CN112469569A - 制造隔音板的方法 - Google Patents
制造隔音板的方法 Download PDFInfo
- Publication number
- CN112469569A CN112469569A CN201980046980.XA CN201980046980A CN112469569A CN 112469569 A CN112469569 A CN 112469569A CN 201980046980 A CN201980046980 A CN 201980046980A CN 112469569 A CN112469569 A CN 112469569A
- Authority
- CN
- China
- Prior art keywords
- wall
- strip
- strips
- honeycomb core
- slot
- 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 27
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 22
- 239000000835 fiber Substances 0.000 claims abstract description 27
- 239000002131 composite material Substances 0.000 claims abstract description 24
- 239000011159 matrix material Substances 0.000 claims abstract description 9
- 239000000853 adhesive Substances 0.000 claims description 21
- 230000001070 adhesive effect Effects 0.000 claims description 21
- 239000000919 ceramic Substances 0.000 claims description 19
- 238000005245 sintering Methods 0.000 claims description 12
- 238000005520 cutting process Methods 0.000 claims description 11
- 239000003292 glue Substances 0.000 claims description 7
- 238000003856 thermoforming Methods 0.000 claims description 5
- 238000004049 embossing Methods 0.000 claims description 3
- 239000011230 binding agent Substances 0.000 description 30
- 239000002002 slurry Substances 0.000 description 16
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 12
- 239000000463 material Substances 0.000 description 12
- 238000011144 upstream manufacturing Methods 0.000 description 12
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 10
- 239000000843 powder Substances 0.000 description 10
- 238000002347 injection Methods 0.000 description 9
- 239000007924 injection Substances 0.000 description 9
- 229920001296 polysiloxane Polymers 0.000 description 8
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 7
- 229910045601 alloy Inorganic materials 0.000 description 7
- 239000000956 alloy Substances 0.000 description 7
- 239000010936 titanium Substances 0.000 description 7
- 229910052719 titanium Inorganic materials 0.000 description 7
- 229910000323 aluminium silicate Inorganic materials 0.000 description 6
- HNPSIPDUKPIQMN-UHFFFAOYSA-N dioxosilane;oxo(oxoalumanyloxy)alumane Chemical compound O=[Si]=O.O=[Al]O[Al]=O HNPSIPDUKPIQMN-UHFFFAOYSA-N 0.000 description 6
- 238000005192 partition Methods 0.000 description 6
- -1 polysiloxane Polymers 0.000 description 6
- 239000011153 ceramic matrix composite Substances 0.000 description 5
- 229910052759 nickel Inorganic materials 0.000 description 5
- 238000001802 infusion Methods 0.000 description 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 4
- 239000007769 metal material Substances 0.000 description 3
- 239000002245 particle Substances 0.000 description 3
- 238000004026 adhesive bonding Methods 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 239000004744 fabric Substances 0.000 description 2
- 239000000945 filler Substances 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000003647 oxidation Effects 0.000 description 2
- 238000007254 oxidation reaction Methods 0.000 description 2
- 239000011224 oxide ceramic Substances 0.000 description 2
- 229910052574 oxide ceramic Inorganic materials 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 239000011347 resin Substances 0.000 description 2
- 229920005989 resin Polymers 0.000 description 2
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 2
- 229910010271 silicon carbide Inorganic materials 0.000 description 2
- 239000002344 surface layer Substances 0.000 description 2
- 229920001169 thermoplastic Polymers 0.000 description 2
- 229920001187 thermosetting polymer Polymers 0.000 description 2
- 239000004416 thermosoftening plastic Substances 0.000 description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- DHAHRLDIUIPTCJ-UHFFFAOYSA-K aluminium metaphosphate Chemical compound [Al+3].[O-]P(=O)=O.[O-]P(=O)=O.[O-]P(=O)=O DHAHRLDIUIPTCJ-UHFFFAOYSA-K 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000012700 ceramic precursor Substances 0.000 description 1
- 238000002144 chemical decomposition reaction Methods 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 229910001026 inconel Inorganic materials 0.000 description 1
- 229910052500 inorganic mineral Inorganic materials 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000005304 joining Methods 0.000 description 1
- 239000010410 layer Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 239000011707 mineral Substances 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 229920000642 polymer Polymers 0.000 description 1
- 238000006116 polymerization reaction Methods 0.000 description 1
- 230000000379 polymerizing effect Effects 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 230000000135 prohibitive effect Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 239000012783 reinforcing fiber Substances 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- RMAQACBXLXPBSY-UHFFFAOYSA-N silicic acid Chemical compound O[Si](O)(O)O RMAQACBXLXPBSY-UHFFFAOYSA-N 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 239000004753 textile Substances 0.000 description 1
- 239000012815 thermoplastic material Substances 0.000 description 1
- 238000001721 transfer moulding Methods 0.000 description 1
- 238000007666 vacuum forming Methods 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
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/14—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers
- B32B37/146—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers whereby one or more of the layers is 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
- B32B18/00—Layered products essentially comprising ceramics, e.g. refractory products
-
- 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
-
- 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
-
- 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
- B32B5/022—Non-woven fabric
-
- 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; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
- B64D33/06—Silencing exhaust or propulsion jets
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/01—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxide ceramics
- C04B35/10—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxide ceramics based on aluminium oxide
- C04B35/111—Fine ceramics
- C04B35/117—Composites
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/01—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxide ceramics
- C04B35/16—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxide ceramics based on silicates other than clay
- C04B35/18—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxide ceramics based on silicates other than clay rich in aluminium oxide
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/71—Ceramic products containing macroscopic reinforcing agents
- C04B35/78—Ceramic products containing macroscopic reinforcing agents containing non-metallic materials
- C04B35/80—Fibres, filaments, whiskers, platelets, or the like
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B37/00—Joining burned ceramic articles with other burned ceramic articles or other articles by heating
- C04B37/003—Joining burned ceramic articles with other burned ceramic articles or other articles by heating by means of an interlayer consisting of a combination of materials selected from glass, or ceramic material with metals, metal oxides or metal salts
- C04B37/005—Joining burned ceramic articles with other burned ceramic articles or other articles by heating by means of an interlayer consisting of a combination of materials selected from glass, or ceramic material with metals, metal oxides or metal salts consisting of glass or ceramic material
-
- 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
- F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
-
- 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
- G10K11/162—Selection of materials
- G10K11/168—Plural layers of different materials, e.g. sandwiches
-
- 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
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C45/00—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor
- B29C45/16—Making multilayered or multicoloured articles
- B29C2045/1692—Making multilayered or multicoloured articles one layer comprising fibres
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C51/00—Shaping by thermoforming, i.e. shaping sheets or sheet like preforms after heating, e.g. shaping sheets in matched moulds or by deep-drawing; Apparatus therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
- B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
- B29C66/725—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined being hollow-walled or honeycombs
- B29C66/7252—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined being hollow-walled or honeycombs hollow-walled
- B29C66/72525—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined being hollow-walled or honeycombs hollow-walled comprising honeycomb cores
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
- B29C66/74—Joining plastics material to non-plastics material
- B29C66/746—Joining plastics material to non-plastics material to inorganic materials not provided for in groups B29C66/742 - B29C66/744
- B29C66/7461—Ceramics
-
- 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
- B32B2307/514—Oriented
- B32B2307/518—Oriented bi-axially
-
- 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
- B32B2315/00—Other materials containing non-metallic inorganic compounds not provided for in groups B32B2311/00 - B32B2313/04
- B32B2315/02—Ceramics
-
- 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
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/48—Organic compounds becoming part of a ceramic after heat treatment, e.g. carbonising phenol resins
- C04B2235/483—Si-containing organic compounds, e.g. silicone resins, (poly)silanes, (poly)siloxanes or (poly)silazanes
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5264—Fibers characterised by the diameter of the fibers
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/02—Aspects relating to interlayers, e.g. used to join ceramic articles with other articles by heating
- C04B2237/04—Ceramic interlayers
- C04B2237/06—Oxidic interlayers
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/02—Aspects relating to interlayers, e.g. used to join ceramic articles with other articles by heating
- C04B2237/04—Ceramic interlayers
- C04B2237/06—Oxidic interlayers
- C04B2237/062—Oxidic interlayers based on silica or silicates
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/02—Aspects relating to interlayers, e.g. used to join ceramic articles with other articles by heating
- C04B2237/04—Ceramic interlayers
- C04B2237/06—Oxidic interlayers
- C04B2237/064—Oxidic interlayers based on alumina or aluminates
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
- C04B2237/32—Ceramic
- C04B2237/38—Fiber or whisker reinforced
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/50—Processing aspects relating to ceramic laminates or to the joining of ceramic articles with other articles by heating
- C04B2237/76—Forming laminates or joined articles comprising at least one member in the form other than a sheet or disc, e.g. two tubes or a tube and a sheet or disc
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/01—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxide ceramics
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/28—Three-dimensional patterned
- F05D2250/283—Three-dimensional patterned honeycomb
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Ceramic Engineering (AREA)
- Materials Engineering (AREA)
- Structural Engineering (AREA)
- Organic Chemistry (AREA)
- Manufacturing & Machinery (AREA)
- Acoustics & Sound (AREA)
- Multimedia (AREA)
- Physics & Mathematics (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Composite Materials (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Textile Engineering (AREA)
- Laminated Bodies (AREA)
- Soundproofing, Sound Blocking, And Sound Damping (AREA)
Abstract
本发明涉及制造复合面板的方法,特别是在涡轮机中的复合面板,其特征在于,所述方法包括以下步骤:a)由复合材料制造第一壁、第二壁、第三壁和第四壁,所述复合材料包括氧化物基质和长氧化物纤维,b)由第一和第二壁制造包括多个单元格(18)的蜂窝芯(12),每个单元格(18)包括第一端和相对的第二端,c)分别用第三壁和第四壁(26)覆盖所述蜂窝芯(12)的单元格(18)的第一和第二端,以封闭单元格(18)的端部。
Description
技术领域
本发明涉及面板领域,特别是旨在用于装备涡轮机且更确切地说是飞机涡轮喷气发动机的热气喷射区的那些面板。更明确地说,本发明涉及一种制造蜂窝芯的方法。
背景技术
通常,涡轮机具有用于经喷射热气的流动的空气动力导引表面,其可经受高达700℃且在一些情况下高达800℃的高温。
为了减少在操作期间由涡轮喷气发动机发射的噪声,已知的是制造具有隔音板10的空气动力导引表面,所述隔音板包括由插入在两个覆盖壁之间的蜂窝芯12组成的夹层式结构,所述覆盖壁也被称为表层14。这些面板10的表层14由金属材料或陶瓷基复合材料制成。蜂窝芯12由呈现出压实粉末或具有短纤维的陶瓷基复合材料的形式的金属单片材料制成。因此,在金属(钛、镍、铬镍铁合金等)或单片芯的情况下,芯12不含增强纤维。在芯由陶瓷基复合材料制成的情况下,复合材料配备有短纤维。
面板通常由钛合金制成。如果面板包含隔音处理,那么其通常由亥姆霍兹(Helmholtz)谐振器式结构执行,即基于形成单元格18的横向分区16的钛条带在蜂窝芯12的两个表层14之间引入。蜂窝芯12通常焊接到两个表层14。蜂窝芯12的结构特征(单元格大小18、壁厚度16、壁高度16)被限定以优化声音减弱。
潜在增加用于未来飞机发动机的气体喷射温度可能会限制例如钛等材料的使用。因此,必须识别耐较高温度的材料。现有技术方案是转变到基于镍的合金,所述合金具有比钛高得多的温度限度。
然而,与基于钛的合金面板相比,基于镍的合金的使用意味着质量显著增加。另外,制造基于镍的合金面板比基于钛的合金面板更复杂。
蜂窝芯12具有形成大量单元格18的横向分区16,明确地说,其可具有矩形横截面或具有带有六边形横截面的蜂窝形状。
最后,包括由具有短纤维的复合材料制成的蜂窝芯12的面板具有低机械阻力。
另外,制成面板10的金属材料具有能够在操作期间达到的温度限度并且具有显著厚度和质量。氧化会引起金属材料的化学降解。
然而,不会考虑使用此类材料来制造隔音板10,因为制造隔音板10的成本会过高。
本发明旨在制造由以较低成本克服上述问题的材料制成的隔音板10。
发明内容
本发明首先涉及制造复合面板的方法,特别是在涡轮机中的复合面板,所述方法的特征在于,其包括以下步骤:
a)由复合材料制造第一壁、第二壁、第三壁和第四壁,所述复合材料包括氧化物基质和长氧化物纤维,
b)由第一和第二壁形成具有多个单元格的蜂窝芯,每个单元格具有第一端和相对的第二端,
c)分别用第三壁和第四壁覆盖所述蜂窝芯的单元格的第一和第二端,以封闭单元格的端部。
完全由具有氧化物基质和长氧化物纤维的复合材料制成的面板在高于700℃的温度下具有比由基于钛的合金制成的相同面板更好的机械阻力,并且质量低于由基于镍的合金制成的相同面板。类似地,具有包括短纤维的蜂窝芯的面板具有比具有包括长纤维的蜂窝芯的面板更低的机械强度。
与短纤维不同,长纤维能够使用单向或双轴纤维形成纺织预成型件。与长纤维相比,短纤维不允许制造此类纺织预成型件。在本发明的情况下,所谓的长纤维为若干千米长。
面板由第三和第四壁覆盖的蜂窝芯组成,第三和第四壁也被称为下部和上部表层,以密封单元格的开口。当根据本发明的隔音板集成到涡轮机的排气壳体中时,所存在的水蒸气不影响面板的结构,因为氧化物基质和氧化物纤维不容易发生氧化。这增加了具有氧化物基质和长氧化物纤维的复合面板的使用寿命。
所涉及的面板可以是设计成减少噪声污染的隔音板。在此情况下,第三壁和第四壁中的至少一个具有穿孔,穿孔中的每一个通向单元格。每一穿孔通向单元格并且因此形成亥姆霍兹谐振器。
在本发明的第一实施例中,在步骤b)中从以下步骤获得蜂窝芯:
i.形成第一壁以获得波纹壁,所述波纹壁具有由顶点连接部分互连的交替的第一顶点部分和第二顶点部分,
ii.在第一顶点和第一壁的顶点连接部分中切割出狭槽,
iii.在第二壁中制造切口以获得多个条带,
iv.将条带插入到第一壁的狭槽中以对多个单元格定界。
在此第一实施例中,形成第一壁以获得波纹金属板料,所述波纹金属板料的一连串顶点部分和顶点连接部分在轴向方向上延伸。在形成第一壁的步骤期间,该第一壁的成形是通过热成型或借助于压印成形而获得的。有利的是,第二顶点部分不包含狭槽,其允许条带邻接第二部分。
狭槽在波纹薄片中沿大体上轴向方向被切割以穿过第一顶点部分、第一顶点部分的邻近顶点连接部分和波纹薄片的下游端的部分,以及将其连接到波纹薄片的第二顶点部分的顶点连接部分。第一壁的此形成使得有可能简单地布置条带,从而在狭槽中形成分区,以与第二顶点部分邻接。波纹薄片的狭槽中条带的布置形成一起限定蜂窝芯的单元格。有利的是,此第一实施例的每个单元格一方面由顶点部分中的一者封闭,并且另一方面由带和顶点连接部分封闭,使得仅与顶点部分相对的单元格的端需要用表层封闭。
有利的是,复合隔音板的第一实施例可包含在于以下的步骤:将粘合剂施加到第一壁和条带的接合区域处,所述粘合剂优选为陶瓷胶。
优选的是在波纹薄片和分区的接合处施加粘合剂,例如陶瓷胶,所述粘合剂由插入在所述波纹薄片的狭槽中的条带形成,以加固蜂窝芯的结构。
在本发明的第二实施例中,从以下步骤获得蜂窝芯:
i.将第一壁和第二壁分别切割成相同宽度的第一和第二条带,第一和第二条带各自具有第一和第二大体上平行的边缘,
ii.在第一条带和第二条带中的每一个的第一边缘中,分别制造第一平行狭槽和第二平行狭槽,
iii.通过将第一条带装配在第二条带的第二狭槽中并且将第二条带装配在第一条带的第一狭槽中来制造蜂窝芯,使得第一狭槽的底部与第二狭槽的底部接触。
第一和第二条带分别在第一和第二狭槽处的互锁允许简单且快速地制造蜂窝芯。所述蜂窝芯包括具有大体上矩形或方形形状并且具有大体上平行且长度相等的至少两个相对侧的成排的单元格。任选地,通过互锁第一和第二条带获得的单元格的形状大体上为方形,并且因此包括具有大体上相等的长度和大体上平行的相对侧的四侧。
在一个实施例变型中,第一和第二条带具有相同宽度。
有利的是,第一条带的宽度、第二条带的宽度和狭槽的深度被设定尺寸以使得第一条带的第一边缘与第二条带的第二边缘齐平,和/或第一条带的第二边缘与第二条带的第一边缘齐平。
第一条带的所有第一边缘与第二条带的第二边缘齐平和/或第一条带的所有第二边缘与第二条带的第一边缘齐平能促进第三壁和/或第四壁的必要的加工以在两侧上形成覆盖蜂窝芯的表层。优选地,第一条带的所有第一边缘与第二条带的第二边缘齐平,并且第一条带的所有第二边缘与第二条带的第一边缘齐平,由此促进构成包封蜂窝芯的表层的第三壁和第四壁的加工。
在实际实施例中,第一条带和第二条带具有相同宽度,并且第一和第二条带的第一和第二狭槽分别从第一边缘开始延伸超过第一和第二条带的一半宽度。因此,在其中狭槽沿平行于宽度方向的方向延伸的优选情况下,第一条带的第一边缘与第二条带的第二边缘齐平,并且第一条带的所有第二边缘与第二条带的第一边缘齐平。
有利的是,复合隔音板的第二实施例可包含以下步骤:将粘合剂施加到第一和第二条带会合的区域,所述粘合剂优选为陶瓷胶。
优选的是将粘合剂施加到第一和第二条带的接合区域,以加固蜂窝芯结构。当第一和第二条带嵌套时,可在第一和第二条带的相交点处施加粘合剂。任选地,在嵌套第一和第二条带之前,还将粘合剂施加到第一和第二狭槽中的每一个的侧和底部。
有利的是,根据第一制造方法和/或第二制造方法制造复合隔音板的方法可包括以下步骤:将粘合剂施加到蜂窝芯与第三壁和第四壁中的至少一个的接合区域,所述粘合剂优选为陶瓷胶。因此,第三壁和第四壁接合到蜂窝芯。
所使用的粘合剂优选地是陶瓷胶或氧化物预制陶瓷树脂。陶瓷粘合剂可由氧化陶瓷填料(大部分常为氧化铝)和一组短效粘结剂制成。陶瓷粘合剂还可由陶瓷填料和矿物聚合物类型粘结剂(偏磷酸铝)或氧化铝溶胶或溶胶-凝胶、硅溶胶(Ludox)制成。最后,陶瓷胶可由可填充有氧化铝的聚硅氧烷族的陶瓷前驱体制成。
所得复合隔音板优选地由包括呈双轴或单向纤维网形式的氧化物基质和长氧化物纤维的复合材料制成,因为其成本、重量和厚度低于三维织物的成本、重量和厚度。
优选地,蜂窝芯的单元格具有矩形或方形形状,并且这与选自先前所提及的两个的实施例无关。
根据特定实施例,第一壁、第二壁、第三壁和第四壁中的至少一个是通过热成型而获得的。
在另一特定实施例中,第一壁、第二壁、第三壁和第四壁中的至少一个是通过借助于压印成形而获得的。
优选地,所述方法包括至少一个脱粘步骤,随后是烧结步骤,脱粘和烧结步骤能够在以下步骤中的至少一个之后进行:
获得第一、第二、第三或第四壁中的一个,
切割出条带,
将条带组装在狭槽中,以及
将第三壁(24)和第四壁(26)粘接到所述蜂窝芯(12)。
在一个特定实施例中,所述方法包含使将纤维粘结在一起的第一粘结剂脱粘的步骤。此第一粘结剂的移除可在压印中进行,压印是保持封闭的并且包括氧化铝粉末或硅铝酸盐和第二粘结剂的浆料被引入到压印中。浆料的引入可通过注射或输注进行。
当参考附图阅读作为非限制性实例给出的以下描述时,将更好地理解本发明,并且本发明的其它细节、特性和优点将呈现出来。
附图说明
图1是根据现有技术的用于涡轮机的隔音板的透视图;
图2a到2d示出了根据本发明第一实施例的隔音板的各种制造步骤;
图3a到3e示出了根据本发明第二实施例的隔音板的各种制造步骤。
具体实施方式
在以下详细描述中,术语“纤维”是指“长氧化物纤维”。当将根据本发明的隔音板10安装在涡轮机中时,术语“轴向”意指大体上平行于涡轮机的纵向轴线而定向的轴向方向。
图1涉及上文所描述的现有技术的隔音板10。
现在参考图2a到2d,其表示根据第一实施例的在陶瓷基复合材料中获得隔音板10的方法。
第一、第二、第三和第四复合壁20、22、24、26分别是由双轴纤维网或单向纤维网获得的。
在双轴纤维网的情况下,该网涂布有浆料,使得浆料渗透到所述网的孔隙率中并且因此形成复合壁。浆料填充有氧化铝粉末和粘结剂,所述粘结剂可为热塑性或短效热固性材料或预制陶瓷氧化物热固性材料。粘结剂允许经涂布双轴纤维网在热处理之后加固。在涂布之后,双轴纤维网在压力或真空油布下传递以确保浆料压缩和渗透到纤维网中。如果使用的粘结剂为短效粘结剂,那么以热处理的形式使经涂布薄片松散,使得从壁去除粘结剂。短效粘结剂意图通过脱粘方法去除。
涂布浆料的步骤可由输注或注射步骤替换。
在网由单向纤维构成的情况下,单向纤维借助于通常被称为“粘结剂”的第一粘结剂彼此粘合,确保它们之间的粘着。以所需形状将单向纤维网直接挂到压印中。此单向纤维网正进行脱粘。此脱粘产生孔隙率。一旦压印封闭,就将浆料注射到单向纤维上。经由STM(浆料传递模塑)法注射浆料,并且将固定在单向纤维网的单向纤维之间。所述浆料填充有氧化铝或硅铝酸盐粉末和热塑性粘结剂(通常为PVA)。浆料的氧化铝或硅铝酸盐形成复合材料的氧化物基质,并且热塑性材料确保单向纤维之间的粘着。浆料的粘结剂用于将氧化铝粉末颗粒或硅铝酸盐保持在一起。粘结剂防止氧化铝粉末或硅铝酸盐粉碎,并且因此这种材料不是很耐用,甚至在注射后也无法保持。此粘结剂随后将在烧结期间在稍后温度下去除,粉末颗粒足够稳固以确保材料的附着力。浆料的此次注射还允许单向纤维网呈压印的形状。因此,在注射之后获得的壁直接呈现所要的形状。
替代地,浆料注射步骤可由输注步骤替换。
应注意,单向纤维网还可由于存在于单向纤维网中的第一粘结剂而被热成型。加热第一粘结剂以允许单向纤维网符合压印的形状。一旦热成型已经完成,就通过使热水在封闭腔中循环来去除第一粘结剂。当移除第一粘结剂时,保持压印封闭,并且在压力下将包括氧化铝粉末或硅铝酸盐和粘结剂的浆料注射到单向纤维网上。
优选地,单向纤维网的厚度在0.1mm与0.3mm之间,并且双轴纤维网的厚度在0.3mm与0.6mm之间。
图2a、2c和2d中所示的波纹薄片28是通过使用上文所描述的方法中的一个形成第一壁20而获得的。
任选地,壁还可通过使用STM法或通过输注将事先涂布有经注射浆料的双轴纤维网进行热成型来获得。短效粘结剂可由陶瓷聚硅氧烷类型粘结剂(优选地为粉末填充的)替换。如果粘结剂为聚硅氧烷类型,那么将经涂布双轴纤维网进行热成型,并且接着热解以将聚硅氧烷转化成陶瓷氧化物。
当将隔音板10安装在涡轮机的壳体上时,波纹壁28(还可以被称为波纹薄片)的宽度指定为圆周分量,并且垂直于顶点部分30(且更通常地说垂直于波纹薄片28)的方向指定为径向方向。波纹薄片28在其宽度的方向上具有弯曲轮廓,以限定环扇区。波纹薄片28在其上游轴向端32与下游轴向端34之间包括沿轴向方向的一连串第一和第二顶点部分36、38以及顶点连接部分40。每一第一顶点部分36沿圆柱形表面(如图所示为42)在大体上轴向方向上延伸。每一第二顶点部分38沿圆柱形表面(如图所示为44)在大体上轴向方向上延伸。圆柱形表面42、44大致彼此平行并且因此不会混淆。每一顶点连接部分40延伸以将第一顶点部分36连接到第二顶点部分38。
因此,在图2a中,顶点的第一部分36都沿着圆柱形表面42对齐,并且顶点的第二部分38都沿着圆柱形表面44对齐。优选地,波纹薄片28的上游轴向端32和下游轴向端34形成也沿着圆柱形表面42延伸的第一顶点部分36。
第一顶点部分36、相应地为第二顶点部分38与邻近顶点的连接部分40一起限定梯形形状而无最大底。较小底由第一顶点部分36和第二顶点部分38相应地限定。梯形的两个非平行侧由在任一侧上连接到形成较小底的顶点部分36、38的顶点连接部分40限定。
每一第一顶点部分36和每一第二顶点部分38以及每一顶点连接部分40沿着弯曲轮廓的曲度跨越整个波纹薄片28的宽度延伸,使得波纹薄片28具有大体上为波纹的形状,并且波纹的方向沿着轴向轴线。
切割波纹薄片28以具有在轴向方向上延伸并且在垂直于波纹薄片的方向上开口的狭槽46。狭槽46在波纹薄片28中沿大体上轴向方向被切割以穿过第一顶点部分36、第一顶点部分36的邻近顶点部分的连接部分40、波纹薄片28的下游端34的部分,以及将其连接到第二顶点部分38的连接部分40。狭槽46中的每一个都意图收纳从第二壁22切割出的条带48。
应注意,可在使用聚硅氧烷的情况下在烧结之前或在聚合聚硅氧烷之后对狭槽46进行切割。对条带48的切割也可在聚硅氧烷聚合以及整个进行组装之后进行。在此情况下,将对整个系统进行热解。也有可能在聚合阶段处胶合两个表层14,并且因此同时对构成隔音分区16的聚硅氧烷进行热解以及对表层14的氧化铝基质进行烧结。
在使用短效第一粘结剂的情况下,优选的是进行以下操作:切割出狭槽、切割出条带48、组装络合物、在预烧结单式元件的阶段胶合表层14。一旦络合物已完全组装,将进行最终烧结以确保整体的结构粘着。
条带48一旦被插入就因此在垂直于波纹薄片28的方向上延伸并且沿着弯曲部横向地分割顶部的第一和第二部分36、38。
切割第二壁22以形成具有大致10mm宽度的大体上相同的条带48。此切割可为机械、喷水或激光方式。每一条带48包括第一笔直边缘50,第一笔直边缘从波纹薄片28的上游端32大体上轴向地延伸到所述波纹薄片的下游端34,以当插入条带时,沿垂直于波纹薄片28的方向从第一顶点部分36以及波纹薄片28的上游端32和下游端34突出。当将隔音板10安装在涡轮机外壳上时,突起的方向对应于径向方向,即径向朝内。条带48中的每一个的第二边缘52与第一边缘50相反延伸并且符合上游端32和连接波纹薄片28的上游端32的顶点连接部分40以及第二顶点部分38的形状。从所述上文所提到的顶点连接部分40的下游端54开始,条带48的第二边缘52平行于第一边缘50轴向地延伸,以符合第二顶点部分38的形状并且当插入条带48时邻接第二顶点部分。从由冠部连接部分40连接到波纹薄片28的下游端34的第二冠部部分38的下游端56开始,条带48的第二边缘52在轴向方向上向下游且朝向第一边缘50延伸。当第一与第二边缘50、52之间的间隔与在上游端34处的间隔相同时,第一边缘50与第二边缘52在轴向方向上平行延伸,使得第二边缘52遵循波纹薄片28的下游部分36的形状。
图2b示出了形成外表层(还可以被称为第一表层14,其已经成形为弯曲状)的第三壁24。第一弯曲表层14还包含在其宽度方向上弯曲以匹配波纹薄片28的弯曲轮廓的轮廓。第一弯曲表层14延伸与波纹薄片28相同的轴向距离。在轴向上,第一表层14形成为在包括波纹薄片28的上游端34和第二顶点部分38的部分上符合波纹薄片28的形状。从由顶点连接部分40连接到波纹薄片28的下游端34的第二顶点部分38的下游端56开始,第一弯曲表层14被成形以遵循插入到波纹薄片28中的条带48的第二边缘52的形状。
图2c示出了由波纹薄片28和插入到波纹薄片28的狭槽46中的条带48组成的蜂窝芯12。当将隔音板10安装在涡轮机中时,由第一顶点部分36限定的蜂窝芯12的每个单元格18径向向外打开。相应地,当将隔音板10安装在涡轮机中时,由第二顶点部分38限定的蜂窝芯12的每个单元格18径向向内打开。
当将形成分区16的条带48插入到波纹薄片28的狭槽48中时,优选的是在波纹薄片28和条带48的接合区域处施加粘合剂。这些接合区由狭槽46的端限定。将粘合剂施加到接合区域将会加固蜂窝芯12。
任选地,粘合剂可在插入条带48之前施加在意图与条带48接触的狭槽46的端部。
当蜂窝芯12被形成和加固时,形成隔音板10的外和内表层14(还可以被称为第一表层和第二表层)的第三壁24和第四壁(未示出)在垂直于波纹薄片28的方向上固定在蜂窝芯12的任一侧上,以包封单元格18。
从第四壁26获得的第二表层(未示出)覆盖蜂窝芯12的与由从第三壁24获得的第一表层覆盖的侧相对的侧。第二表层围绕隔音板10的整个圆周周向地延伸,并且从第一表层的上游端纵向延伸到下游端。第二表层被成形以粘附到蜂窝芯12,并且第一表层在蜂窝芯12的上游和下游径向布置在蜂窝芯12外部。
为了确保表层14附接到蜂窝芯12,将粘合剂施加到与蜂窝芯12的顶部的第一和第二部分36、38接触的表层14的表面58。替代地或另外,在波纹薄片28的下游端36处,将粘合剂施加到波纹薄片28的上游端34的表面60、第二顶点部分38的表面62和条带48的第二边缘52。上游端32的表面60、62和顶部的第二部分38以及条带48的第二边缘52与由第三壁24形成的表层14相对。所使用的粘合剂优选地为预制陶瓷氧化物树脂或陶瓷胶,如上文所描述。
当表层14固定时,获得根据第一实施例的隔音板10。
优选地,当分别获得波纹薄片28、形成蜂窝芯12的单元格18的分区16的条带48、表层14时,可进行脱粘和预烧结。
进行脱粘以从使用第一、第二、第三和第四壁20、22、24、26获得的上述部分中去除浆料。在预烧结循环中的温度上升期间去除此浆料。
预烧结在大致1,000到1,100℃的温度下进行以使材料固结。在此温度下,氧化铝粉末的颗粒在其之间建立桥梁,赋予了材料强度。
任选地,还可在将条带48组装在波纹薄片28的狭槽46中之后或在将表层14胶合到蜂窝芯12之后进行这些脱粘和预烧结步骤。
图3a到3e示出根据本发明的第二实施例的隔音板。
在复合隔音板10的第二实施例中,如在第一实施例中,第一、第二、第三和第四复合壁20、22、24、26分别是由双轴纤维网或单向纤维网获得。
图3a示出了在涂布和按压或真空形成之后获得的第一复合壁20。示出了呈平行虚线形式以形成第一条带66的第一壁20的切块区域64。此切割可为机械、喷水或激光方式。第一条带66具有大致矩形形状。每一第一条带66的宽度68约为10mm。
通过与第一壁20相同的方法获得第二壁22,并且第二壁还切割成具有与第一条带66相同的特性的第二条带70。
任选地,可从第一壁20和/或第二壁22获得第一和第二条带66、70。
第一和第二条带66、70各自包括限定第一和第二条带66、70的长度的第一平行边缘72和第二平行边缘74。第一和第二条带66、70的第一和第二边缘72、74间隔开,以限定第一和第二条带66、70的宽度68。
图3b示出了第一条带66中的第一狭槽76和第二条带70中相应的第二狭槽78的切割。第一和第二狭槽76、78分别在平行于第一和第二条带66、70的宽度68的方向上从其相应的第一边缘72延伸。第一和第二狭槽76、78各自包括底部80和在所述底部80的任一侧上平行延伸的两个侧面82。第一和第二狭槽76、78中的每一个分别延伸超过第一和第二条带66、70的一半宽度68。分别具有第一和第二狭槽76、78的第一和第二条带66、70形成梳状物。第一条带66的第一狭槽76相等地间隔开。第二条带70的第二狭槽78以彼此相等的距离相等地间隔开。
图3c示出了在第二条带70的第二狭槽78中的第一条带66的互锁和在第一条带66的第一狭槽76中的第二条带70的互锁,使得第一狭槽76的底部80与第二狭槽78的底部80接触。
第一条带66的第一狭槽76彼此相等地间隔开,并且同样地,第二条带70的第二狭槽78也相等地间隔开。所有第一条带66大体上相同,并且所有第二条带70大体上相同。当将第一条带66嵌套在第二条带70的第二狭槽78中时,第一条带66彼此平行而延伸。类似地,当将第二条带70嵌套在第一条带66的第一狭槽76中时,第二条带70彼此平行而延伸。第二条带70垂直于第一条带66延伸。
因此,第一和第二条带66、70的这些嵌套允许制造蜂窝芯12(图3d中示出)。蜂窝芯12的单元格18由第一条带66与第二条带70的相交点限定。因此,单元格18由两个连续第一条带66与两个连续第二条带70的相交点限定。第一条带66和相应的第二条带70的平行以及第一和第二条带66、70的垂直允许限定具有矩形且优选地为方形形状的单元格18。单元格18包含在限定单元格18的第一和第二条带66、70的露出部分处的开口端。
有利的是,当通过互锁第一条带66和第二条带70获得蜂窝芯12时,在第一和第二条带66、70的接合区域处施加粘合剂,以加固蜂窝芯12并且以避免构成蜂窝芯12的第一条带66和第二条带70的分离。
任选地,在嵌套第一和第二条带66、70之前,可将粘合剂施加到第一和第二狭槽66、70中的每一个的底部80和侧面82。
在制造和加固蜂窝芯12时,对使用第一、第二、第三和第四壁20、22、24、26而获得的部分进行脱粘和预烧结。所述方法与本发明的第一实施例中所描述的方法相同。
当脱粘和预烧结已完成时,将形成表层14的第三壁24和第四壁26定位在蜂窝芯12的任一侧上,以覆盖单元格18的开口端,如图3e中所示。形成表层14的第三壁24和第四壁26用粘合剂附接到蜂窝芯12。优选地,粘合剂为氧化物陶瓷胶。将氧化物陶瓷粘合剂施加到与蜂窝芯12接触的第三壁24的表面和第四壁26的表面,和/或施加到要与第三和第四壁24、26接触的单元格18的开口端。
表层14与蜂窝芯12的组装使得有可能制造根据第二实施例的隔音板10。
根据第一和第二实施例的隔音板10呈环形扇区的形式。若干隔音板10可周向地端对端布置以形成隔音板10的环。
Claims (13)
1.制造复合面板的方法,特别是在涡轮机中的复合面板,其特征在于,所述方法包括以下步骤:
a)由复合材料制造第一壁(20)、第二壁(22)、第三壁(24)和第四壁(26),所述复合材料包括氧化物基质和长氧化物纤维,
b)由第一和第二壁(20、22)形成具有多个单元格(18)的蜂窝芯(12),每个单元格(18)具有第一端和相对的第二端,
c)分别用第三壁(24)和第四壁(26)覆盖所述蜂窝芯(12)的单元格(18)的第一和第二端,以封闭单元格(18)的端部。
2.根据权利要求1所述的方法,其特征在于,所述方法包括以下步骤:
i.形成第一壁以获得波纹壁(28),所述波纹壁(28)具有由顶点连接部分(40)互连的交替的第一和第二顶点部分(36、38),
ii.在第一顶点部分(36)和第一壁(20)的所述顶点连接部分(40)中切割出狭槽,
iii.在第二壁(22)中制造切口以获得多个条带(48),
iv.将条带(48)插入到第一壁(20)的狭槽(46)中以对多个单元格(18)定界。
3.根据权利要求2所述的方法,其特征在于,所述方法包括以下步骤:将粘合剂施加到第一壁(20)和条带(48)的接合区域,所述粘合剂优选为陶瓷胶。
4.根据权利要求1所述的方法,其特征在于,所述方法包括以下步骤:
i.将第一壁(20)和第二壁(22)分别切割成相同宽度(68)的第一条带(66)和第二条带(70),第一条带(66)和第二条带(70)各自具有大体上平行的第一边缘(72)和第二边缘(74),
ii.在第一条带(66)和第二条带(70)中的每一个的第一边缘(72)中,分别制造第一平行狭槽(76)和第二平行狭槽(78),
iii.通过将第一条带(66)嵌套在第二条带(70)的第二狭槽(78)中并且将第二条带(70)嵌套在第一条带(66)的第一狭槽(76)中来形成所述蜂窝芯(12),使得第一狭槽(76)的底部(80)与第二狭槽(78)的底部(80)接触。
5.根据权利要求4所述的方法,其特征在于,第一条带(66)和第二条带(70)具有相同宽度(68)。
6.根据权利要求4或5所述的方法,其特征在于,第一条带(66)的宽度(68)、第二条带(70)的宽度(68)和狭槽(76、78)的深度被设定尺寸以使得第一条带(66)的第一边缘(72)与第二条带(70)的第二边缘(74)齐平,和/或第一条带(66)的第二边缘(74)与第二条带(70)的第一边缘(72)齐平。
7.根据权利要求4到6中任一项所述的方法,其特征在于,所述方法包括以下步骤:将粘合剂施加到第一条带(66)和第二条带(70)的接合区域,所述粘合剂优选为陶瓷胶。
8.根据权利要求2到7中任一项所述的方法,其特征在于,所述方法包括以下步骤:将粘合剂施加到所述蜂窝芯(12)与第三壁(24)和第四壁(26)中的至少一个的接合区域,所述粘合剂优选为陶瓷胶。
9.根据权利要求1到8中任一项所述的方法,其特征在于,所述复合材料是通过将粘结浆料添加到双轴或单向纤维网而获得的。
10.根据权利要求1到9中任一项所述的方法,其特征在于,第一壁(20)、第二壁(22)、第三壁(24)和第四壁(26)中的至少一个是通过热成型而获得的。
11.根据权利要求1到9中任一项所述的方法,其特征在于,第一壁(20)、第二壁(22)、第三壁(24)和第四壁(26)中的至少一个是通过借助于压印成形而获得的。
12.根据权利要求1到11中任一项所述的方法,其特征在于,所述方法包括至少一个脱粘步骤,随后是烧结步骤,脱粘和烧结步骤能够在以下步骤中的至少一个之后进行:
-获得第一、第二、第三或第四壁(20、22、24、26)中的一个,
-切割出条带(48、66、70),
-将条带(48、66、70)组装在狭槽(46、76、78)中,以及
-将第三壁(24)和第四壁(26)粘接到所述蜂窝芯(12)。
13.根据权利要求1到12中任一项所述的方法,其特征在于,第三壁(24)和第四壁(26)中的至少一个包括穿孔,穿孔中的每一个通向单元格(18)。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1856607 | 2018-07-17 | ||
FR1856607A FR3084011B1 (fr) | 2018-07-17 | 2018-07-17 | Procede de fabrication d'un panneau accoustique |
PCT/FR2019/051782 WO2020016520A1 (fr) | 2018-07-17 | 2019-07-16 | Procede de fabrication d'un panneau acoustique |
Publications (2)
Publication Number | Publication Date |
---|---|
CN112469569A true CN112469569A (zh) | 2021-03-09 |
CN112469569B CN112469569B (zh) | 2023-05-05 |
Family
ID=65031449
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN201980046980.XA Active CN112469569B (zh) | 2018-07-17 | 2019-07-16 | 制造隔音板的方法 |
Country Status (5)
Country | Link |
---|---|
US (1) | US20210323295A1 (zh) |
EP (1) | EP3823831A1 (zh) |
CN (1) | CN112469569B (zh) |
FR (1) | FR3084011B1 (zh) |
WO (1) | WO2020016520A1 (zh) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112873939A (zh) * | 2021-03-10 | 2021-06-01 | 沈阳吉化轨道工程科技开发有限公司 | 一种组合式蜂窝及其制备方法 |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3081510B1 (fr) * | 2018-05-24 | 2020-05-29 | Safran Nacelles | Panneau d’attenuation acoustique pour nacelle de turboreacteur d’aeronef |
FR3111949B1 (fr) * | 2020-06-26 | 2022-06-10 | Safran Ceram | Caisson acoustique pour un cône d’éjection |
IT202100017474A1 (it) * | 2021-07-02 | 2023-01-02 | Leonardo Spa | Procedimento di fabbricazione di un nucleo per pannello fonoassorbente con struttura a sandwich per la riduzione del rumore in un aeromobile |
DE102022129653A1 (de) | 2022-11-09 | 2024-05-16 | Rolls-Royce Deutschland Ltd & Co Kg | Verfahren zum Herstellen einer akustisch dämpfenden zellularen Struktur, akustisch dämpfende zellulare Struktur und strömungsführendes Bauteil mit mehreren akustisch dämpfenden zellularen Strukturen |
CN115891302A (zh) * | 2022-11-14 | 2023-04-04 | 傅洪杰 | 一种蜂窝芯板及其加工工艺 |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN101557924A (zh) * | 2006-12-15 | 2009-10-14 | 纳幕尔杜邦公司 | 制造成型的蜂窝结构的方法及由此制造的蜂窝结构 |
US20090263627A1 (en) * | 2008-04-21 | 2009-10-22 | The Boeing Company | Exhaust Washed Structure And Associated Composite Structure And Method Of Fabrication |
CN102292210A (zh) * | 2009-02-05 | 2011-12-21 | 埃尔塞乐公司 | 制造涡轮喷气发动机舱用的具有孔格芯体的结构的方法 |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2960197A (en) * | 1958-10-07 | 1960-11-15 | Engelhard Ind Inc | Sandwich structure |
US4034135A (en) * | 1975-11-20 | 1977-07-05 | Passmore Michael Edward Anthon | Rigid structure |
FR2493304A1 (fr) * | 1980-10-30 | 1982-05-07 | Europ Propulsion | Procede d'assemblage de pieces refractaires |
SU1743891A1 (ru) * | 1990-04-16 | 1992-06-30 | Челябинский Политехнический Институт Им.Ленинского Комсомола | Способ изготовлени трехслойных панелей с сотовым заполнителем и устройство дл его осуществлени |
FR2701665B1 (fr) * | 1993-02-17 | 1995-05-19 | Europ Propulsion | Procédé de fabrication d'une pièce en matériau composite, notamment un panneau sandwich, à partir de plusieurs préformes assemblées. |
US20130167374A1 (en) * | 2011-12-29 | 2013-07-04 | General Electric Company | Process of producing ceramic matrix composites and ceramic matrix composites formed thereby |
FR3030503B1 (fr) * | 2014-12-23 | 2019-08-23 | Safran | Procede de fabrication d'une piece en materiau composite |
FR3044963B1 (fr) * | 2015-12-14 | 2018-01-19 | Safran Nacelles | Procede de fabrication d’un panneau sandwich composite pour un ensemble propulsif d’aeronef |
-
2018
- 2018-07-17 FR FR1856607A patent/FR3084011B1/fr active Active
-
2019
- 2019-07-16 US US17/260,006 patent/US20210323295A1/en active Pending
- 2019-07-16 CN CN201980046980.XA patent/CN112469569B/zh active Active
- 2019-07-16 WO PCT/FR2019/051782 patent/WO2020016520A1/fr unknown
- 2019-07-16 EP EP19753167.6A patent/EP3823831A1/fr active Pending
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN101557924A (zh) * | 2006-12-15 | 2009-10-14 | 纳幕尔杜邦公司 | 制造成型的蜂窝结构的方法及由此制造的蜂窝结构 |
US20090263627A1 (en) * | 2008-04-21 | 2009-10-22 | The Boeing Company | Exhaust Washed Structure And Associated Composite Structure And Method Of Fabrication |
CN102292210A (zh) * | 2009-02-05 | 2011-12-21 | 埃尔塞乐公司 | 制造涡轮喷气发动机舱用的具有孔格芯体的结构的方法 |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112873939A (zh) * | 2021-03-10 | 2021-06-01 | 沈阳吉化轨道工程科技开发有限公司 | 一种组合式蜂窝及其制备方法 |
Also Published As
Publication number | Publication date |
---|---|
EP3823831A1 (fr) | 2021-05-26 |
US20210323295A1 (en) | 2021-10-21 |
CN112469569B (zh) | 2023-05-05 |
FR3084011A1 (fr) | 2020-01-24 |
WO2020016520A1 (fr) | 2020-01-23 |
FR3084011B1 (fr) | 2021-02-26 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CN112469569B (zh) | 制造隔音板的方法 | |
CN108868901B (zh) | 具有微通道的cmc部件及用于在cmc部件中形成微通道的方法 | |
US8043690B2 (en) | Exhaust washed structure and associated composite structure and method of fabrication | |
JP5599865B2 (ja) | 複合材料から作られるターボ機械ブレードを製造する方法 | |
US10151207B2 (en) | High strength joints in ceramic matrix composite preforms | |
US9784113B2 (en) | Method of fabricating a turbine or compressor guide vane sector made of composite material for a turbine engine, and a turbine or a compressor incorporating such guide vane sectors | |
CN109424371B (zh) | 用于燃气涡轮发动机的流径组件及其组装方法 | |
CN106640206B (zh) | 单面板或多面板的制造 | |
US9261008B2 (en) | Exhaust with an acoustic attenuation system | |
EP3339573B1 (en) | Composite turbine vane with three-dimensional fiber reinforcements | |
JP6038153B2 (ja) | タービンエンジン用の、複合材料で作られたタービンノズルまたは圧縮機静翼のセクタの製造方法、および前記セクタからなるノズルまたは静翼を含むタービンまたは圧縮機 | |
EP3075531A1 (en) | Sandwich arrangement with ceramic panels and ceramic felts | |
US20100189556A1 (en) | Segmented ceramic matrix composite turbine airfoil component | |
EP3447760B1 (en) | Method for forming a structural panel | |
US10239227B2 (en) | Method of manufacturing a composite sandwich panel for an aircraft propulsion unit | |
EP3049626B1 (en) | Cmc airfoil with sharp trailing edge and method of making same | |
WO2016009817A1 (ja) | セラミックス基複合材料よりなるタービン静翼 | |
US11643948B2 (en) | Internal cooling circuits for CMC and method of manufacture | |
CN109178291B (zh) | 用于形成纤维增强复合结构的方法 | |
CN111318856A (zh) | 形成具有一个或多个结构加强件的结构化面板 | |
CN114434881A (zh) | 夹层结构面板及制造方法 | |
US11959440B2 (en) | Acoustic attenuation structure made of composite material and method for manufacturing same | |
JP7455549B2 (ja) | 開口部で画定された内側部分を有するプライによるcmc積層およびノズル端壁 |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PB01 | Publication | ||
PB01 | Publication | ||
SE01 | Entry into force of request for substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
GR01 | Patent grant | ||
GR01 | Patent grant |