CN113123875A - Aeroengine sound absorption device and aeroengine - Google Patents
Aeroengine sound absorption device and aeroengine Download PDFInfo
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- CN113123875A CN113123875A CN201911406074.4A CN201911406074A CN113123875A CN 113123875 A CN113123875 A CN 113123875A CN 201911406074 A CN201911406074 A CN 201911406074A CN 113123875 A CN113123875 A CN 113123875A
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- 238000010521 absorption reaction Methods 0.000 title claims abstract description 52
- 239000006096 absorbing agent Substances 0.000 claims description 14
- 239000011358 absorbing material Substances 0.000 claims description 6
- 239000002184 metal Substances 0.000 claims description 4
- 230000000712 assembly Effects 0.000 claims description 3
- 238000000429 assembly Methods 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 6
- 239000000463 material Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000006260 foam Substances 0.000 description 1
- 239000012784 inorganic fiber Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 238000001228 spectrum Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Soundproofing, Sound Blocking, And Sound Damping (AREA)
Abstract
The invention relates to an aero-engine sound absorption device and an aero-engine. Wherein, aeroengine sound absorbing device includes: a first sound-absorbing layer comprising at least two first chambers; a second sound absorbing layer comprising at least two second chambers; and the sound absorption wedge is arranged in the second cavity. The invention can meet the requirements of lower frequency and high frequency sound absorption and improve the noise reduction effect.
Description
Technical Field
The invention relates to the field of aviation equipment, in particular to an aero-engine sound absorption device and an aero-engine.
Background
For a turbofan engine with a large bypass ratio, laying an acoustic liner on the inner wall surface of a nacelle is one of the most effective methods for noise reduction, and is widely applied. In recent years, the research work of acoustic liners is further promoted by the increasing civil aviation noise airworthiness requirement. Although sound lining technology has been studied and used for over 70 years, there are still many scientific and engineering problems that have not been solved.
Disclosure of Invention
Some embodiments of the invention provide an aircraft engine sound absorption device and an aircraft engine, which are used for relieving the problem of poor noise reduction effect.
Some embodiments of the present invention provide an aircraft engine sound absorbing device comprising:
a first sound-absorbing layer comprising at least two first chambers;
a second sound absorbing layer comprising at least two second chambers; and
and the sound absorption wedge is arranged in the second cavity.
In some embodiments, the aero-engine sound absorber includes a first plate and a second plate, the first sound absorbing layer is disposed between the first plate and the second plate, and each of the first plate and the second plate has at least two through holes.
In some embodiments, the aircraft engine sound absorbing device includes a third plate disposed on a side of the second plate remote from the first sound absorbing layer. The second sound absorbing layer is disposed between the second panel and the third panel.
In some embodiments, the cross-sectional area of the second lumen is greater than the cross-sectional area of the first lumen.
In some embodiments, the sound absorbing wedges are provided on a circumferential side wall of the second chamber.
In some embodiments, the direction of extension of the wedges is perpendicular to the thickness direction of the second acoustic layer.
In some embodiments, the circumferential side wall of the second cavity is provided with a wedge assembly, and the wedge assembly comprises at least two sound-absorbing wedges arranged at intervals along the thickness direction of the second sound-absorbing layer.
In some embodiments, at least two wedge assemblies are arranged along the circumferential direction of the side wall of the second cavity.
In some embodiments, the second cavity has a circular, triangular, quadrilateral, pentagonal, or hexagonal cross-section.
In some embodiments, the wedge includes a base portion and a wedge portion, the cross-sectional area of the base portion is the same along the length direction of the wedge, the cross-sectional area of the wedge portion is smaller, and the ratio of the dimension of the base portion along the length direction of the wedge to the dimension of the wedge portion along the length direction of the wedge is 1: 4.
in some embodiments, the sound wedges comprise a sound absorbing material and a wire mesh or perforated metal sheet encasing the sound absorbing material.
Some embodiments of the invention provide an aircraft engine comprising an aircraft engine sound absorption device as described above.
In some embodiments, the aircraft engine sound absorption device comprises an air inlet casing, and the air inlet casing is arranged on the inner surface of the air inlet casing.
Based on the technical scheme, the invention at least has the following beneficial effects:
in some embodiments, the aeroengine sound absorption device at least comprises a first sound absorption layer and a second sound absorption layer, and the sound absorption requirements of lower frequency and high frequency can be met and the noise reduction effect can be improved through a plurality of sound absorption layer structures and the sound absorption wedges arranged in one of the sound absorption layers.
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 view of an aircraft engine sound absorber provided in accordance with some embodiments of the present invention in an installed condition;
FIG. 2 is a schematic illustration in partial cross-section of an aircraft engine sound absorber provided in accordance with some embodiments of the invention;
FIG. 3 is a schematic, partially cut-away, top view of an aircraft engine sound absorber provided in accordance with some embodiments of the invention.
The reference numbers in the drawings illustrate the following:
1-a first sound absorbing layer; 11-a first cavity;
2-a second sound-absorbing layer; 21-a second cavity;
3-sound wedge; 31-a base; 32-a split portion;
4-a first plate;
5-a second plate;
6-a third plate;
7-inlet casing;
8-a hub;
9-fan blades;
10-aeroengine sound absorption.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments. It is to be understood that the described embodiments are merely a few embodiments of the invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the present invention without any inventive step, are within the scope of the present invention.
In the description of the present invention, it is to be understood that the terms "center", "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 merely for convenience in describing the present invention and for simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be taken as limiting the scope of the present invention.
As shown in fig. 2 and 3, some embodiments provide an aircraft engine sound absorption device, which comprises a first sound absorption layer 1, a second sound absorption layer 2 and a wedge 3.
The first sound-absorbing layer 1 comprises at least two first chambers 11.
In some embodiments, the first sound-absorbing layer 1 includes a plurality of first cavities 11, and adjacent first cavities 11 share a sidewall therebetween.
Optionally, the first cavity 11 of the first sound-absorbing layer 1 is enclosed by a partition.
In some embodiments, the first sound-absorbing layer 1 comprises a honeycomb core. The first chamber 11 and its circumferential side walls form a honeycomb unit, each of which is a helmholtz resonator.
The second sound-absorbing layer 2 comprises at least two second chambers 21.
In some embodiments, the second sound absorbing layer 2 comprises a plurality of second cavities 21, with a common side wall between adjacent second cavities 21.
Optionally, the second chamber 21 of the second sound-absorbing layer 2 is enclosed by a baffle.
In some embodiments, the second sound absorbing layer 2 comprises a honeycomb core. The second chamber 21 and its circumferential side wall form a honeycomb unit, each of which is a helmholtz resonator.
An acoustic wedge 3 is provided in the second chamber 21.
In some embodiments, the aero-engine sound absorber includes at least a first sound absorber layer 1 and a second sound absorber layer 2, but is not limited to two sound absorber layers, and may include a third sound absorber layer, and the like. Through a plurality of sound-absorbing layer structures to and combine the wedge 3 that absorbs sound that sets up in one of them sound-absorbing layer, can satisfy than low frequency and high frequency sound absorption requirement, improve noise reduction effect.
Dimensional parameters of the structure of each component of the sound absorption device of the aircraft engine can be set according to the target frequency.
In some embodiments, the aero-engine sound absorber comprises a first panel 4 and a second panel 5, with the first sound absorbing layer 1 disposed between the first panel 4 and the second panel 5. At least two first cavities 11 are located between the first plate 4 and the second plate 5, and at least two through holes are arranged on the first plate 4 and the second plate 5.
Optionally, the first plate 4 and the second plate 5 are both perforated plates.
In some embodiments, the aircraft engine sound absorption device comprises a third plate 6, the third plate 6 being disposed on the side of the second plate 5 remote from the first sound absorption layer 1, the second sound absorption layer 2 being disposed between the third plate 6 and the second plate 5, and at least two second cavities 21 being located between the second plate 5 and the third plate 6.
In some embodiments, the third plate 6 comprises a rigid plate. The third plate 6 has no holes and can be used as a mounting plate for mounting on an aircraft engine.
The acoustic impedance model is a conversion model of the structural parameters of the sound absorption device and the corresponding acoustic impedance values of the sound absorption device. In some embodiments, the sound absorption device for the aircraft engine includes the first sound absorption layer 1 and the second sound absorption layer 2, which are of a double-layer honeycomb sound liner structure, so that a two-degree-of-freedom sound liner acoustic impedance model is applied, and an optimal acoustic impedance value can be obtained within a constraint range according to a target sound source frequency (such as a high-order Blade Pass Frequency (BPF) sound source) through an acoustic impedance optimization method, so as to optimize and obtain structural parameters such as the plate thicknesses of the first plate 4 and the second plate 5, the sizes of the first cavity 11 and the second cavity 21, the perforation rates of the first plate 4 and the second plate 5, the thicknesses of the first sound absorption layer 1 and the second sound absorption layer 2, the depths of the first cavity 11 and the second cavity 21, and the size of the sound-absorbing wedge 3.
In some embodiments, the cross-sectional area of the second lumen 21 is greater than the cross-sectional area of the first lumen 11. Disposed within second chamber 21 is sound wedge 3.
In some embodiments, the acoustic wedges 3 are provided on the circumferential side wall of the second chamber 21.
In some embodiments, the direction of extension of the wedges 3 is perpendicular to the thickness direction of the second acoustic layer 2. Inside the second chamber 21, according to the cut-off frequency requirements, a correspondingly dimensioned acoustic wedge 3 is arranged transversely.
The thickness direction of the second sound absorption layer 2 is consistent with that of the first sound absorption layer 1, and the thickness direction of the second sound absorption layer 2 is the direction from the first sound absorption layer 1 to the second sound absorption layer 2 or the direction from the second sound absorption layer 2 to the first sound absorption layer 1.
In some embodiments, the first cavity 11 of the first sound-absorbing layer 1 is not filled with a substance or the side walls of the first cavity 11 are not provided with any substance; the lateral wall of each second chamber 21 of the second sound-absorbing layer 2 is provided with acoustic wedges 3 transversely.
Through transversely setting up wedge 3 that absorbs sound at the lateral wall of every second chamber 21 of second sound-absorbing layer 2, according to aeroengine fan low order BPF noise, through calculating target BPF frequency and wedge 3's size relation, obtain the wedge 3 that absorbs sound of required size, reach the optimization acoustic impedance design to a plurality of target frequencies to the multi-peak value sound lining design that satisfies lower frequency sound absorption requirement is realized, reaches better noise reduction.
In some embodiments, the circumferential side wall of the second chamber 21 is provided with a wedge assembly comprising at least two sound-absorbing wedges 3 arranged at intervals along the thickness direction of the second sound-absorbing layer 2.
In some embodiments, at least two wedge assemblies are provided along the circumferential direction of the sidewall of the second chamber 21.
In some embodiments, second cavity 21 has a cross-section that is circular, triangular, quadrilateral, pentagonal, hexagonal, or the like.
In some embodiments, as shown in fig. 3, the second cavity 21 has a hexagonal cross section, and six circumferential side walls of the second cavity 21 are each provided with a wedge assembly, each wedge assembly comprising two sound-absorbing wedges 3 arranged at intervals along the thickness direction of the second sound-absorbing layer 2.
In some embodiments, the cross-section of the first cavity 11 is circular, triangular, quadrilateral, pentagonal, hexagonal, or the like.
In some embodiments, as shown in fig. 2, wedge 3 includes a base portion 31 and a split portion 32, the cross-sectional area of the base portion 31 is the same along the length direction of the wedge 3, the cross-sectional area of the split portion 32 becomes smaller, and the ratio of the dimension of the base portion 31 along the length direction of the wedge 3 to the dimension of the split portion 32 along the length direction of the wedge 3 is 1: 4.
in some embodiments, the cross-sectional area of split 32 tapers from base 31 to the end of wedge 3 along the length of wedge 3 to form a point.
Since the cross-sectional area of the wedge portion 32 of the sound-absorbing wedge 3 gradually increases from the tip to the base 31, it is matched to the air characteristic impedance, and thus the incident sound waves are absorbed completely almost without reflection.
In some embodiments, the length ratio of the base 31 to the split 32 of the wedge 3 is controlled to be 1: around 4 and with a total length of typically 1/4 wavelengths for the target sound source. For a turbofan engine with a large bypass ratio, the 1 st order BPF is about 1000Hz, and if the design of the sound-absorbing wedge is performed for the target sound source, the total length of the sound-absorbing wedge is about 85 mm.
In some embodiments, sound wedges 3 comprise sound absorbing material, and a wire mesh or perforated metal sheet encasing the sound absorbing material.
In some embodiments, the surface of wedge 3 is covered with a wire mesh or perforated metal plate, which has good strength and rigidity. The sound absorption material filled in the sound absorption wedges 3 comprises inorganic fiber sound absorption material, organic fiber sound absorption material or sound absorption foam plastic and the like.
Some embodiments provide an aircraft engine comprising the aircraft engine sound absorber 10 described above.
The aero-engine sound absorption device 10 is an impedance composite sound absorption device suitable for aero-engines, can achieve the noise reduction requirements of multiple target frequencies in a targeted manner by optimizing the thickness, the aperture and the perforation rate of the first plate 4 and the second plate 5 and the sound lining structure parameters such as the depths of the first cavity 11 and the second cavity 21, can achieve a good noise reduction effect on low-order BPF (broadband Filter) noise, and can alleviate the defect that the honeycomb sound lining sound absorption frequency band of the traditional single-degree-of-freedom plate is narrow, and effectively reduce the fan noise of the aero-engine.
In some embodiments, the aircraft engine includes an inlet casing 7, a hub 8, and fan blades 9, the hub 8 and fan blades 9 being disposed within the inlet casing 7, and the fan blades 9 being disposed on the hub 8.
In some embodiments, as shown in FIG. 1, the aero-engine sound absorber 10 is disposed on an inner surface of the inlet casing 7.
In some embodiments, the aero-engine sound absorber 10 is mounted to the inner surface of the inlet casing 7 by a screw connection.
The aero-engine sound absorption device 10 can meet the noise reduction requirements of multi-target frequencies of the fan static interference noise blade passing frequency spectrum and the harmonic frequency of the fan static interference noise blade, namely meet the noise reduction requirements of the multi-target frequencies, can achieve a good noise reduction effect on low-order BPF noise and low frequency, and effectively reduces the fan noise of the aero-engine.
In the description of the present invention, it should be understood that the terms "first", "second", "third", etc. are used to define the components, and are used only for the convenience of distinguishing the components, and if not otherwise stated, the terms have no special meaning, and thus, should not be construed as limiting the scope of the present invention.
Furthermore, the technical features of one embodiment may be combined with one or more other embodiments advantageously without explicit negatives.
Finally, it should be noted that the above examples are only used to illustrate the technical solutions of the present invention and not to limit the same; although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art will understand that: modifications to the specific embodiments of the invention or equivalent substitutions for parts of the technical features may be made; without departing from the spirit of the present invention, it is intended to cover all aspects of the invention as defined by the appended claims.
Claims (13)
1. An aircraft engine sound absorbing device, comprising:
a first sound-absorbing layer (1) comprising at least two first chambers (11);
a second sound-absorbing layer (2) comprising at least two second chambers (21); and
and the sound absorption wedge (3) is arranged in the second cavity (21).
2. An aircraft engine sound-absorbing device according to claim 1, characterised in that it comprises a first plate (4) and a second plate (5), the first sound-absorbing layer (1) being arranged between the first plate (4) and the second plate (5), at least two through holes being provided in each of the first plate (4) and the second plate (5).
3. An aircraft engine sound-absorbing device according to claim 2, comprising a third plate (6), the third plate (6) being provided on the side of the second plate (5) remote from the first sound-absorbing layer (1). The second sound absorption layer (2) is arranged between the second plate (5) and the third plate (6).
4. An aircraft engine sound-absorbing device according to claim 1, characterised in that the cross-sectional area of the second cavity (21) is greater than the cross-sectional area of the first cavity (11).
5. The aeroengine sound-absorbing device according to claim 1, wherein said wedge (3) is provided on a circumferential side wall of said second chamber (21).
6. The aeroengine sound-absorbing device of claim 5, wherein the direction of extension of the wedges (3) is perpendicular to the thickness direction of the second sound-absorbing layer (2).
7. An aircraft engine sound-absorbing device according to claim 1, characterized in that the circumferential side wall of the second chamber (21) is provided with a wedge assembly comprising at least two sound-absorbing wedges (3) arranged at intervals in the thickness direction of the second sound-absorbing layer (2).
8. An aeroengine sound-absorbing device as defined in claim 7, wherein at least two of said wedge assemblies are disposed circumferentially along a sidewall of said second chamber (21).
9. An aircraft engine sound-absorbing device according to claim 1, characterised in that the cross-section of the second chamber (21) is circular, triangular, quadrangular, pentagonal or hexagonal.
10. The aircraft engine sound-absorbing device as claimed in claim 1, characterized in that the sound-absorbing wedge (3) comprises a base portion (31) and a wedge portion (32), the cross-sectional area of the base portion (31) is the same along the length direction of the sound-absorbing wedge (3), the cross-sectional area of the wedge portion (32) becomes smaller, and the ratio of the dimension of the base portion (31) along the length direction of the sound-absorbing wedge (3) to the dimension of the wedge portion (32) along the length direction of the sound-absorbing wedge (3) is 1: 4.
11. the aeroengine sound-absorbing device according to claim 1, wherein said wedge (3) comprises a sound-absorbing material, and a wire mesh or perforated metal sheet covering said sound-absorbing material.
12. An aircraft engine, characterized in that it comprises a sound-absorbing device (10) according to any one of claims 1 to 11.
13. An aircraft engine according to claim 12, characterised in that it comprises an air intake casing (7), the sound absorber (10) of the aircraft engine being provided on the inner surface of the air intake casing (7).
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| CN201911406074.4A CN113123875B (en) | 2019-12-31 | 2019-12-31 | Aeroengine sound absorption device and aeroengine |
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| CN201911406074.4A CN113123875B (en) | 2019-12-31 | 2019-12-31 | Aeroengine sound absorption device and aeroengine |
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| CN113123875B CN113123875B (en) | 2022-07-08 |
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|---|---|---|---|---|
| CN113936635A (en) * | 2021-10-25 | 2022-01-14 | 中航长沙设计研究院有限公司 | An active muffler system applied in aero-engine test room |
| CN119532247A (en) * | 2023-08-31 | 2025-02-28 | 中国航发商用航空发动机有限责任公司 | Outlet guide vane, power propulsion system and noise reduction method thereof |
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| Publication number | Publication date |
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| CN113123875B (en) | 2022-07-08 |
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