CN113103689A - Airplane nacelle noise elimination device based on lattice configuration and manufacturing method thereof - Google Patents

Airplane nacelle noise elimination device based on lattice configuration and manufacturing method thereof Download PDF

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Publication number
CN113103689A
CN113103689A CN202110483954.2A CN202110483954A CN113103689A CN 113103689 A CN113103689 A CN 113103689A CN 202110483954 A CN202110483954 A CN 202110483954A CN 113103689 A CN113103689 A CN 113103689A
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China
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lattice
interlayer
plate
dot matrix
back plate
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CN113103689B (en
Inventor
刘倩
张烨
马立敏
胡震东
张嘉振
张颖哲
石越
齐山贺
彭俊阳
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Commercial Aircraft Corp of China Ltd
Beijing Aeronautic Science and Technology Research Institute of COMAC
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Commercial Aircraft Corp of China Ltd
Beijing Aeronautic Science and Technology Research Institute of COMAC
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/01—Layered products comprising a layer of metal all layers being exclusively metallic
    • B32B15/016—Layered products comprising a layer of metal all layers being exclusively metallic all layers being formed of aluminium or aluminium alloys
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B15/043—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of metal
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/06—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B27/08—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form
    • B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
    • B32B3/12—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B33/00—Layered products characterised by particular properties or particular surface features, e.g. particular surface coatings; Layered products designed for particular purposes not covered by another single class
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
    • B32B7/04—Interconnection of layers
    • B32B7/10—Interconnection of layers at least one layer having inter-reactive properties
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
    • B32B7/04—Interconnection of layers
    • B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/10—Properties of the layers or laminate having particular acoustical properties
    • B32B2307/102—Insulating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2605/00—Vehicles
    • B32B2605/18—Aircraft
    • 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
    • Y02T50/40—Weight reduction

Abstract

An airplane nacelle noise elimination device based on lattice configuration and a manufacturing method thereof relate to the technical field of airplane noise elimination devices and comprise the following steps: the micro-porous plate is used for transmitting sound waves; the lattice interlayer is used for reflecting the sound waves input through the micropore plate and dissipating sound wave energy to realize noise elimination; the back plate is used for supporting the dot matrix interlayer and discharging accumulated liquid in the dot matrix interlayer; the lattice interlayer is arranged between the microporous plate and the back plate and comprises a plurality of lattice cells arranged in a lattice manner. The silencer disclosed by the invention is composed of a lattice structure, has the characteristics of small volume density, large specific surface area and high structural efficiency, can effectively eliminate sound wave noise of each wavelength while ensuring the structural strength, and can control the manufacturing cost and the structural weight within a lower range.

Description

Airplane nacelle noise elimination device based on lattice configuration and manufacturing method thereof
Technical Field
The invention relates to the technical field of airplane noise elimination devices, in particular to an airplane nacelle noise elimination device based on a dot matrix configuration and a manufacturing method thereof.
Background
The airplane nacelle is one of the key parts of the airplane propulsion system, consists of an air inlet, a fan cover, a reverse thrust system and a tail spraying device, and provides multiple functions of system protection, pneumatic rectification, noise reduction, ventilation, liquid drainage, maintenance and the like for an engine. In airworthiness terms, strict requirements are placed on the noise of the aircraft operating in each scene. The engine is used as a main noise source in the takeoff stage of the airplane, and the noise reduction level of the nacelle directly influences the overall performance and the airworthiness evidence obtaining result of the airplane.
At present, the aircraft nacelle mainly applies the sound lining technology to reduce the fan noise of an engine, and the technical core is to design a noise eliminator in a nacelle air inlet channel, a reverse thrust structure and a tail jet system to weaken the energy of noise in the transmission process, so that the noise radiated to the ground is reduced.
The typical silencing structure of the airplane nacelle is in a form of a micro-perforated plate and a honeycomb sandwich layer and consists of a micro-perforated panel, a honeycomb sandwich layer and a back plate. Aircraft are weight-sensitive products and manufacturers desire to maximize aircraft structural strength and performance with a minimum of materials and a minimum of weight. The fine noise elimination design brings complexity of structure and assembly, and under the traditional process scheme, the honeycomb is single in structure, so that the wavelength range of the absorbed sound wave is narrow; the strength and rigidity of the fiber screen are not enough, and the problem of hole blockage is easy to occur in assembly and bonding. Meanwhile, because the modulus in the honeycomb structure surface is low, the strength of the traditional honeycomb interlayer along the course of the engine is weak, and the structural efficiency is not high in the bird collision scene of an air inlet channel.
Disclosure of Invention
The invention provides an airplane nacelle noise elimination device based on a lattice configuration and a manufacturing method thereof, wherein the nacelle noise elimination device is composed of a lattice structure, has the characteristics of small volume density, large specific surface area and high structural efficiency, can effectively eliminate sound wave noise of each wavelength while ensuring the structural strength, and can control the manufacturing cost and the structural weight within a lower range.
In order to achieve the purpose, the invention adopts the technical scheme that:
according to a first aspect of the invention, there is provided an aircraft nacelle acoustic abatement device based on a lattice configuration, comprising:
the micro-porous plate is used for transmitting sound waves;
the lattice interlayer is used for reflecting the sound waves input through the micropore plate;
the back plate is used for supporting the dot matrix interlayer and discharging accumulated liquid in the dot matrix interlayer;
the lattice interlayer is arranged between the microporous plate and the back plate and comprises a plurality of lattice cells arranged in a lattice manner.
Further, the lattice cell includes a plurality of interconnected members, wherein any one of the members has at least two common nodes with the other members.
Further, the member comprises a rod-shaped member and/or a plate-shaped member, and the cross section of the rod-shaped member comprises a circle and/or a square.
Further, the lattice cell is of a symmetrical configuration and the lattice cell is at least symmetrical about a plane passing through a center position of the lattice cell or at least symmetrical about the center position of the lattice cell.
Furthermore, the surface roughness of the lattice cell is larger than 5 μm, and the lattice cell can reflect sound waves.
Furthermore, the junction of the lattice interlayer and the microporous plate is not sealed, and the junction of the lattice interlayer and the backboard is not sealed.
Furthermore, the micropore plate comprises a pneumatic surface far away from one side of the dot matrix interlayer, and the pneumatic surface is a smooth surface.
Furthermore, the micropore plate and the dot matrix interlayer are integrally formed, and the back plate can be integrally formed with the micropore plate and the dot matrix; or the microporous plate can be glued or welded with the dot matrix interlayer after the formation of the microporous plate and the dot matrix interlayer is finished.
Furthermore, at least part of the dot matrix cells have different heights, and the shape of the back plate is adapted to the heights of the dot matrix cells.
Furthermore, the micropore plate is provided with a plurality of through holes, and the diameter of each through hole is 1-3 mm.
Furthermore, the back plate is provided with at least one liquid discharge hole, and the diameter of the liquid discharge hole is not less than 2 mm.
According to a second aspect of the present invention, there is provided a method for manufacturing an aircraft nacelle noise silencer device based on a lattice configuration, the method being used for manufacturing the aircraft nacelle noise silencer device, and comprising:
step 1: selecting additive materials and manufacturing a formed noise eliminator through an additive process, wherein the noise eliminator comprises a microporous plate, a dot matrix interlayer and a back plate;
the back plate, the micropore plate and the dot matrix interlayer are integrally formed;
or the micropore plate and the dot matrix interlayer are integrally formed, and the back plate is glued or welded on one side of the dot matrix interlayer.
Step 2: performing post-treatment operations on the muffler device, wherein the post-treatment operations comprise one or more of removing excess powder, removing supports, performing surface polishing treatment and performing heat treatment;
and step 3: and carrying out nondestructive testing on the silencing device, wherein the nondestructive testing comprises one or more of X-ray testing and industrial CT testing.
Further, the additive process comprises a selective laser melting process or a selective laser sintering process;
the additive material comprises aluminum alloy, titanium alloy, high-strength resin or fiber reinforced composite material;
the additive process and the additive material are selected according to the working environment of the silencing device.
Compared with the prior art, the aircraft nacelle noise elimination device based on the lattice configuration and the manufacturing method thereof have the following advantages:
(1) the problem of traditional honeycomb sandwich noise-damping structure, plane direction rigidity is weak is solved, structural efficiency and intake duct bird hit performance are promoted.
(2) The assembly weight of the nacelle noise elimination device is reduced by using additive manufacturing and integrated molding, and the tolerance control of the noise elimination structure is improved.
(3) By utilizing the diversified characteristics of the lattice configuration, the design of the noise elimination device is improved, and the noise elimination wavelength of the airplane nacelle noise elimination device is adjustable.
(4) The porous characteristic of lattice structure is used, the traditional flowing back design is improved, and the structural strength loss caused by additionally arranging a liquid discharge groove is avoided.
Drawings
The accompanying drawings are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention and not to limit the invention.
In the drawings:
FIG. 1 is an overall schematic view of a lattice-configuration aircraft nacelle silencer in an embodiment of the invention;
FIG. 2 is a perspective view of a lattice configuration aircraft nacelle muffler assembly in an embodiment of the present invention;
FIG. 3 is a schematic diagram of a lattice sandwich of the lattice-configured aircraft nacelle silencer in the embodiment of the invention;
FIG. 4 is a further perspective view of the lattice-configured aircraft nacelle muffler assembly of the present invention;
FIG. 5 is a schematic liquid discharge diagram of the lattice-configuration aircraft nacelle muffler device in the embodiment of the invention;
fig. 6 is a schematic diagram of a lattice cell variant of the lattice-configured aircraft nacelle noise elimination device in the embodiment.
Wherein, 1-a micro-porous plate; 2-dot matrix interlayer; 3-a back plate; 4-a through hole; 5-liquid discharge hole; 6-lattice cell.
Detailed Description
Reference will now be made in detail to the exemplary embodiments, examples of which are illustrated in the accompanying drawings. When the following description refers to the accompanying drawings, like numbers in different drawings represent the same or similar elements unless otherwise indicated. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. Rather, they are merely examples of apparatus and methods consistent with certain aspects of the invention, as detailed in the appended claims.
The terms first, second and the like in the description and in the claims of the present invention are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the invention described herein are, for example, capable of operation in sequences other than those illustrated or otherwise described herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
A plurality, including two or more.
And/or, it should be understood that, as used herein, the term "and/or" is merely one type of association that describes an associated object, meaning that three types of relationships may exist. For example, a and/or B, may represent: a exists alone, A and B exist simultaneously, and B exists alone.
An aircraft nacelle noise abatement device based on a lattice configuration, comprising:
the micro-porous plate 1 is used for transmitting sound waves;
the dot matrix interlayer 2 is used for reflecting the sound waves input through the micropore plate 1 and dissipating sound wave energy to realize noise elimination;
the back plate 3 is used for supporting the dot matrix interlayer 2 and discharging accumulated liquid in the dot matrix interlayer 2;
the micro-porous plate 1 and the back plate 3 also have the function of enhancing the reflection of sound waves, so that the sound waves can reciprocate in the cavity formed by the micro-porous plate and the back plate.
The lattice interlayer 2 is arranged between the microporous plate 1 and the back plate 3, and the lattice interlayer 2 comprises a plurality of lattice cells 6 arranged in a lattice manner.
The lattice cell 6 includes a plurality of interconnected elements, wherein any element has at least two common nodes with other elements.
The member comprises a rod-shaped member and/or a plate-shaped member, and the cross section of the rod-shaped member comprises a circle and/or a square.
The lattice cell 6 is symmetrically configured, and the lattice cell 6 is at least symmetrical about a plane passing through the center position of the lattice cell 6 or at least symmetrical about the center position of the lattice cell 6.
The surface roughness of the lattice cell 6 is larger than 5 μm, and the lattice cell can reflect sound waves.
The junction of the lattice interlayer 2 and the microporous plate 1 is not closed, and the junction of the lattice interlayer 2 and the backboard 3 is not closed.
The micropore plate 1 comprises a pneumatic surface far away from one side of the dot matrix interlayer 2, and the pneumatic surface is a smooth surface.
At least some of the lattice cells 6 have different heights, and the shape of the back plate 3 is adapted to the height of the lattice cells 6.
A plurality of through holes 4 are formed in the microporous plate 1, and the diameter of each through hole 4 is 1-3 mm.
At least one liquid discharge hole 5 is formed in the back plate 3, and the diameter of the liquid discharge hole 5 is not less than 2 mm.
A manufacturing method of an airplane nacelle noise elimination device based on lattice configuration is used for manufacturing the airplane nacelle noise elimination device and comprises the following steps:
step 1: converting a design model of the nacelle noise eliminator into a printing model which can be identified by additive manufacturing equipment;
step 2: the microporous plate 1, the dot matrix interlayer 2 and the back plate 3 are formed through additive manufacturing. The microporous plate 1 and the dot matrix interlayer 2 are integrally formed, and the back plate 3, the microporous plate 1 and the dot matrix interlayer 2 can be integrally formed; or the microporous plate 1 and the dot matrix interlayer 2 can be glued or welded after the molding of the microporous plate 1 and the dot matrix interlayer 2 is finished.
And step 3: after fabrication, post-processing is performed, including but not limited to removing excess powder, removing supports, pneumatic surface polishing, heat treatment, etc.
And 4, step 4: and carrying out nondestructive testing on the finished silencing device after the post-treatment is finished, wherein the nondestructive testing comprises but is not limited to X-ray or industrial CT and the like.
Preferably, the additive manufacturing process selected for forming the muffler device includes, but is not limited to, a Selective Laser Melting (SLM) process, a Selective Laser Sintering (SLS) process, and the like, the material includes, but is not limited to, an aluminum alloy, a titanium alloy, a high-strength resin, a fiber reinforced composite material, and the like, and the corresponding trade-off selection is made according to the working environment (including, but not limited to, the temperature) of the muffler device.
Example 1:
as shown in fig. 1, the present embodiment proposes an aircraft engine nacelle noise damping device based on an additive manufacturing lattice configuration. The silencer can be assembled on the aerodynamic surface of an engine duct of an airplane nacelle, such as an inner wall plate of an air inlet channel of the airplane nacelle, which needs structural silencing and denoising treatment.
The lattice structure is a space truss formed by the repeated arrangement of micro-elements such as rods, plates and the like according to a certain rule. The composite material has the characteristics of small volume density, large specific surface area and high structural efficiency. The lattice structure is difficult to manufacture by the traditional process, and the complex design and forming of the lattice structure can be realized by additive manufacturing.
As shown in fig. 2, the muffler device of the present embodiment is a three-layer sandwich structure, the sandwich adopts a lattice configuration, and mainly includes a microporous plate 1, a lattice interlayer 2, and a back plate 3, and through holes 4 are arranged on the microporous plate 1.
The materials of the microporous plate 1, the lattice interlayer 2 and the back plate 3 can be metal such as aluminum alloy or titanium alloy or high-temperature metal according to the use environment and service working condition of the silencer, and are preferably fiber reinforced composite materials.
The design of the microporous plate 1 and the dot matrix interlayer 2 is designed according to the acoustic environment of the silencer and the noise spectrum in the structural mechanics working condition, and the maximum silencing efficiency is realized on the premise of meeting the strength.
The size, distribution and shape of the through holes 4 on the micro-porous plate 1 can be optimized according to the design requirements, and the shape includes but is not limited to circular, oval and polygonal.
The dimensions of the lattice cells 6 in the lattice sandwich 2, the dimensions and shape of the constituent elements (rods, plates) can be made straight and flexible, and surface detail features such as surface roughness can be adapted to different solutions according to the requirements of acoustic design and structural strength, in order to achieve better acoustic and structural efficiency.
As shown in fig. 3, the lattice cell 6 has a rough surface, preferably a surface roughness greater than 5 μm, so that the lattice cell 6 can effectively reflect sound waves, and the sound waves are reflected numerous times among the lattice cells 6, so that the sound energy is dissipated due to the friction and damping characteristics of air, thereby achieving the purpose of reducing noise.
Preferably, the side length of the lattice cell is not less than 5 mm.
The height of the lattice sandwich 2 can be optimized according to the configuration, density and acoustic performance requirements of the lattice cells 6. The microporous plate 1 keeps the requirement of the pneumatic surface, and changes the shape of the back plate 3 along with the change of the height of the dot matrix interlayer so as to realize the closed three-layer sandwich noise eliminator. Through the advantage of the material increase manufacturing design freedom degree, the interlayer height is optimized, the integral structural efficiency of the silencer is improved, and the structural weight reduction is realized.
As shown in fig. 4, in the assembled muffler device, at least one drain hole 5 is formed in the back plate 3 located at the lowest part, and as shown in fig. 5, when rainwater enters the muffler device through the through hole 4, the rainwater can be drained through the drain hole 5 at the bottom part in a concentrated manner through a gap in the dot matrix interlayer, so that the influence on use caused by accumulated water in the muffler device is avoided.
As shown in fig. 6, the lattice cells 6 in the lattice sandwich 2 can adopt different topological configurations composed of several components, which are not limited to those shown in the figure, so as to obtain better sound wave reflection and scattering absorption effects.
Example 2:
the embodiment provides a manufacturing method of an aircraft engine nacelle noise elimination device based on additive manufacturing lattice configuration, which specifically comprises the following steps:
a) according to design requirements, materials and structures of the microporous plate 1, the dot matrix interlayer 2 and the back plate 3 are obtained through acoustic design and necessary noise elimination performance simulation calculation, and a proper additive manufacturing process and proper additive manufacturing equipment are selected.
b) And (3) manufacturing the formed microporous plate 1, the dot matrix interlayer 2 and the back plate 3 in an additive mode, and then performing post-processing and corresponding machining and detection.
c) The back plate 3 can also comprehensively consider the cost and the post-treatment process, and the integral silencing device is obtained by selecting a shelf plate product to be glued and welded with the dot matrix interlayer 2.
Optionally, an aluminum alloy material is adopted, and a laser selective melting additive manufacturing (SLM) process is adopted, wherein typical manufacturing process parameters are as follows:
equipment: concept Laser 1000R, SLM (selective Laser melting) additive manufacturing process
Materials: commercial AlSi10Mg powder
Scanning strategy: chessboard (ZW)
Scanning direction random
Scanning angle of 65 °
Strip width of 0.2mm
Scanning speed 1300mm/s
The diameter of a laser spot is 0.2mm
Laser power of 400W
The thickness of the overlay is 50 μm
Optionally, the noise abatement device is made of a fiber reinforced composite material, and is manufactured by a Selective Laser Sintering (SLS) additive manufacturing process.
The above-mentioned serial numbers of the embodiments of the present invention are merely for description and do not represent the merits of the embodiments.
While the present invention has been described with reference to the embodiments shown in the drawings, the present invention is not limited to the embodiments, which are illustrative and not restrictive, and it will be apparent to those skilled in the art that various changes and modifications can be made therein without departing from the spirit and scope of the invention as defined in the appended claims.

Claims (10)

1. The utility model provides an aircraft nacelle noise eliminator based on dot matrix configuration which characterized in that includes:
the micro-porous plate is used for transmitting sound waves;
the lattice interlayer is used for reflecting the sound waves input through the micropore plate and dissipating sound wave energy to realize noise elimination;
the back plate is used for supporting the dot matrix interlayer and discharging accumulated liquid in the dot matrix interlayer;
the lattice interlayer is arranged between the microporous plate and the back plate and comprises a plurality of lattice cells arranged in a lattice manner.
2. An aircraft nacelle noise silencer assembly as claimed in claim 1, wherein the lattice cells comprise a plurality of interconnected members, any one of which has two common nodes with at least one other member.
3. An aircraft nacelle sound damping device based on a lattice configuration as claimed in claim 2, wherein the member comprises a rod-shaped member and/or a plate-shaped member, and the cross section of the rod-shaped member comprises a circle and/or a square.
4. The apparatus of claim 1, wherein the lattice cell is symmetrical and the lattice cell is at least symmetrical about a plane passing through the center of the lattice cell or at least symmetrical about the center of the lattice cell.
5. An aircraft nacelle noise silencer assembly as claimed in claim 1 wherein the lattice cells have a surface roughness greater than 5 μm and are capable of reflecting sound waves.
6. The aircraft nacelle noise eliminator based on lattice configuration of claim 1, wherein the junction of the lattice interlayer and the microporous plate is not closed, and the junction of the lattice interlayer and the back plate is not closed.
7. The aircraft nacelle silencer based on the lattice configuration of claim 1, wherein the micro-perforated plate includes a pneumatic surface on a side away from the lattice interlayer, and the pneumatic surface is a smooth surface.
8. The aircraft nacelle silencer based on the lattice configuration of claim 1, wherein the micro-porous plate is provided with a plurality of through holes, and the back plate is provided with at least one drain hole.
9. A method for manufacturing an aircraft nacelle noise silencer based on a lattice configuration, wherein the method is used for manufacturing the aircraft nacelle noise silencer according to any one of claims 1-8, and comprises the following steps:
step 1: selecting additive materials and manufacturing a formed noise eliminator through an additive process, wherein the noise eliminator comprises a microporous plate, a dot matrix interlayer and a back plate;
the back plate, the micropore plate and the dot matrix interlayer are integrally formed;
or the microporous plate and the dot matrix interlayer are integrally formed, and the back plate is glued or welded on one side of the dot matrix interlayer;
step 2: performing post-treatment operations on the muffler device, wherein the post-treatment operations comprise one or more of removing excess powder, removing supports, performing surface polishing treatment and performing heat treatment;
and step 3: and carrying out nondestructive testing on the silencing device, wherein the nondestructive testing comprises one or more of X-ray testing and industrial CT testing.
10. The manufacturing method of the aircraft nacelle noise eliminator based on lattice configuration as claimed in claim 9, wherein the additive process comprises a selective laser melting process or a selective laser sintering process;
the additive material comprises aluminum alloy, titanium alloy, high-strength resin or fiber reinforced composite material;
the additive process and the additive material are selected according to the working environment of the silencing device.
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