CN102292210A - 制造涡轮喷气发动机舱用的具有孔格芯体的结构的方法 - Google Patents
制造涡轮喷气发动机舱用的具有孔格芯体的结构的方法 Download PDFInfo
- Publication number
- CN102292210A CN102292210A CN2010800050388A CN201080005038A CN102292210A CN 102292210 A CN102292210 A CN 102292210A CN 2010800050388 A CN2010800050388 A CN 2010800050388A CN 201080005038 A CN201080005038 A CN 201080005038A CN 102292210 A CN102292210 A CN 102292210A
- Authority
- CN
- China
- Prior art keywords
- honeycomb cells
- core body
- hole lattice
- wall
- lattice core
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 31
- 238000004519 manufacturing process Methods 0.000 title abstract description 6
- 230000001413 cellular effect Effects 0.000 title abstract 4
- 230000015572 biosynthetic process Effects 0.000 claims description 4
- 238000005304 joining Methods 0.000 abstract description 2
- 241000264877 Hippospongia communis Species 0.000 description 66
- 239000010410 layer Substances 0.000 description 20
- 239000000853 adhesive Substances 0.000 description 7
- 230000001070 adhesive effect Effects 0.000 description 7
- 238000012986 modification Methods 0.000 description 6
- 230000004048 modification Effects 0.000 description 6
- 238000005452 bending Methods 0.000 description 5
- 238000010276 construction Methods 0.000 description 4
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 2
- 239000004411 aluminium Substances 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 239000012141 concentrate Substances 0.000 description 2
- 239000011229 interlayer Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 229920002994 synthetic fiber Polymers 0.000 description 2
- 239000010936 titanium Substances 0.000 description 2
- 229910052719 titanium Inorganic materials 0.000 description 2
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- YFXPPSKYMBTNAV-UHFFFAOYSA-N bensultap Chemical compound C=1C=CC=CC=1S(=O)(=O)SCC(N(C)C)CSS(=O)(=O)C1=CC=CC=C1 YFXPPSKYMBTNAV-UHFFFAOYSA-N 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 238000006116 polymerization reaction Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 239000002356 single layer Substances 0.000 description 1
Images
Classifications
-
- 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 shape; Layered products comprising a layer 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 shape; Layered products comprising a layer 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 shape; Layered products comprising a layer 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
-
- 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
-
- 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
-
- 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
-
- 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
- B32B15/20—Layered products comprising a layer of metal comprising aluminium or copper
-
- 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 shape; Layered products comprising a layer 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 shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
- B32B3/18—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by an internal layer formed of separate pieces of material which are juxtaposed side-by-side
-
- 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 shape; Layered products comprising a layer 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 shape; Layered products comprising a layer 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 shape; Layered products comprising a layer 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
-
- 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
- B32B37/12—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
-
- 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
- B32B38/00—Ancillary operations in connection with laminating processes
- B32B38/0012—Mechanical treatment, e.g. roughening, deforming, stretching
-
- 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
- B32B5/14—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 a layer differing constitutionally or physically in different parts, e.g. denser near its faces
- B32B5/142—Variation across the area of the layer
-
- 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
- B32B5/22—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 the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
- B32B5/24—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 the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/827—Sound absorbing structures or liners
-
- G—PHYSICS
- G10—MUSICAL INSTRUMENTS; ACOUSTICS
- G10K—SOUND-PRODUCING DEVICES; METHODS OR DEVICES FOR PROTECTING AGAINST, OR FOR DAMPING, NOISE OR OTHER ACOUSTIC WAVES IN GENERAL; ACOUSTICS NOT OTHERWISE PROVIDED FOR
- G10K11/00—Methods or devices for transmitting, conducting or directing sound in general; Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
- G10K11/16—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
- G10K11/172—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using resonance effects
-
- 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
- B32B38/00—Ancillary operations in connection with laminating processes
- B32B2038/0052—Other operations not otherwise provided for
-
- 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
- B32B2307/00—Properties of the layers or laminate
- B32B2307/50—Properties of the layers or laminate having particular mechanical 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
- B32B2307/00—Properties of the layers or laminate
- B32B2307/50—Properties of the layers or laminate having particular mechanical properties
- B32B2307/546—Flexural strength; Flexion stiffness
-
- 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
- B32B2307/724—Permeability to gases, adsorption
-
- 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
- B32B2307/724—Permeability to gases, adsorption
- B32B2307/7242—Non-permeable
-
- 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
- Y02T50/60—Efficient propulsion technologies, e.g. for 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T137/00—Fluid handling
- Y10T137/0536—Highspeed fluid intake means [e.g., jet engine intake]
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
- Y10T156/10—Methods of surface bonding and/or assembly therefor
- Y10T156/1002—Methods of surface bonding and/or assembly therefor with permanent bending or reshaping or surface deformation of self sustaining lamina
- Y10T156/1003—Methods of surface bonding and/or assembly therefor with permanent bending or reshaping or surface deformation of self sustaining lamina by separating laminae between spaced secured areas [e.g., honeycomb expanding]
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/19—Sheets or webs edge spliced or joined
- Y10T428/192—Sheets or webs coplanar
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
- Y10T428/24149—Honeycomb-like
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Acoustics & Sound (AREA)
- Physics & Mathematics (AREA)
- Multimedia (AREA)
- Soundproofing, Sound Blocking, And Sound Damping (AREA)
- Laminated Bodies (AREA)
- Finishing Walls (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
本发明涉及一种用于制造具有孔格芯体的结构(202)的方法,所述具有孔格芯体的结构(202)能够在涡轮喷气发动机舱的结构板中使用,所述具有孔格芯体的结构(202)包括至少一个孔格芯体块(A,B),所述孔格芯体块(A,B)具有中央部分(5a,5b)和至少两个侧部分(9a,9a’,9b,9b’),所述中央部分(5a,5b)具有芯体蜂窝隔室(7a,7b),所述至少两个侧部分(9a,9a’,9b,9b’)均包括侧蜂窝隔室(11a,11b),其中,所述方法包括以下步骤:A)在所述侧蜂窝隔室(11a,11b)上形成接合壁(36),其中所述接合壁(36)能够相互作用以形成接合区域(213);B)展开所形成的所述接合壁;以及C)端对端地接合所展开的并属于两个不同侧部分(9a,9b)的壁,使得所接合的壁(46)装配在一起,从而形成接合区域(213)。本发明还涉及一种结构板和发动机舱,所述结构板和发动机舱包括由所述方法获得的具有孔格芯体的结构。
Description
本发明涉及一种用于制造具有孔格芯体的结构的方法,其中,所述结构用在涡轮喷气发动机舱的结构板中。
本发明还涉及包括这种具有孔格芯体的结构的一种板和发动机舱。
以发动机舱围绕飞行器涡轮喷气发动机而对之进行保护,以及确保其运转。发动机舱由以非结构板和结构板组成的壁构成。所述结构板确保发动机舱具有足够刚度。为此,结构板通常具有一层或多层孔格芯体结构(通常称为“蜂窝”结构)。这些层通常在其所谓的外表面(即,在径向上离发动机轴线最远的表面)以及在其内表面(即,在径向上最接近发动机轴线的表面)处被表层覆盖。
通过下述方式来组合结构板:布置不同的表层和层,然后将这些表层和层贴在具有所需形状的模具上。在炉内对该组合件进行加工处理,从而保持所述复数个层,并使粘合剂聚合。
同时,涡轮喷气发动机产生严重的噪音污染。因此,强烈希望减少这种污染,在所使用的涡轮喷气发动机变得越来越强劲的情况下尤其希望减少这种污染。
为此,所使用的一些板是声学结构板,所述声学结构板的各层通常覆盖在具有不透气表层(称为“质密”)的外表面上、以及覆盖在具有透气有孔表层(称为“声学”)的内表面上。
结构声学板也可包括多层孔格芯体结构,在这多个层之间设置有多孔表层(称为“隔层”)。在板的组合/粘合阶段期间,此表层通过加热被粘附在孔格芯体结构之间。
这种板构成声学共振器,该声学共振器能够“截留”噪音,并且因此减少朝着发动机舱外侧的声音发散。
根据已知方式,孔格芯体结构包括至少一个孔格芯体块,该孔格芯体块包括具有芯体蜂窝隔室的中央部分和各自具有多个蜂窝接合隔室的两个侧部分。
声学结构板的声学性能(即作为根据声音的频率和声级的函数的噪音吸收率)特别依赖于孔格芯体块的接合。
从工业角度看,粘合剂的使用需要过厚部的过长的放置和切割时间。
另外,这些过厚部具有减小孔格芯体结构的有效声学表面并造成突然的阻抗中断的缺陷,阻抗中断会在涡轮喷气发动机的运转过程中减小声学板的声学性能。
从国际申请WO2008/113904得知另一种具有孔格芯体的结构,其中,位于具有孔格芯体并构成所述结构的多个块的边缘上的蜂窝边缘隔室被切开,接着被装配在一起以接合所述块。
但是,这种具有孔格芯体的结构需要通过对孔格芯体结构压紧来维护,这使得制造更加复杂。
此外,此实施例不能使其获得最佳的弯曲强度。
本发明的一个目的因此在于提供一种容易制造并具有良好弯曲强度的孔格芯体结构。
本发明的另一目的在于提供一种能够在声学板中有效地吸收来自涡轮喷气发动机的噪音的孔格芯体结构。
为此,根据第一方面,本发明涉及一种用于制造具有孔格芯体的结构的方法,所述具有孔格芯体的结构能够在涡轮喷气发动机舱的结构板中使用,所述具有孔格芯体的结构包括至少一个孔格芯体块,所述孔格芯体块具有中央部分和至少两个侧部分,所述中央部分具有芯体蜂窝隔室,所述至少两个侧部分均包括侧蜂窝隔室,其中,所述方法包括以下步骤:
A)在所述侧蜂窝隔室上形成接合壁,所述接合壁能够相互作用以形成接合区域;
B)展开所形成的所述接合壁;以及
C)端对端地接合所展开的并属于两个不同侧部分的壁,使得由此接合的壁装配在一起,从而形成接合区域。
通过将接合的壁装配在一起来接合一个或多个孔格芯体块使得可以避免对使用本发明的方法获得的结构进行压紧。实际上,通过简单地交织所述壁就可以实现接合而不用所述壁必须接触。
弯曲强度得到改善。实际上,接合的壁中的大部分不彼此接触,它们可各自自由变形,而不影响其他壁。此外,应力从一个外表层传递到另一外表层而在这些外表层中传递,以防止力集中在接合部的轴线上。
另外,使用本发明的方法获得的孔格芯体结构具有在孔格芯体块的接合部处不堵塞蜂窝隔室的优点。因此,孔格芯体结构能够非常有效地吸收涡轮喷气发动机运转而发出的噪音。
根据本发明的其他特征,本发明的方法包括以下单独考虑或根据所有可能组合的一个或多个可选特征:
-每个接合的壁的长度大于或等于所述侧蜂窝隔室和/或所述芯体蜂窝隔室的最大长度,这使得能够改善弯曲强度;
-属于孔格芯体块的侧部分端对端地接合,其中,所述孔格芯体块的侧蜂窝隔室和芯体蜂窝隔室具有不同尺寸,这使得能够适用于所需的结构的机械强度;
-在步骤A中,打通位于待接合的块的侧部分的边缘上的边缘蜂窝隔室以及与所述边缘蜂窝隔室相邻的蜂窝隔室,从而形成所述接合的壁,这使得接合的壁可以简单而有效的形成;
-所述边缘蜂窝隔室和相邻蜂窝隔室通过对蜂窝隔室的侧面和/或壁切开而打通;
-本发明的方法包括附加的步骤D,在步骤D中,在步骤C中完成的装配通过紧固构件、特别是通过夹具或钉子来保持,使得能够在不需要压紧的情况下耐久地保持孔格芯体结构。
根据第二方面,本发明涉及一种用于围绕涡轮喷气发动机的发动机舱的结构板,其特征在于,该结构板装备有至少一个使用本发明方法获得的孔格芯体结构。
优选地,根据本发明的板是声学板,其孔格芯体结构在其表面之一上覆有不透气的外表层,并且在其另一表面上覆有有孔内表层,使得能够得益于声学结构板内的所述结构的优点。
根据一个优选变型,本发明的板包括彼此叠置的至少两个孔格芯体结构,这使得能够增强根据本发明的板的机械刚度。
根据另一方面,本发明涉及一种飞行器发动机舱,其特征在于,所述飞行器发动机舱包括至少一个根据本发明的板。
优选地,所述结构板位于所述发动机舱的进气口区域中。
通过阅读下面参考附图所作的非限制性描述,将更好地理解本发明。
图1是根据本发明的单层结构板的剖视图;
图2是根据本发明的双层结构板的剖视图;
图3是本发明方法的示意图;
图4是在本发明方法结束时得到的结构的俯视图;
图5是在本发明中使用的蜂窝隔室的主视图;
图6是图3的实施例的变型。
如图1所示,根据本发明的结构板1可以是单层声学板或吸音板,该单层声学板或吸音板包括根据本发明的孔格芯体结构2,该孔格芯体结构2由一个或多个(在此实施例中为两个)彼此接合在一起的孔格芯体块A和B形成。在使用单个孔格芯体块的情况下,该单个孔格芯体块本身接合以形成孔格芯体结构,例如通过形成可以在发动机舱进气口中使用的大致圆柱形的结构来形成孔格芯体结构。
所使用的孔格芯体块A和B可具有任何几何形状,例如方形,或者任何其他适当的形状。
在本发明的结构包括限定了多个接合区域的多个孔格芯体块A、B的情况下,则可以对每个块进行选择以获得所需的机械强度以及所需的吸音性能(如果适用的话)。
孔格芯体结构2被夹在内表层3和外表层4之间,使得机械应力得以传递。另外,这些表层3和4的存在使得能够将孔格芯体结构2保持在单个元件中。
这两个孔格芯体块A、B包括具有芯体蜂窝隔室7a、7b的中央部分5以及通常多个(在此例中为两个)侧部分9a、9b,每个侧部分均包括多个侧蜂窝隔室11a、11b。块例如可包括至少四个侧部分。每个块A和B的侧蜂窝隔室11a、11b邻近接合区域13,其特征将在下面详细描述。
如图3和4所示,芯体蜂窝隔室7a、7b和侧蜂窝隔室11a、11b在此例中具有六边形截面,由此形成所谓的蜂窝结构。所述蜂窝隔室7a、7b和11a、11b还可以具有除六边形之外的任何几何形状的截面。
如图1所示,块A的芯体蜂窝隔室7a和侧蜂窝隔室11a的截面可以例如小于块B的芯体蜂窝隔室7b和侧蜂窝隔室11b的截面,从而满足制造商提出的声学和/或机械应力的要求。
优选地,侧蜂窝隔室11a、11b和芯体蜂窝隔室7a、7b由金属、合金或者合成材料制成,从而有助于芯体蜂窝隔室7a、7b和侧蜂窝隔室11a、11b的制造,并且为后者提供良好的机械强度。形成内表层3的材料可以由例如铝或钛的金属材料或者织物制成,并且形成外表层4的材料可以是多层合成材料或例如铝或钛的金属材料。
图1中所示的结构板1是声学板。在这种情况下,内表层3包括面向芯体蜂窝隔室7a、7b和侧蜂窝隔室11a、11b定位的穿孔15。以此方式,结构板1可以吸收由涡轮喷气发动机运转而产生的噪音。
在图2所示的变型中,结构板101是根据本发明的双层板,其包括分别由块A、B以及A’、B’形成的两层孔格芯体块。所述层通过已知方式组装在一起并类似于图1的情形被夹在内表层103和外表层104之间。形成结构板101的其他元件与图1所示的结构板1的其他元件相同,其相应的附图标记也是一样的。
根据一个变型,可以获得一种包括多层(大于两层)孔格芯体块的结构板,特别地所述层数大于或等于3。
在此双层板中,一方面的孔格芯体块A、B以及另一方面的A’、B’在一个或多个接合区域113内接合在一起。
与图1和2中所示的声学板1和101相类似的声学板的操作原理本身是已知的;板1、101用来安装在飞行器发动机舱的内壁中,优选安装在所述发动机舱的进气口区域中,从而内表层3、103定位成对着位于所述发动机舱中的发动机。
由发动机发出的噪音经由位于内表层3、103中的孔口15进入蜂窝隔室A、B,并且在构成声音共振器的这些芯体蜂窝隔室7a、7b和侧蜂窝隔室11a、11b内振动。以此方式,可以实现声音能量的消散以及随后的噪音等级的减小。为了改善吸音,可以将带孔的表层(也称为隔层)施加在结构板101的具有孔格芯体A、B以及A’、B’的两层块之间,从而块A’和B’的芯体蜂窝隔室7a’、7b’和侧蜂窝隔室11a’、11b’也构成声音共振器。
根据图3和4所示的实施例,根据本发明的在结构板中所使用的孔格芯体结构202通过使用本发明的方法来获得,所述方法包括由箭头30所表示的步骤A、由箭头31所表示的步骤B、以及步骤C(未示出)。
在步骤A中,在侧蜂窝隔室11a和11b上形成接合壁36,该接合壁36能够配合以形成接合区域。
为此,根据图3所示的实施例,打通位于待接合的一个或多个块A、B的侧部分9a、9b的边缘上的边缘蜂窝隔室33a、33b、以及与边缘蜂窝隔室33a、33b相邻的蜂窝隔室34a、34b,从而形成接合壁36。以此方式,有利地,在侧蜂窝隔室11a和11b上形成接合壁36,接合壁36能够配合以形成接合区域。
在此实施例中,通过利用本领域普通技术人员已知的任何方式在蜂窝隔室的侧面和/或壁上进行切割而打通边缘蜂窝隔室33a、33b和相邻蜂窝隔室34a、34b。因此,例如可以使用诸如剪刀的切割工具形成切口。
根据未示出的另一实施例,可以使用一个或多个孔格芯体块,其中,在所述块的制造过程中形成其接合壁。根据另一实施例,接合壁可以使用本领域普通技术人员已知的任何方式附接在已经形成的孔格芯体块上。
在步骤B,使用本领域普通技术人员已知的任何方式(特别是使用夹具)使由此形成的接合壁36展开。接合壁36的这种布置因此使得能够获得较大长度的接合区域。
如图4所示,在步骤C中,属于两个不同侧部分9a和9b的由此展开的壁被端对端地接合,从而使得所述接合的壁46装配在一起以形成接合区域213。
有利地,使用根据本发明的方法获得的孔格芯体结构具有在孔格芯体块的接合部处不堵塞蜂窝隔室的优点。因此,本发明的结构能够有效地吸收来自涡轮喷气发动机运转所发出的噪音。
根据一个变型,接合的壁46被展开,从而使其大致彼此平行地布置,使得由此展开的接合的壁46类似于蜂巢一样装配在一起。
根据本发明的结构201可以由自身接合的单个块形成,或者通过接合多个孔格块(特别是两个块A、B或者三个孔格块)来形成。
展开的接合的壁46可有利地具有长度e,该长度e大于或等于较大侧蜂窝隔室或芯体蜂窝隔室的最大长度l。
最大长度l被限定为蜂窝隔室的的两个不邻接边缘之间的最大距离。在规则的蜂窝隔室的情况下,此最大长度l与最大蜂窝隔室的外切圆的直径相对应。
步骤C中的装配在一起,可以在与扩张之前孔格芯体块A、B的取向相对应的“胶合(ruban)”方向51上进行(见图5)。“扩张”方向53与垂直于胶合方向51的方向相对应(见图5)。在一个变型中,还可以将“胶合”方向上的一个块与“扩张”方向上的另一块相接合。
“扩张”方向指的是下述方向:芯体蜂窝隔室7a、7a’、7b、7b’以及侧蜂窝隔室11a、11a’、11b、11b’沿该方向打通从而形成能够截留声音的开放隔室,并由此形成蜂窝结构。
因此在图3所示的情况下,沿胶合方向来装配在一起。
蜂窝隔室11a、11b的打通也可以允许沿扩张方向装配在一起,如图6所示。
根据一个实施例,在步骤C中,至少两个孔格芯体块端对端地接合,所述孔格芯体块的侧和芯体蜂窝隔室具有不同尺寸。根据一个变型,同一孔格芯体块可具有不同尺寸的侧蜂窝隔室和芯体蜂窝隔室。
因此,在不同尺寸的至少两个孔格芯体块被接合的情况下,最大长度l可相对于块A和/或块B中的最大侧蜂窝隔室和芯体蜂窝隔室而得出。
在接合包括尺寸实质相同的侧和芯体蜂窝隔室的两个块的情况下,最大长度1可以相对于任何侧蜂窝隔室或芯体蜂窝隔室来得出。
根据一个实施例,本发明的方法可包括附加的步骤D,在步骤D中,使用紧固构件来保持在步骤C中所完成的装配。
紧固构件例如是夹具或钉子,其使得能够确保良好的保持。
在向这样结合孔格芯体块之间施加常用胶以紧固外表层之前,能够通过挤压固化之前的气泡来保持所述接合。
使用本发明的方法获得的结构2、102、202具有一个或多个没有被压紧的接合区域13、113和213。因此,与现有技术中所述的实施例相比,本方法的实施更简化。
另外,接合的壁46中的大部分不接触,这使得能够确保良好的弯曲强度。实际上,接合的壁46可以均各自独立于其他的接合壁而变形。孔格芯体块的交织性允许力从一个外表层传递到另一外表层,从而避免这些力集中在接合部的轴线上。
Claims (11)
1.一种用于制造具有孔格芯体的结构(2;102;202)的方法,所述具有孔格芯体的结构(2;102;202)能够在涡轮喷气发动机舱的结构板(1;101)中使用,所述具有孔格芯体的结构(2;102;202)包括至少一个孔格芯体块(A,B),所述孔格芯体块(A,B)具有中央部分(5a,5a’,5b,5b’)和至少两个侧部分(9a,9a’,9b,9b’),所述中央部分(5a,5a’,5b,5b’)具有芯体蜂窝隔室(7a,7a’,7b,7b’),所述至少两个侧部分(9a,9a’,9b,9b’)均包括侧蜂窝隔室(11a,11a’,11b,11b’),其中,所述方法包括以下步骤:
A)在所述侧蜂窝隔室(11a,11a’,11b,11b’)上形成接合壁(36),其中所述接合壁(36)能够相互作用以形成接合区域(13;113;213);
B)展开所形成的所述接合壁(36);以及
C)端对端地接合所展开的并属于两个不同侧部分(9a,9a’,9b,9b’)的壁,使得所接合的壁(46)装配在一起,从而形成接合区域(13;113;213)。
2.如权利要求1所述的方法,其中,每个所述接合的壁(46)的长度(e)大于或等于所述侧蜂窝隔室(11a,11a’,11b,11b’)和/或所述芯体蜂窝隔室(7a,7a’,7b,7b’)的最大长度(1)。
3.如权利要求1或2所述的方法,其中,属于所述孔格芯体块(A,B)的所述侧部分(9a,9b)端对端地接合,其中,所述孔格芯体块(A,B)的所述侧蜂窝隔室(11a,11a’,11b,11b’)和所述芯体蜂窝隔室(7a,7a’,7b,7b’)具有不同尺寸。
4.如上述权利要求中任一项所述的方法,其中,在步骤A中,打通位于待接合的块的侧部分(9a,9a’,9b,9b’)的边缘上的边缘蜂窝隔室(33a,33b)以及与所述边缘蜂窝隔室(33a,33b)相邻的蜂窝隔室(34a,34b),从而形成所述接合的壁(46)。
5.如权利要求4所述的方法,其中,通过对蜂窝隔室(33a,33b;34a,34b)的侧面和/或壁进行切割而打通所述边缘蜂窝隔室(33a,33b)和相邻蜂窝隔室(34a,34b)。
6.如上述权利要求中任一项所述的方法,包括附加的步骤D,在步骤D中,通过夹具或钉子来保持在步骤C中完成的装配。
7.一种用于围绕涡轮喷气发动机的发动机舱的结构板(1;101),其特征在于,所述结构板装备有至少一个使用根据上述权利要求中任一项所述的方法获得的孔格芯体结构(2;102;202)。
8.如权利要求7所述的结构板(1;101),所述结构板(1;101)是声学板,所述声学板的孔格芯体结构(2;102;202)在其表面之一上覆有不透气的外表层(4),并且在其另一表面上覆有透气的有孔内表层(3)。
9.如权利要求7或8所述的结构板,具有彼此叠置的至少两个孔格芯体结构(102)。
10.一种飞行器发动机舱,其特征在于,包括至少一个如权利要求7-9中任一项所述的结构板(1,101)。
11.如权利要求10所述的发动机舱,其特征在于,所述结构板(1,101)位于所述发动机舱的进气口区域中。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0900500A FR2941648B1 (fr) | 2009-02-05 | 2009-02-05 | Procede de fabrication d'une structure a ame alveolaire pour une nacelle de turboreacteur |
FR09/00500 | 2009-02-05 | ||
PCT/FR2010/000019 WO2010089471A1 (fr) | 2009-02-05 | 2010-01-08 | Procédé de fabrication d'une structure a âmes alvéolaires pour une nacelle de turboréacteur |
Publications (2)
Publication Number | Publication Date |
---|---|
CN102292210A true CN102292210A (zh) | 2011-12-21 |
CN102292210B CN102292210B (zh) | 2014-04-09 |
Family
ID=40901996
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN201080005038.8A Expired - Fee Related CN102292210B (zh) | 2009-02-05 | 2010-01-08 | 制造涡轮喷气发动机舱用的具有孔格芯体的结构的方法 |
Country Status (8)
Country | Link |
---|---|
US (2) | US20110290333A1 (zh) |
EP (1) | EP2393651B1 (zh) |
CN (1) | CN102292210B (zh) |
CA (1) | CA2748386A1 (zh) |
ES (1) | ES2398075T3 (zh) |
FR (1) | FR2941648B1 (zh) |
RU (1) | RU2515750C2 (zh) |
WO (1) | WO2010089471A1 (zh) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN105452643A (zh) * | 2013-08-12 | 2016-03-30 | 赫克赛尔公司 | 包括具有内隔膜的蜂巢构件的噪声吸收结构 |
CN107639884A (zh) * | 2017-08-09 | 2018-01-30 | 中国航空工业集团公司基础技术研究院 | 一种无缝拼接蜂窝芯材的制备方法 |
CN110573328A (zh) * | 2017-05-01 | 2019-12-13 | 赫克赛尔公司 | 封堵的隔音蜂窝体 |
CN111456854A (zh) * | 2020-04-09 | 2020-07-28 | 中国航空工业集团公司西安飞机设计研究所 | 一种涡扇发动机短舱消声结构 |
CN112469569A (zh) * | 2018-07-17 | 2021-03-09 | 赛峰航空陶瓷技术公司 | 制造隔音板的方法 |
CN114348241A (zh) * | 2020-10-14 | 2022-04-15 | 保时捷股份公司 | 飞行器的涵道螺旋桨、飞行器及飞行器的构件 |
CN115352078A (zh) * | 2022-08-26 | 2022-11-18 | 上海复合材料科技有限公司 | 复合材料蜂窝及其制备方法 |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7983373B2 (en) * | 2007-02-07 | 2011-07-19 | Vintomie Networks B.V., Llc | Clock distribution for 10GBase-T analog front end |
FR2975943B1 (fr) * | 2011-06-01 | 2013-05-17 | Aircelle Sa | Procede de fabrication d'un panneau d'attenuation acoustique |
FR3081510B1 (fr) * | 2018-05-24 | 2020-05-29 | Safran Nacelles | Panneau d’attenuation acoustique pour nacelle de turboreacteur d’aeronef |
US10751971B1 (en) | 2019-04-19 | 2020-08-25 | Goodrich Corporation | Edge damage tolerant heated and unheated composite panels with rotated honeycomb edge pieces |
FR3101723B1 (fr) * | 2019-10-08 | 2022-07-22 | Safran Nacelles | Panneau d’atténuation acoustique pour onde basses fréquences |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20080047121A1 (en) * | 2006-08-18 | 2008-02-28 | Rohr, Inc. | Method of joining composite honeycomb panel sections, and composite panels resulting therefrom |
WO2008113904A2 (fr) * | 2007-02-28 | 2008-09-25 | Aircelle | Procédé de fabrication d'un panneau d'absorption acoustique notamment pour nacelle de moteur d'aéronef |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2081267C1 (ru) * | 1995-02-22 | 1997-06-10 | Анатолий Алексеевич Иванов | Способ изготовления сотовых заполнителей |
DE19922358C1 (de) * | 1999-05-14 | 2001-01-25 | Helmut Swars | Wabenkörper |
JP2002191982A (ja) * | 2000-12-27 | 2002-07-10 | Nippon Steel Corp | メタル担体及びその製造方法 |
UA26423U (en) * | 2007-03-19 | 2007-09-25 | Illich Mariupol Metallurg Works Ojsc | Method of manufacturing casting mould |
FR2926614B1 (fr) * | 2008-01-23 | 2010-02-12 | Aircelle Sa | Procede de jonction de panneaux acoustiques alveolaires |
-
2009
- 2009-02-05 FR FR0900500A patent/FR2941648B1/fr not_active Expired - Fee Related
-
2010
- 2010-01-08 RU RU2011136388/05A patent/RU2515750C2/ru not_active IP Right Cessation
- 2010-01-08 ES ES10702518T patent/ES2398075T3/es active Active
- 2010-01-08 CN CN201080005038.8A patent/CN102292210B/zh not_active Expired - Fee Related
- 2010-01-08 CA CA2748386A patent/CA2748386A1/fr not_active Abandoned
- 2010-01-08 US US13/148,057 patent/US20110290333A1/en not_active Abandoned
- 2010-01-08 EP EP10702518A patent/EP2393651B1/fr not_active Not-in-force
- 2010-01-08 WO PCT/FR2010/000019 patent/WO2010089471A1/fr active Application Filing
-
2015
- 2015-03-02 US US14/635,667 patent/US9518509B2/en not_active Expired - Fee Related
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20080047121A1 (en) * | 2006-08-18 | 2008-02-28 | Rohr, Inc. | Method of joining composite honeycomb panel sections, and composite panels resulting therefrom |
WO2008113904A2 (fr) * | 2007-02-28 | 2008-09-25 | Aircelle | Procédé de fabrication d'un panneau d'absorption acoustique notamment pour nacelle de moteur d'aéronef |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN105452643A (zh) * | 2013-08-12 | 2016-03-30 | 赫克赛尔公司 | 包括具有内隔膜的蜂巢构件的噪声吸收结构 |
CN110573328A (zh) * | 2017-05-01 | 2019-12-13 | 赫克赛尔公司 | 封堵的隔音蜂窝体 |
CN107639884A (zh) * | 2017-08-09 | 2018-01-30 | 中国航空工业集团公司基础技术研究院 | 一种无缝拼接蜂窝芯材的制备方法 |
CN107639884B (zh) * | 2017-08-09 | 2019-05-21 | 中国航空工业集团公司基础技术研究院 | 一种无缝拼接蜂窝芯材的制备方法 |
CN112469569A (zh) * | 2018-07-17 | 2021-03-09 | 赛峰航空陶瓷技术公司 | 制造隔音板的方法 |
CN112469569B (zh) * | 2018-07-17 | 2023-05-05 | 赛峰航空陶瓷技术公司 | 制造隔音板的方法 |
CN111456854A (zh) * | 2020-04-09 | 2020-07-28 | 中国航空工业集团公司西安飞机设计研究所 | 一种涡扇发动机短舱消声结构 |
CN114348241A (zh) * | 2020-10-14 | 2022-04-15 | 保时捷股份公司 | 飞行器的涵道螺旋桨、飞行器及飞行器的构件 |
CN114348241B (zh) * | 2020-10-14 | 2023-11-14 | 保时捷股份公司 | 飞行器的涵道螺旋桨、飞行器及飞行器的构件 |
CN115352078A (zh) * | 2022-08-26 | 2022-11-18 | 上海复合材料科技有限公司 | 复合材料蜂窝及其制备方法 |
Also Published As
Publication number | Publication date |
---|---|
ES2398075T3 (es) | 2013-03-13 |
FR2941648A1 (fr) | 2010-08-06 |
US20150267613A1 (en) | 2015-09-24 |
WO2010089471A1 (fr) | 2010-08-12 |
CA2748386A1 (fr) | 2010-08-12 |
US20110290333A1 (en) | 2011-12-01 |
US9518509B2 (en) | 2016-12-13 |
RU2515750C2 (ru) | 2014-05-20 |
RU2011136388A (ru) | 2013-03-10 |
FR2941648B1 (fr) | 2011-01-14 |
EP2393651A1 (fr) | 2011-12-14 |
EP2393651B1 (fr) | 2012-10-24 |
CN102292210B (zh) | 2014-04-09 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CN102292210B (zh) | 制造涡轮喷气发动机舱用的具有孔格芯体的结构的方法 | |
CN102300703B (zh) | 用于喷气发动机机舱的结构板的蜂窝芯体结构 | |
CN103561948B (zh) | 制造声衰减板的方法 | |
RU2450367C2 (ru) | Способ изготовления звукопоглощающей панели, в частности, для гондолы авиадвигателя | |
US8245815B2 (en) | Cellular-core structure for an acoustic panel | |
CN101903160B (zh) | 用于接合孔格吸音板的方法 | |
US6179086B1 (en) | Noise attenuating sandwich composite panel | |
JP5063595B2 (ja) | 周波数選択2重壁挙動を呈するサンドイッチ構造体 | |
US8770344B2 (en) | Acoustic panel | |
US20140326536A1 (en) | Structural acoustic attenuation panel | |
CA2645106A1 (en) | Sandwich element for the sound-absorbing inner cladding of means of transport, especially for the sound-absorbing inner cladding of aircraft | |
CN103827958A (zh) | 中间隔音表层及其实施 | |
AU2008100620A4 (en) | An acoustic panel and a method of manufacturing acoustic panels | |
WO2023275836A1 (en) | Method for manufacturing a core for a sound-absorbing panel with sandwich structure for noise reduction in an aircraft | |
RU2247878C2 (ru) | Способ изготовления звукопоглощающей конструкции газового тракта | |
US20200102890A1 (en) | Assembly comprising two juxtaposed acoustic panels in which the panels comprise a resistive face which extends as far as an end wall | |
RU172257U1 (ru) | Звукоизоляционная панель газотурбинного двигателя | |
US11931996B2 (en) | Method for manufacturing a soundproofing assembly having two superposed panels |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
C06 | Publication | ||
PB01 | Publication | ||
C10 | Entry into substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
C14 | Grant of patent or utility model | ||
GR01 | Patent grant | ||
CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140409 Termination date: 20160108 |
|
CF01 | Termination of patent right due to non-payment of annual fee |