CN105346152A - Engine nacelle acoustic liner - Google Patents
Engine nacelle acoustic liner Download PDFInfo
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- CN105346152A CN105346152A CN201510923492.6A CN201510923492A CN105346152A CN 105346152 A CN105346152 A CN 105346152A CN 201510923492 A CN201510923492 A CN 201510923492A CN 105346152 A CN105346152 A CN 105346152A
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- engine nacelle
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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
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
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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
- B32B15/02—Layer formed of wires, e.g. mesh
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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
- B32B15/14—Layered products comprising a layer of metal next to a fibrous or filamentary layer
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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
- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/12—Layered products comprising a layer of synthetic resin next to a fibrous or filamentary layer
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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
- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/34—Layered products comprising a layer of synthetic resin comprising polyamides
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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
- 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
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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
- 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
- B32B3/26—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 particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
- B32B3/266—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 particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by an apertured layer, the apertures going through the whole thickness of the layer, e.g. expanded metal, perforated layer, slit layer regular cells B32B3/12
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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
- 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
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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
- B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
- B32B2260/02—Composition of the impregnated, bonded or embedded layer
- B32B2260/021—Fibrous or filamentary layer
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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
- B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
- B32B2260/04—Impregnation, embedding, or binder material
- B32B2260/046—Synthetic resin
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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
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/02—Synthetic macromolecular fibres
- B32B2262/0261—Polyamide fibres
- B32B2262/0269—Aromatic polyamide fibres
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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
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/103—Metal fibres
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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
- B32B2307/00—Properties of the layers or laminate
- B32B2307/10—Properties of the layers or laminate having particular acoustical properties
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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
- B32B2307/00—Properties of the layers or laminate
- B32B2307/70—Other properties
- B32B2307/718—Weight, e.g. weight per square meter
Abstract
The invention discloses an engine nacelle acoustic liner. The engine nacelle acoustic liner comprises a backboard (1), a honeycomb core (2), a structural layer (3), a dissipation layer (4) and an acoustic resistance layer (5), wherein the backboard (1) is used for providing a hard wall environment; the honeycomb core (2) is provided with multiple holes with the same size, and one end of an upper hole in the honeycomb core (2) is fixedly connected with one side of the backboard (1); the surface of the structural layer (3) is perforated, and one side face of the structural layer (3) is fixedly connected with the other end of the upper hole in the honeycomb core (2); the surface of the dissipation layer (4) is perforated, and one side face of the dissipation layer (4) is fixedly connected with the other side face of the structural layer (3); the surface of the acoustic resistance layer (5) is perforated, and one side face of the acoustic resistance layer (5) is fixedly connected with the other side face of the dissipation layer (4). The engine nacelle acoustic liner has the beneficial effects that a higher silencing effect under a high sound pressure level can be achieved, the sound absorption frequency range is wider, and the requirements of flow resistance and structural strength can be met.
Description
Technical field
The present invention relates to duct attenuation technical field, be specifically related to a kind of engine nacelle sound lining.
Background technology
At present, known sound serves as a contrast mainly single-degree-of-freedom sound lining, double freedom sound and serves as a contrast even Three Degree Of Freedom sound lining.Its basic structure is made up of the perforated plate of outermost aluminum backboard, middle aluminum honeycomb core, inner side, and double freedom sound lining and Three Degree Of Freedom sound lining continue superposition 1 to 2 layer of honeycomb core and perforated plate on this basis to the inside.Aperture and the inner cavity on perforated plate surface constitute Helmholtz resonator, and numerous resonator achieves the effect reducing noise.But for the sound lining structure of this three quasi-tradition, require the restriction of harmony lining structure requirement of strength by air-flow lower resistance, perforated plate punching rate is very low, cause sound to serve as a contrast noise reduction under noise high sound pressure level low, sound lining effect noisy frequency range is very narrow.Although double freedom sound lining and Three Degree Of Freedom sound lining increase sound absorption frequency range, increase sound lining weight simultaneously.
Summary of the invention
The object of this invention is to provide a kind of engine nacelle sound lining, to solve or at least to alleviate the problem at least one place existing in background technology.
Technical scheme of the present invention is: provide a kind of engine nacelle sound to serve as a contrast, comprise backboard, described backboard is used for providing sclerine environment; Honeycomb core, described honeycomb core is provided with multiple measure-alike hole, and on honeycomb core, the one end in hole is fixedly connected with the side of described backboard; Structure sheaf, the perforate surface of described structure sheaf, a side of structure sheaf is fixedly connected with the other end of honeycomb core upper plenum; Dissipation layer, the perforate surface of described dissipation layer, a side of dissipation layer is fixedly connected with the another side of the strong layer of described structure; Acoustic resistance layer, described acoustic resistance layer perforate surface, a side of acoustic resistance layer is fixedly connected with the another side of described dissipation layer.
Preferably, the perforate surface of described acoustic resistance layer is rectangular opening, the length direction of described rectangular opening is along airflow direction, and described rectangular opening width dimensions is less than or equal to the described honeycomb core single hole length of side, and described rectangular opening length dimension is 2 ~ 4 times of the single hole length of side in described honeycomb core.
Preferably, the thickness of described acoustic resistance layer is less than or equal to 0.5 millimeter.
Preferably, described acoustic resistance layer is made up of unidirectional fibre, and described fiber thermoplastic resin carries out pre-preg, and the direction of fiber is identical with airflow direction.
Preferably, described dissipation layer is set to stainless steel metal silk screen, and the mesh wire diameter of described woven wire is less than or equal to 1 millimeter, and described woven wire perforation is more than 100 orders.
Preferably, described structure sheaf is made up of unidirectional fibre, and described fiber thermoplastic resin carries out pre-preg, the direction of fiber is identical with airflow direction, structure sheaf perforate surface, hole shape is rectangular, and the length direction in hole is identical with airflow direction, and the thickness of structure sheaf is greater than the thickness of described acoustic resistance layer and is less than or equal to 1 millimeter.
Preferably, the surface rectangle hole of described structure sheaf and the surface rectangle hole of described acoustic resistance layer are to it.
Preferably, described structure sheaf is made up of the fabric be interweaved, the fibre warps be interweaved or weft direction identical with airflow direction.
Preferably, described backboard is made up of the fiber prepreg stain resin being interweaved.
Preferably, described honeycomb core is manufactured by NOMEX.
Beneficial effect of the present invention: engine nacelle sound lining of the present invention is sandwich construction, comprise backboard, honeycomb core, structure sheaf, dissipation layer and acoustic resistance layer, and be interconnected successively between each layer, described honeycomb core is provided with multiple measure-alike hole, structure sheaf, dissipation layer and acoustic resistance layer surface are provided with perforation, described sandwich construction sound lining drastically increases punching rate, and the raising of punching rate contributes to the increase of described sound lining acoustics nonlinear improvement and sound absorption frequency range, noise elimination effect higher under can realizing high sound pressure level, sound absorption frequency range is wider, and the requirement of flow resistance and structural strength can be reached.
The thickness of acoustic resistance layer is less than or equal to 0.5 millimeter, ensure that its low flow resistance performance when perforate.
Dissipation layer is set to stainless steel metal silk screen, and the effect of woven wire is to ensure that the good low flow resistance performance that described sandwich construction sound serves as a contrast while the described acoustic resistance layer large perforation rate of guarantee, and described wire mesh structure has good dissipative performance.
The surface rectangle hole of structure sheaf and the surface rectangle hole of described acoustic resistance layer, to it, ensure that described engine nacelle sound serves as a contrast maximum punching rate.
Acoustic resistance layer, structure sheaf, backboard and honeycomb core adopt composite to make, and alleviate the weight of sound lining.
Accompanying drawing explanation
Fig. 1 is an example structure schematic diagram of engine nacelle sound of the present invention lining.
Wherein: 1-backboard, 2-honeycomb core, 3-structure sheaf, 4-dissipation layer, 5-acoustic resistance layer.
Detailed description of the invention
For making object of the invention process, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the present invention's part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.Below in conjunction with accompanying drawing, embodiments of the invention are described in detail.
In describing the invention; it will be appreciated that; term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " etc. instruction orientation or position relationship be based on orientation shown in the drawings or position relationship; be only the present invention for convenience of description and simplified characterization; instead of instruction or imply indication device or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limiting the scope of the invention.
In order to overcome the deficiency that existing sound lining soundproof effect under noise high sound pressure level is low and sound absorption frequency range is narrow, the invention provides a kind of engine nacelle sound lining, this sound lining not only achieves lower non-linear and wider sound absorption frequency range, and can ensure low flow resistance and the structural strength performance in inner-walls of duct face.
As shown in Figure 1, described engine nacelle sound lining comprises backboard 1, and described backboard 1 is for providing sclerine environment; Honeycomb core 2, described honeycomb core 2 is provided with multiple measure-alike hole, and on honeycomb core 2, the one end in hole is fixedly connected with the side of described backboard 1; Structure sheaf 3, the perforate surface of described structure sheaf 3, a side of structure sheaf 3 is fixedly connected with the other end in hole on honeycomb core 2; Dissipation layer 4, the perforate surface of described dissipation layer 4, a side of dissipation layer 4 is fixedly connected with the another side of the strong layer 3 of described structure; Acoustic resistance layer 5, described acoustic resistance layer 5 perforate surface, a side of acoustic resistance layer 5 is fixedly connected with the another side of described dissipation layer 4.Described acoustic resistance layer 5 flushes with engine duct inner surface, thus described engine nacelle sound lining is contacted with engine noise.
Engine nacelle sound lining of the present invention is sandwich construction, comprise backboard 1, honeycomb core 2, structure sheaf 3, dissipation layer 4 and acoustic resistance layer 5, and be interconnected successively between each layer, described honeycomb core 2 is provided with multiple measure-alike hole, structure sheaf 3, dissipation layer 4 and acoustic resistance layer 5 surface are provided with perforation, described sandwich construction sound lining drastically increases punching rate, and the raising of punching rate contributes to the increase of described sound lining acoustics nonlinear improvement and sound absorption frequency range, noise elimination effect higher under can realizing high sound pressure level, sound absorption frequency range is wider, and the requirement of flow resistance and structural strength can be reached.
In the present embodiment, connection and the dissipation layer 4 of the connection of the connection of described backboard 1 and honeycomb core 2, honeycomb core 2 and structure sheaf 3, structure sheaf 3 and dissipation layer 4 are bonding with the connection of acoustic resistance layer 5.
In the present embodiment, the perforate surface of described acoustic resistance layer 5 is rectangular opening, the length direction of described rectangular opening is along airflow direction, and described rectangular opening width dimensions is less than or equal to the described honeycomb core single hole length of side, and described rectangular opening length dimension is 2 ~ 4 times of the single hole length of side in described honeycomb core.
Be understandable that, the minor face on the width of described rectangular opening can also do semicircle process, connects two long limits by semi arch.Described rectangular opening length dimension can also set according to actual conditions, and such as, in an alternative embodiment, described rectangular opening length dimension is 3 times of the single hole length of side in described honeycomb core 2.Be understandable that, described rectangular opening length dimension also can be set to the single hole length of side in described honeycomb core 2 non-integral multiple, and multiple is arranged between 2 ~ 4 times.
Be understandable that, the thickness of described acoustic resistance layer 5 is less than or equal to 0.5 millimeter.Its low flow resistance performance is ensure that when perforate.
In the present embodiment, described acoustic resistance layer 5 is made up of unidirectional fibre, and described fiber thermoplastic resin carries out pre-preg, and the direction of fiber is identical with airflow direction.
Be understandable that, described acoustic resistance layer 5 can also be noted by multi-layer fiber the composite formed after resin and form.
Be understandable that, the kinds of fibers that acoustic resistance layer 5 is applied comprises carbon fiber, glass fibre.Pre-impregnated resin is thermoplastic resin, can ensure between acoustic resistance layer 5 with dissipation layer 4 good bonding like this.The rectangular opening on acoustic resistance layer 5 surface is formed through pressure cutting after fiber solidifying.Acoustic resistance layer 5 covers the one side of whole sound lining and air flow contacts.
In the present embodiment, described dissipation layer 4 is set to stainless steel metal silk screen, and the mesh wire diameter of described woven wire is less than or equal to 1 millimeter, and described woven wire perforation, more than 100 orders, ensures while ensureing high punching rate thus that single actual space is very little.The effect of described woven wire is to ensure that the good low flow resistance performance that described sound serves as a contrast while the described acoustic resistance layer large perforation rate of guarantee.And described wire mesh structure has good dissipative performance.
In the present embodiment, described structure sheaf 3 is made up of unidirectional fibre, and described fiber thermoplastic resin carries out pre-preg, the direction of fiber is identical with airflow direction, structure sheaf 3 perforate surface, hole shape is rectangular, and the length direction in hole is identical with airflow direction, and the thickness of structure sheaf 3 is greater than the thickness of described acoustic resistance layer 5 and is less than or equal to 1 millimeter.
In the present embodiment, the surface rectangle hole of described structure sheaf 3 and the surface rectangle hole of described acoustic resistance layer 5 are to it.This ensure that described a kind of engine nacelle sound serves as a contrast maximum punching rate.The effect of structure sheaf 5 is that transmission sound serves as a contrast part peripheral force, axial force and the radial load of bearing in pipeline or nacelle.Ensure that described engine nacelle sound lining has good structural behaviour while large perforation rate.
In the present embodiment, described structure sheaf 3 is made up of the fabric be interweaved, the fibre warps be interweaved or weft direction identical with airflow direction.In the present embodiment, the warp-wise of fiber is perpendicular to airflow direction, and the broadwise of described fiber is along airflow direction.
Structure sheaf 3 does not act on by the pressure of air, suction, can the thermosetting resin of application of epoxy, mutually bonding to ensure other parts that structure sheaf 3 and sound serve as a contrast.Structure sheaf 3 also can use thermoplastic resin.
In the present embodiment, described backboard 1 is made up of the fiber prepreg stain resin being interweaved.Be understandable that, the material of backboard 1 can also be the composite formed by multi-layer fiber note resin.
In the present embodiment, described honeycomb core 2 is manufactured by NOMEX.
In the present embodiment, acoustic resistance layer 5, structure sheaf 3, backboard 1 and honeycomb core 2 adopt composite to make, and alleviate the weight of sound lining.The high temperature polymerization effect of the bonding pre-impregnated resin that can be mixed by one or more between backboard 1, honeycomb core 2, structure sheaf 3, dissipation layer 4 harmony resistance layer 5 is realized.
The process of the engine nacelle sound lining of the present embodiment is: first, form the composite layer in Single Fiber direction at the mold outer surface identical with engine nacelle inner surface; Secondly, mould is opened rectangular opening vertically; Again, acoustic resistance layer 5 is laid dissipation layer 4, dissipation layer 4 is laid structure sheaf 3, lay honeycomb core 2 and backboard 1 successively; Finally, assembly is put into high temperature stove to be polymerized.
Be understandable which floor honeycomb core 2 can be divided into, so just form multiple degrees of freedom sound lining.
Finally it is to be noted: above embodiment only in order to technical scheme of the present invention to be described, is not intended to limit.Although with reference to previous embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (10)
1. an engine nacelle sound lining, is characterized in that: comprise,
Backboard (1), described backboard (1) is for providing sclerine environment;
Honeycomb core (2), described honeycomb core (2) is provided with multiple measure-alike hole, and the one end in the upper hole of honeycomb core (2) is fixedly connected with the side of described backboard (1);
Structure sheaf (3), the perforate surface of described structure sheaf (3), a side of structure sheaf (3) is fixedly connected with the other end in the upper hole of honeycomb core (2);
Dissipation layer (4), the perforate surface of described dissipation layer (4), a side of dissipation layer (4) is fixedly connected with the another side of the strong layer of described structure (3);
Acoustic resistance layer (5), described acoustic resistance layer (5) perforate surface, a side of acoustic resistance layer (5) is fixedly connected with the another side of described dissipation layer (4).
2. engine nacelle sound lining as claimed in claim 1, it is characterized in that: the perforate surface of described acoustic resistance layer (5) is rectangular opening, the length direction of described rectangular opening is along airflow direction, described rectangular opening width dimensions is less than or equal to the described honeycomb core single hole length of side, and described rectangular opening length dimension is 2 ~ 4 times of the single hole length of side in described honeycomb core.
3. engine nacelle sound lining as claimed in claim 2, is characterized in that: the thickness of described acoustic resistance layer (5) is less than or equal to 0.5 millimeter.
4. engine nacelle sound lining as claimed in claim 2, is characterized in that: described acoustic resistance layer (5) is made up of unidirectional fibre, and described fiber thermoplastic resin carries out pre-preg, and the direction of fiber is identical with airflow direction.
5. engine nacelle sound lining as claimed in claim 1, it is characterized in that: described dissipation layer (4) is set to stainless steel metal silk screen, the mesh wire diameter of described woven wire is less than or equal to 1 millimeter, and described woven wire perforation is more than 100 orders.
6. engine nacelle sound lining as claimed in claim 1, it is characterized in that: described structure sheaf (3) is made up of unidirectional fibre, and described fiber thermoplastic resin carries out pre-preg, the direction of fiber is identical with airflow direction, structure sheaf (3) perforate surface, hole shape is rectangular, and the length direction in hole is identical with airflow direction, and the thickness of structure sheaf (3) is greater than the thickness of described acoustic resistance layer (5) and is less than or equal to 1 millimeter.
7. engine nacelle sound lining as claimed in claim 1, is characterized in that: the surface rectangle hole of described structure sheaf (3) and the surface rectangle hole of described acoustic resistance layer (5) are to it.
8. engine nacelle sound lining as claimed in claim 1, is characterized in that: described structure sheaf (3) is made up of the fabric be interweaved, the fibre warps be interweaved or weft direction identical with airflow direction.
9. engine nacelle sound lining as claimed in claim 1, is characterized in that: described backboard (1) is made up of the fiber prepreg stain resin being interweaved.
10. engine nacelle sound lining as claimed in claim 1, is characterized in that: described honeycomb core (2) is manufactured by NOMEX.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510923492.6A CN105346152A (en) | 2015-12-11 | 2015-12-11 | Engine nacelle acoustic liner |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510923492.6A CN105346152A (en) | 2015-12-11 | 2015-12-11 | Engine nacelle acoustic liner |
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| CN105346152A true CN105346152A (en) | 2016-02-24 |
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| CN201510923492.6A Pending CN105346152A (en) | 2015-12-11 | 2015-12-11 | Engine nacelle acoustic liner |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110126288A (en) * | 2018-02-09 | 2019-08-16 | 波音公司 | Thermoplastic adhesive for the linear face thin plate of Acoustic treatment is handled |
| CN110487533A (en) * | 2019-09-17 | 2019-11-22 | 中国航发沈阳发动机研究所 | A kind of sound lining testpieces, assemble method and its test structure |
| IT201900004761A1 (en) | 2019-03-29 | 2020-09-29 | Leonardo Spa | Manufacturing process of a sound-absorbing panel with a sandwich structure to reduce the sound impact of an aircraft engine |
| CN111816149A (en) * | 2019-04-11 | 2020-10-23 | 中国科学院声学研究所 | Low-frequency honeycomb sound absorption device |
| CN112339360A (en) * | 2020-10-29 | 2021-02-09 | 株洲时代新材料科技股份有限公司 | Light noise-eliminating sound-insulating material for nacelle and preparation process thereof |
| CN113898476A (en) * | 2020-06-22 | 2022-01-07 | 中国航发商用航空发动机有限责任公司 | Acoustic liner, dynamic propulsion system and inlet plate set |
| CN113895098A (en) * | 2020-06-22 | 2022-01-07 | 中国航发商用航空发动机有限责任公司 | Acoustic liner, method of manufacture, power propulsion system, and honeycomb core |
| CN114321024A (en) * | 2021-12-31 | 2022-04-12 | 广东美的白色家电技术创新中心有限公司 | Control method and control device of noise reduction device, storage medium and noise reduction device |
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