limiting the scope of the present invention.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, and not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: it is to be understood that modifications may be made to the technical solutions described in the foregoing embodiments, or equivalents may be substituted for some of the technical features thereof, but such modifications or substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (11)
1. An aircraft engine acoustic liner apparatus, comprising:
the pore plate (1) is provided with a through hole penetrating through the thickness direction of the pore plate;
the back plate (2) is parallel to the pore plate (1) and arranged at intervals; and
the honeycomb layer assembly (3) is arranged between the pore plate (1) and the back plate (2), the honeycomb layer assembly (3) comprises at least two honeycomb layers, and the adjacent two honeycomb layers are connected in series, in parallel or in series-parallel.
2. The aero engine acoustic liner device of claim 1 wherein the honeycomb layer comprises:
the first honeycomb layer (31), the first end of the first honeycomb layer (31) is fixedly connected with the pore plate (1); and
a second honeycomb layer (32), wherein a first end of the second honeycomb layer (32) is fixedly connected with a second end of the first honeycomb layer (31), and a second end of the second honeycomb layer (32) is fixedly connected with the back plate (2); wherein the opening size of each cell hole of the second end of the second honeycomb layer (32) is larger than the opening size of each cell hole of the first end of the second honeycomb layer (32).
3. The aero engine acoustic liner device of claim 2 wherein the opening size of each honeycomb cell of the second end of the second honeycomb layer (32) is 2-4 times the opening size of each honeycomb cell of the first end of the second honeycomb layer (32).
4. The aero engine acoustic liner device of claim 2 wherein each cell of the second honeycomb layer (32) is connected to each cell of the first honeycomb layer (31) in a one-to-one correspondence.
5. The aircraft engine acoustic liner apparatus as set forth in claim 2 wherein the honeycomb cells of said second honeycomb layer (32) are provided with a metal foam.
6. The aircraft engine acoustic liner apparatus of claim 2, further comprising:
and a third honeycomb layer (33) which is located at the same layer as the second honeycomb layer (32), wherein part of the cells of the first honeycomb layer (31) are connected with the second honeycomb layer (32), and the gaps between the adjacent second honeycomb layers (32) are used as the third honeycomb layer (33).
7. The aero engine acoustic liner device of claim 6 wherein L1 ═ L2; wherein L1 is a sum of an opening size of a first end of each cell of the third cell layer (33) and an opening size of a first end of each cell of the second cell layer (32), and L2 is a sum of an opening size of a second end of each cell of the third cell layer (33) and an opening size of a second end of each cell of the second cell layer (32).
8. The aero engine acoustic liner device of claim 6 wherein a first end of the third honeycomb layer (33) is coplanar with a first end of the second honeycomb layer (32).
9. The aero engine acoustic liner device of claim 6 wherein a second end of the third honeycomb layer (33) is coplanar with a second end of the second honeycomb layer (32).
10. The aero-engine acoustic liner device of claim 6 wherein the third honeycomb layer (33) has metal foam disposed within the honeycomb cells.
11. An aircraft engine comprising an aircraft engine acoustic liner apparatus according to any of claims 1 to 10.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110171435.2A CN114909223A (en) | 2021-02-08 | 2021-02-08 | Aeroengine sound lining device and aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110171435.2A CN114909223A (en) | 2021-02-08 | 2021-02-08 | Aeroengine sound lining device and aeroengine |
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| Publication Number | Publication Date |
|---|---|
| CN114909223A true CN114909223A (en) | 2022-08-16 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110171435.2A Pending CN114909223A (en) | 2021-02-08 | 2021-02-08 | Aeroengine sound lining device and aeroengine |
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| CN (1) | CN114909223A (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3831710A (en) * | 1973-01-24 | 1974-08-27 | Lockheed Aircraft Corp | Sound absorbing panel |
| EP0405581A1 (en) * | 1989-06-30 | 1991-01-02 | Nitto Boseki Co., Ltd. | Sound absorber |
| US20150292413A1 (en) * | 2014-04-11 | 2015-10-15 | Rohr, Inc. | Acoustic liner |
| US20160123160A1 (en) * | 2014-10-30 | 2016-05-05 | United Technologies Corporation | Thermal-Sprayed Bonding of a Ceramic Structure to a Substrate |
| CN107023402A (en) * | 2015-12-30 | 2017-08-08 | 通用电气公司 | Acoustic lining for gas turbine engine component |
| CN110230541A (en) * | 2018-03-05 | 2019-09-13 | 通用电气公司 | Acoustics bushing with inclination honeycomb |
| CN110431295A (en) * | 2017-02-01 | 2019-11-08 | 通用电气公司 | Continuous freedom degree sound core |
| CN209674870U (en) * | 2018-12-29 | 2019-11-22 | 沈阳鼓风机集团股份有限公司 | A kind of compressor entrance noise elimination noise reduction structure |
| CN111696502A (en) * | 2020-06-01 | 2020-09-22 | 西安交通大学 | Underwater sound absorption metamaterial structure with damping lining and double-layer honeycomb perforated plate |
| CN111749793A (en) * | 2019-03-29 | 2020-10-09 | 通用电气公司 | Acoustic liner with enhanced acoustic absorption and reduced drag characteristics |
| CN112278294A (en) * | 2020-10-30 | 2021-01-29 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Noise elimination structure of airplane nacelle |
| CN212461140U (en) * | 2020-06-30 | 2021-02-02 | 南昌航空大学 | Honeycomb-micro-perforated structure with adjustable sound absorption performance |
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2021
- 2021-02-08 CN CN202110171435.2A patent/CN114909223A/en active Pending
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3831710A (en) * | 1973-01-24 | 1974-08-27 | Lockheed Aircraft Corp | Sound absorbing panel |
| EP0405581A1 (en) * | 1989-06-30 | 1991-01-02 | Nitto Boseki Co., Ltd. | Sound absorber |
| US20150292413A1 (en) * | 2014-04-11 | 2015-10-15 | Rohr, Inc. | Acoustic liner |
| US20160123160A1 (en) * | 2014-10-30 | 2016-05-05 | United Technologies Corporation | Thermal-Sprayed Bonding of a Ceramic Structure to a Substrate |
| CN107023402A (en) * | 2015-12-30 | 2017-08-08 | 通用电气公司 | Acoustic lining for gas turbine engine component |
| CN110431295A (en) * | 2017-02-01 | 2019-11-08 | 通用电气公司 | Continuous freedom degree sound core |
| CN110230541A (en) * | 2018-03-05 | 2019-09-13 | 通用电气公司 | Acoustics bushing with inclination honeycomb |
| CN209674870U (en) * | 2018-12-29 | 2019-11-22 | 沈阳鼓风机集团股份有限公司 | A kind of compressor entrance noise elimination noise reduction structure |
| CN111749793A (en) * | 2019-03-29 | 2020-10-09 | 通用电气公司 | Acoustic liner with enhanced acoustic absorption and reduced drag characteristics |
| CN111696502A (en) * | 2020-06-01 | 2020-09-22 | 西安交通大学 | Underwater sound absorption metamaterial structure with damping lining and double-layer honeycomb perforated plate |
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