CN115162021A - Formula and preparation method of aircraft engine heat shield - Google Patents
Formula and preparation method of aircraft engine heat shield Download PDFInfo
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- CN115162021A CN115162021A CN202210905676.XA CN202210905676A CN115162021A CN 115162021 A CN115162021 A CN 115162021A CN 202210905676 A CN202210905676 A CN 202210905676A CN 115162021 A CN115162021 A CN 115162021A
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- 238000009472 formulation Methods 0.000 title claims description 6
- 238000002360 preparation method Methods 0.000 title abstract description 10
- 239000000853 adhesive Substances 0.000 claims abstract description 31
- 230000001070 adhesive effect Effects 0.000 claims abstract description 31
- 239000003822 epoxy resin Substances 0.000 claims abstract description 31
- 229920000647 polyepoxide Polymers 0.000 claims abstract description 31
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 26
- 239000000843 powder Substances 0.000 claims abstract description 22
- 239000003085 diluting agent Substances 0.000 claims abstract description 13
- 239000003973 paint Substances 0.000 claims abstract description 13
- 229920001296 polysiloxane Polymers 0.000 claims abstract description 13
- 238000009413 insulation Methods 0.000 claims abstract description 12
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 4
- 230000009974 thixotropic effect Effects 0.000 claims abstract description 4
- 239000000203 mixture Substances 0.000 claims description 77
- 238000003756 stirring Methods 0.000 claims description 54
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 42
- 238000000465 moulding Methods 0.000 claims description 37
- 239000011265 semifinished product Substances 0.000 claims description 36
- 238000002156 mixing Methods 0.000 claims description 27
- 239000004744 fabric Substances 0.000 claims description 22
- 239000000377 silicon dioxide Substances 0.000 claims description 21
- 239000000047 product Substances 0.000 claims description 20
- 238000001816 cooling Methods 0.000 claims description 19
- 239000002994 raw material Substances 0.000 claims description 18
- 239000011248 coating agent Substances 0.000 claims description 15
- 238000000576 coating method Methods 0.000 claims description 15
- 238000004519 manufacturing process Methods 0.000 claims description 13
- 239000011148 porous material Substances 0.000 claims description 12
- 238000007731 hot pressing Methods 0.000 claims description 9
- 238000009966 trimming Methods 0.000 claims description 9
- 238000003892 spreading Methods 0.000 claims description 8
- 230000007480 spreading Effects 0.000 claims description 8
- 230000001680 brushing effect Effects 0.000 claims description 7
- 230000007547 defect Effects 0.000 claims description 5
- 230000006978 adaptation Effects 0.000 claims description 3
- 238000004026 adhesive bonding Methods 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 7
- 239000000463 material Substances 0.000 abstract description 7
- 230000003647 oxidation Effects 0.000 abstract description 4
- 238000007254 oxidation reaction Methods 0.000 abstract description 4
- 238000000034 method Methods 0.000 description 10
- 238000005507 spraying Methods 0.000 description 6
- 239000012774 insulation material Substances 0.000 description 5
- 239000007921 spray Substances 0.000 description 4
- 239000012752 auxiliary agent Substances 0.000 description 3
- 239000011153 ceramic matrix composite Substances 0.000 description 3
- 230000006872 improvement Effects 0.000 description 2
- 239000011810 insulating material Substances 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 239000004809 Teflon Substances 0.000 description 1
- 229920006362 Teflon® Polymers 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 238000000748 compression moulding Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- D—TEXTILES; PAPER
- D06—TREATMENT OF TEXTILES OR THE LIKE; LAUNDERING; FLEXIBLE MATERIALS NOT OTHERWISE PROVIDED FOR
- D06N—WALL, FLOOR, OR LIKE COVERING MATERIALS, e.g. LINOLEUM, OILCLOTH, ARTIFICIAL LEATHER, ROOFING FELT, CONSISTING OF A FIBROUS WEB COATED WITH A LAYER OF MACROMOLECULAR MATERIAL; FLEXIBLE SHEET MATERIAL NOT OTHERWISE PROVIDED FOR
- D06N3/00—Artificial leather, oilcloth or other material obtained by covering fibrous webs with macromolecular material, e.g. resins, rubber or derivatives thereof
- D06N3/12—Artificial leather, oilcloth or other material obtained by covering fibrous webs with macromolecular material, e.g. resins, rubber or derivatives thereof with macromolecular compounds obtained otherwise than by reactions only involving carbon-to-carbon unsaturated bonds, e.g. gelatine proteins
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- D—TEXTILES; PAPER
- D06—TREATMENT OF TEXTILES OR THE LIKE; LAUNDERING; FLEXIBLE MATERIALS NOT OTHERWISE PROVIDED FOR
- D06N—WALL, FLOOR, OR LIKE COVERING MATERIALS, e.g. LINOLEUM, OILCLOTH, ARTIFICIAL LEATHER, ROOFING FELT, CONSISTING OF A FIBROUS WEB COATED WITH A LAYER OF MACROMOLECULAR MATERIAL; FLEXIBLE SHEET MATERIAL NOT OTHERWISE PROVIDED FOR
- D06N3/00—Artificial leather, oilcloth or other material obtained by covering fibrous webs with macromolecular material, e.g. resins, rubber or derivatives thereof
- D06N3/0056—Artificial leather, oilcloth or other material obtained by covering fibrous webs with macromolecular material, e.g. resins, rubber or derivatives thereof characterised by the compounding ingredients of the macro-molecular coating
- D06N3/0061—Organic fillers or organic fibrous fillers, e.g. ground leather waste, wood bark, cork powder, vegetable flour; Other organic compounding ingredients; Post-treatment with organic compounds
-
- D—TEXTILES; PAPER
- D06—TREATMENT OF TEXTILES OR THE LIKE; LAUNDERING; FLEXIBLE MATERIALS NOT OTHERWISE PROVIDED FOR
- D06N—WALL, FLOOR, OR LIKE COVERING MATERIALS, e.g. LINOLEUM, OILCLOTH, ARTIFICIAL LEATHER, ROOFING FELT, CONSISTING OF A FIBROUS WEB COATED WITH A LAYER OF MACROMOLECULAR MATERIAL; FLEXIBLE SHEET MATERIAL NOT OTHERWISE PROVIDED FOR
- D06N3/00—Artificial leather, oilcloth or other material obtained by covering fibrous webs with macromolecular material, e.g. resins, rubber or derivatives thereof
- D06N3/0056—Artificial leather, oilcloth or other material obtained by covering fibrous webs with macromolecular material, e.g. resins, rubber or derivatives thereof characterised by the compounding ingredients of the macro-molecular coating
- D06N3/0063—Inorganic compounding ingredients, e.g. metals, carbon fibres, Na2CO3, metal layers; Post-treatment with inorganic compounds
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- D—TEXTILES; PAPER
- D06—TREATMENT OF TEXTILES OR THE LIKE; LAUNDERING; FLEXIBLE MATERIALS NOT OTHERWISE PROVIDED FOR
- D06N—WALL, FLOOR, OR LIKE COVERING MATERIALS, e.g. LINOLEUM, OILCLOTH, ARTIFICIAL LEATHER, ROOFING FELT, CONSISTING OF A FIBROUS WEB COATED WITH A LAYER OF MACROMOLECULAR MATERIAL; FLEXIBLE SHEET MATERIAL NOT OTHERWISE PROVIDED FOR
- D06N3/00—Artificial leather, oilcloth or other material obtained by covering fibrous webs with macromolecular material, e.g. resins, rubber or derivatives thereof
- D06N3/007—Artificial leather, oilcloth or other material obtained by covering fibrous webs with macromolecular material, e.g. resins, rubber or derivatives thereof characterised by mechanical or physical treatments
- D06N3/0077—Embossing; Pressing of the surface; Tumbling and crumbling; Cracking; Cooling; Heating, e.g. mirror finish
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- D—TEXTILES; PAPER
- D06—TREATMENT OF TEXTILES OR THE LIKE; LAUNDERING; FLEXIBLE MATERIALS NOT OTHERWISE PROVIDED FOR
- D06N—WALL, FLOOR, OR LIKE COVERING MATERIALS, e.g. LINOLEUM, OILCLOTH, ARTIFICIAL LEATHER, ROOFING FELT, CONSISTING OF A FIBROUS WEB COATED WITH A LAYER OF MACROMOLECULAR MATERIAL; FLEXIBLE SHEET MATERIAL NOT OTHERWISE PROVIDED FOR
- D06N3/00—Artificial leather, oilcloth or other material obtained by covering fibrous webs with macromolecular material, e.g. resins, rubber or derivatives thereof
- D06N3/0086—Artificial leather, oilcloth or other material obtained by covering fibrous webs with macromolecular material, e.g. resins, rubber or derivatives thereof characterised by the application technique
- D06N3/0088—Artificial leather, oilcloth or other material obtained by covering fibrous webs with macromolecular material, e.g. resins, rubber or derivatives thereof characterised by the application technique by directly applying the resin
-
- 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
- F02C7/24—Heat or noise insulation
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- D—TEXTILES; PAPER
- D06—TREATMENT OF TEXTILES OR THE LIKE; LAUNDERING; FLEXIBLE MATERIALS NOT OTHERWISE PROVIDED FOR
- D06N—WALL, FLOOR, OR LIKE COVERING MATERIALS, e.g. LINOLEUM, OILCLOTH, ARTIFICIAL LEATHER, ROOFING FELT, CONSISTING OF A FIBROUS WEB COATED WITH A LAYER OF MACROMOLECULAR MATERIAL; FLEXIBLE SHEET MATERIAL NOT OTHERWISE PROVIDED FOR
- D06N2209/00—Properties of the materials
- D06N2209/06—Properties of the materials having thermal properties
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- D—TEXTILES; PAPER
- D06—TREATMENT OF TEXTILES OR THE LIKE; LAUNDERING; FLEXIBLE MATERIALS NOT OTHERWISE PROVIDED FOR
- D06N—WALL, FLOOR, OR LIKE COVERING MATERIALS, e.g. LINOLEUM, OILCLOTH, ARTIFICIAL LEATHER, ROOFING FELT, CONSISTING OF A FIBROUS WEB COATED WITH A LAYER OF MACROMOLECULAR MATERIAL; FLEXIBLE SHEET MATERIAL NOT OTHERWISE PROVIDED FOR
- D06N2211/00—Specially adapted uses
- D06N2211/12—Decorative or sun protection articles
- D06N2211/26—Vehicles, transportation
- D06N2211/267—Aircraft
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- Engineering & Computer Science (AREA)
- Textile Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Dispersion Chemistry (AREA)
- Life Sciences & Earth Sciences (AREA)
- Wood Science & Technology (AREA)
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- Paints Or Removers (AREA)
- Adhesives Or Adhesive Processes (AREA)
Abstract
The invention discloses a formula of an aircraft engine heat shield and a preparation method thereof, relating to the technical field of aviation materials, wherein the formula comprises the following components in parts by weight: 45-70 parts of silicone paint, 30-55 parts of diluent, 10-15 parts of epoxy resin adhesive and 5-10 parts of fine powder aluminum powder. The epoxy resin adhesive is an aluminum-filled, thixotropic, single-component epoxy resin adhesive. By adopting the technical scheme, the invention can ensure the heat insulation effect, increase the oxidation resistance and high temperature resistance, and has simple preparation process.
Description
Technical Field
The invention relates to the technical field of aviation materials, in particular to a preparation method of an aircraft engine heat shield.
Background
With the rapid development of the domestic aviation industry, the engine is particularly obvious as the heart of the aviation industry, and directly influences various performances of an airplane, but because the engine generates huge heat in the working process, the performances and the service life of peripheral components are influenced, and meanwhile, the requirements on the peripheral components are increased; therefore, the protection of the engine heat becomes more important, and the current protection measures of the engine heat are directly covered by soft fiber heat-insulating materials, but the material structure is damaged due to vibration at high temperature, so that the heat-insulating effect is influenced; at present, hard heat shields made of high-temperature ceramic matrix composite materials are available in the market, but the ceramic matrix composite materials are high in heat conductivity and easy to cause heat conduction, so that the application and development of the ceramic matrix composite materials on engine heat insulation are greatly limited, and the development of heat insulation materials with excellent heat insulation performance is particularly important for the heat insulation technology of aero-engines.
In view of the above, the present invention is conceived based on the defects and inconveniences caused by the improvements mentioned above, and the present invention is developed and designed through active research and improvement.
Disclosure of Invention
Aiming at the defects and shortcomings of the prior art, the invention provides the formula of the aircraft engine heat shield and the preparation method thereof, wherein the formula can ensure the heat insulation effect, increase the oxidation resistance and the high temperature resistance and has a simple preparation process.
In order to achieve the purpose, the invention adopts the following technical scheme:
a formulation for an aircraft engine heat shield, the formulation comprising by weight: 45-70 parts of silicone paint, 30-55 parts of diluent, 10-15 parts of epoxy resin adhesive and 5-10 parts of fine powder aluminum powder.
Further, the epoxy resin adhesive is an aluminum-filled, thixotropic, one-component epoxy resin adhesive.
A method of making an aircraft engine heat shield, comprising the steps of:
the method comprises the following steps: taking 45-70 parts of silicone paint and 30-55 parts of diluent, and stirring and mixing the raw materials in percentage by weight at the temperature of 10-35 ℃ at the stirring speed of 100-600 r/min to prepare a mixture A;
step two: taking 10-15 parts of epoxy resin adhesive and 5-10 parts of fine powder aluminum powder, stirring and mixing the raw materials in percentage by weight at the temperature of 10-35 ℃, and stirring at the speed of 20-50 r/min to prepare a mixture B;
step three: taking 80-85 parts of the mixture A obtained in the step one and 15-20 parts of the mixture B obtained in the step two, and stirring and mixing at the temperature of 10-35 ℃ at the stirring speed of 100-600 r/min to obtain a mixture C;
step four: flatly paving high silica cloth with the thickness of 0.5-0.75 mm in a mold cavity of a heat shield, uniformly coating the mixture C obtained in the step three on the upper surface and the lower surface of the high silica cloth by using a brush, and coating the mixture C with the thickness of 0.2-0.3 mm; then closing the mold, placing the mold into a hot pressing table for molding, cooling to below 60 ℃, opening the mold to obtain a molded semi-finished product, and performing trimming treatment;
step five: and (4) uniformly brushing the mixture C obtained in the third step on the upper surface and the lower surface of the semi-finished product obtained in the fourth step by using a brush, repairing surface pores, then placing the semi-finished product into a secondary forming mold, locking the mold, placing the semi-finished product into an oven for baking, and cooling to obtain a finished product of the heat insulation cover.
Further, the size of the fine powder aluminum powder in the second step is more than or equal to 200 meshes.
Furthermore, the viscosity of the epoxy resin adhesive in the second step is 150,000-300,000cP, and the collapse degree is less than or equal to 0.3mm.
Further, in the fourth step, the molding temperature is 100-180 ℃, the pressure of a molding machine is 30-70T, and the molding time is 120-180 min.
Further, in the fifth step, the baking temperature is 140-180 ℃, and the baking time is 60-120 min.
And further, the finished product of the heat shield obtained in the fifth step has pores or surface defects, the fifth step can be repeated for repairing to obtain the finished product of the heat shield, and then the gluing surface of the product is coated with the mixture and then is put into a jig for adaptation and fixation.
Compared with the traditional aircraft engine heat shield, the thermal insulation effect is guaranteed, the thermal insulation intermediate layer is reduced, the auxiliary agent is added to modify the thermal insulation material, the oxidation resistance and the high temperature resistance of the aircraft engine heat shield are effectively improved, and the obtained aircraft engine heat shield is light in weight, good in thermal insulation and cold protection effects, wide in temperature resistance range, simple in preparation process and worthy of popularization.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a flow chart of the preparation process of the present invention.
Detailed Description
In order to further explain the technical scheme of the invention, the invention is explained in detail by the specific embodiment.
The invention discloses a formula of an aircraft engine heat shield, which comprises the following components in percentage by weight: 45-70 parts of silicone paint, 30-55 parts of diluent, 10-15 parts of epoxy resin adhesive and 5-10 parts of fine powder aluminum powder.
Referring to FIG. 1, a method of making an aircraft engine heat shield is also disclosed, comprising the steps of:
the method comprises the following steps: taking 45-70 parts of silicone paint and 30-55 parts of diluent, and stirring and mixing the raw materials in percentage by weight at the temperature of 10-35 ℃ at the stirring speed of 100-600 r/min to prepare a mixture A;
step two: taking 10-15 parts of epoxy resin adhesive and 5-10 parts of fine powder aluminum powder, stirring and mixing the raw materials in percentage by weight at the temperature of 10-35 ℃, and stirring at the speed of 20-50 r/min to prepare a mixture B; the fine powder aluminum powder is 200 meshes in specification; the viscosity of the epoxy resin adhesive is 150,000-300,000cP, and the collapse degree is less than or equal to 0.3mm;
step three: taking 80-85 parts of the mixture A obtained in the step one and 15-20 parts of the mixture B obtained in the step two, and stirring and mixing at the temperature of 10-35 ℃ at the stirring speed of 100-600 r/min to obtain a mixture C;
step four: spreading high silica cloth with the thickness of 0.5-0.75 mm in a cavity of a heat shield mould, uniformly coating the mixture C obtained in the step three on the upper surface and the lower surface of the high silica cloth by using a brush, and coating the mixture C with the thickness of 0.3mm; then closing the mold, and putting the mold into a hot-pressing table for molding; the molding temperature is 100-180 ℃, the pressure of a molding machine is 30-70T, and the molding time is 120-180 min; then cooling to below 60 ℃, opening the mold to obtain a shaped semi-finished product, and trimming;
step five: uniformly brushing the mixture C obtained in the third step on the upper surface and the lower surface of the semi-finished product obtained in the fourth step by using a brush, repairing surface pores, then placing the semi-finished product into a secondary forming die, locking the die, and placing the semi-finished product into an oven for baking at the baking temperature of 140-180 ℃ for 60-120 min; and cooling to obtain a finished product of the heat shield.
Furthermore, the epoxy resin adhesive in the second step is an aluminum-filled, thixotropic and single-component epoxy resin adhesive, has the advantage of high temperature resistance, has excellent tensile shear strength and impact resistance, can be used for bonding oily and other operation surfaces with poor pretreatment, and is suitable for bonding various materials.
And further, the finished product of the heat shield obtained in the fifth step has pores or surface defects, the fifth step can be repeated for repairing to obtain the finished product of the heat shield, and then the gluing surface of the product is coated with the mixture and then is put into a jig for adaptation and fixation.
In the above, if a weight part is 5g, the weight of each component is multiplied by the corresponding part by 5g, and the specific weight of each weight part is set according to actual needs.
In the fourth step, the surface of the mould is required to be cleaned, teflon cloth is attached according to the size of a mould cavity of the mould, and then the high silica cloth is properly enlarged by 100mm-150mm according to the flat laying size of a product; and then the molding process is carried out.
Example 1
A method of making an aircraft engine heat shield comprising the steps of:
the method comprises the following steps: taking 70 parts of silicone paint and 55 parts of diluent, and stirring and mixing the raw materials in percentage by weight at the temperature of 10-35 ℃ at the stirring speed of 600r/min to prepare a mixture A;
step two: taking 14 parts of epoxy resin adhesive and 10 parts of fine powder aluminum powder, and stirring and mixing the raw materials in percentage by weight at 25 ℃ at a stirring speed of 50r/min to prepare a mixture B; the fine powder aluminum powder is 200 meshes in specification; the viscosity of the epoxy resin adhesive is 150,000-300,000cP, and the collapse degree is less than or equal to 0.3mm;
step three: taking 80 parts of the mixture A obtained in the step one and 20 parts of the mixture B obtained in the step two, and stirring and mixing at the temperature of 20 ℃ at the stirring speed of 600r/min to obtain a mixture C;
step four: spreading high silica cloth with the thickness of 0.6mm in a cavity of a heat shield die, and uniformly coating the mixture C obtained in the step three on the upper surface and the lower surface of the high silica cloth by using a brush, wherein the coating thickness is 0.3mm; then closing the die and placing the die into a hot-pressing table for molding; the molding temperature is 150 ℃, the pressure of a molding machine is 70T, and the molding time is 180min; then cooling to below 60 ℃, opening the mold to obtain a shaped semi-finished product, and trimming;
step five: uniformly brushing the mixture C obtained in the third step on the upper surface and the lower surface of the semi-finished product obtained in the fourth step by using a brush, repairing surface pores, then placing the semi-finished product into a secondary forming mold, locking the mold, and placing the semi-finished product into an oven for baking at the baking temperature of 180 ℃ for 60min; and cooling to obtain a finished product of the heat shield.
Example 2
A method of making an aircraft engine heat shield comprising the steps of:
the method comprises the following steps: taking 45 parts of silicone paint and 36 parts of diluent, and stirring and mixing the raw materials in percentage by weight at 10 ℃ at a stirring speed of 100r/min to prepare a mixture A;
step two: taking 10 parts of epoxy resin adhesive and 5 parts of fine powder aluminum powder, stirring and mixing the raw materials in percentage by weight at 10 ℃ at a stirring speed of 20r/min to prepare a mixture B; the size of the fine powder aluminum powder is more than or equal to 200 meshes; the viscosity of the epoxy resin adhesive is 150,000-300,000cP, and the collapse degree is less than or equal to 0.3mm;
step three: taking 80 parts of the mixture A obtained in the step one and 15 parts of the mixture B obtained in the step two, and stirring and mixing at the temperature of 10 ℃ at the stirring speed of 100r/min to obtain a mixture C;
step four: spreading high silica cloth with the thickness of 0.5mm in a cavity of a heat shield die, and uniformly coating the mixture C obtained in the step three on the upper surface and the lower surface of the high silica cloth by using a brush, wherein the coating thickness is 0.2mm; then closing the mold, and putting the mold into a hot-pressing table for molding; the molding temperature is 120 ℃, the pressure of a molding machine is 30T, and the molding time is 120min; then cooling to below 60 ℃, opening the mold to obtain a shaped semi-finished product, and trimming;
step five: uniformly brushing the mixture C obtained in the third step on the upper surface and the lower surface of the semi-finished product obtained in the fourth step by using a brush, repairing surface pores, then placing the semi-finished product into a secondary forming mold, locking the mold, and placing the semi-finished product into an oven for baking at the baking temperature of 140 ℃ for 120min; and cooling to obtain a finished product of the heat shield.
Example 3
A method of making an aircraft engine heat shield comprising the steps of:
the method comprises the following steps: taking 60 parts of silicone paint and 48 parts of diluent, and stirring and mixing the raw materials in percentage by weight at 25 ℃ at a stirring speed of 300r/min to prepare a mixture A;
step two: taking 12 parts of epoxy resin adhesive and 8 parts of fine powder aluminum powder, stirring and mixing the raw materials in percentage by weight at 25 ℃, wherein the stirring speed is 30r/min, and preparing a mixture B; the size of the fine powder aluminum powder is more than or equal to 200 meshes; the viscosity of the epoxy resin adhesive is 150,000-300,000cP, and the collapse degree is less than or equal to 0.3mm;
step three: taking 85 parts of the mixture A obtained in the step one and 15 parts of the mixture B obtained in the step two, and stirring and mixing at the temperature of 25 ℃ at the stirring speed of 300r/min to obtain a mixture C;
step four: spreading high silica cloth with the thickness of 0.6mm in a cavity of a heat shield die, and uniformly coating the mixture C obtained in the step three on the upper surface and the lower surface of the high silica cloth by using a brush, wherein the coating thickness is 0.25mm; then closing the mold, and putting the mold into a hot-pressing table for molding; the molding temperature is 160 ℃, the pressure of a molding machine is 50T, and the molding time is 150min; then cooling to below 60 ℃, opening the mold to obtain a shaped semi-finished product, and trimming;
step five: uniformly brushing the mixture C obtained in the third step on the upper surface and the lower surface of the semi-finished product obtained in the fourth step by using a brush, repairing surface pores, then placing the semi-finished product into a secondary forming mold, locking the mold, and placing the semi-finished product into an oven for baking at the baking temperature of 160 ℃ for 80min; and cooling to obtain a finished product of the heat shield.
Example 4
The method comprises the following steps: taking 55 parts of silicone paint and 44 parts of diluent, and stirring and mixing the raw materials in percentage by weight at the temperature of 20 ℃ at the stirring speed of 600r/min to prepare a mixture A;
step two: taking 11 parts of epoxy resin adhesive and 10 parts of fine powder aluminum powder, and stirring and mixing the raw materials in percentage by weight at the temperature of 30 ℃, wherein the stirring speed is 50r/min, so as to prepare a mixture B; the size of the fine powder aluminum powder is more than or equal to 200 meshes; the viscosity of the epoxy resin adhesive is 150,000-300,000cP, and the collapse degree is less than or equal to 0.3mm;
step three: taking 85 parts of the mixture A obtained in the step one and 10 parts of the mixture B obtained in the step two, and stirring and mixing at the temperature of 30 ℃ at the stirring speed of 600r/min to obtain a mixture C;
step four: spreading high silica cloth with the thickness of 0.75mm in a cavity of a heat shield mould, and uniformly coating the mixture C obtained in the step three on the upper surface and the lower surface of the high silica cloth by using a brush, wherein the coating thickness is 0.3mm; then closing the mold, and putting the mold into a hot-pressing table for molding; the molding temperature is 180 ℃, the pressure of a molding machine is 70T, and the molding time is 120min; then cooling to below 60 ℃, opening the die to obtain a shaped semi-finished product, and trimming;
step five: uniformly brushing the mixture C obtained in the third step on the upper surface and the lower surface of the semi-finished product obtained in the fourth step by using a brush, repairing surface pores, then placing the semi-finished product into a secondary forming mold, locking the mold, and placing the semi-finished product into an oven for baking at the baking temperature of 180 ℃ for 60min; and cooling to obtain a finished product of the heat shield.
Example 5
A method of making an aircraft engine heat shield comprising the steps of:
the method comprises the following steps: taking 70 parts of silicone paint and 55 parts of diluent, and stirring and mixing the raw materials in percentage by weight at the temperature of 30 ℃ at the stirring speed of 600r/min to prepare a mixture A;
step two: taking 15 parts of epoxy resin adhesive and 6 parts of fine powder aluminum powder, stirring and mixing the raw materials in percentage by weight at the temperature of 30 ℃, and stirring at the speed of 40r/min to obtain a mixture B; the size of the fine powder aluminum powder is more than or equal to 200 meshes; the viscosity of the epoxy resin adhesive is 150,000-300,000cP, and the collapse degree is less than or equal to 0.3mm;
step three: and (4) taking 80 parts of the mixture A obtained in the step one and 20 parts of the mixture B obtained in the step two, and stirring and mixing at the temperature of 25 ℃ at the stirring speed of 200r/min to obtain a mixture C.
Step four: spreading high silica cloth with the thickness of 0.55mm in a cavity of a heat shield die, and uniformly spraying the mixture C obtained in the step three on the upper surface and the lower surface of the high silica cloth by using a spray gun, wherein the spraying thickness is 0.1mm; then closing the mold, and putting the mold into a hot-pressing table for molding; the molding temperature is 160 ℃, the pressure of a molding machine is 45T, and the molding time is 150min; cooling to below 60 ℃, opening the mold to obtain a shaped semi-finished product, and trimming;
step five: repeating the step four 1-2 times;
step six: uniformly spraying the mixture C obtained in the step three on the upper surface and the lower surface of the semi-finished product obtained in the step four by using a spray gun, repairing surface pores, then placing the semi-finished product into a secondary forming die, locking the die, and placing the semi-finished product into an oven for baking, wherein the baking temperature is 150 ℃, and the baking time is 70min; and cooling to obtain a finished product of the heat shield.
Example 6
A method of making an aircraft engine heat shield, comprising the steps of:
the method comprises the following steps: taking 65 parts of silicone paint and 52 parts of diluent, and stirring and mixing the raw materials in percentage by weight at 25 ℃ at a stirring speed of 400r/min to prepare a mixture A;
step two: taking 13 parts of epoxy resin adhesive and 9 parts of fine powder aluminum powder, stirring and mixing the raw materials in percentage by weight at 25 ℃, wherein the stirring speed is 50r/min, and preparing a mixture B; the size of the fine powder aluminum powder is more than or equal to 200 meshes; the viscosity of the epoxy resin adhesive is 150,000-300,000cP, and the collapse degree is less than or equal to 0.3mm;
step three: and taking 85 parts of the mixture A obtained in the step one and 20 parts of the mixture B obtained in the step two, and stirring and mixing at the stirring speed of 400r/min at the environment of 15 ℃ to obtain a mixture C.
Step four: spreading high silica cloth with the thickness of 0.65mm in a cavity of a heat shield die, and uniformly spraying the mixture C obtained in the step three on the upper surface and the lower surface of the high silica cloth by using a spray gun, wherein the spraying thickness is 0.2mm; then closing the die and placing the die into a hot-pressing table for molding; the molding temperature is 180 ℃, the pressure of a molding machine is 70T, and the molding time is 180min; cooling to below 60 ℃, opening the mold to obtain a shaped semi-finished product, and trimming;
step five: repeating the step four 1-2 times;
step six: uniformly spraying the mixture C obtained in the step three on the upper surface and the lower surface of the semi-finished product obtained in the step four by using a spray gun, repairing surface pores, then placing the semi-finished product into a secondary forming die, locking the die, and placing the semi-finished product into an oven for baking, wherein the baking temperature is 180 ℃, and the baking time is 120min; and cooling to obtain a finished product of the heat shield.
The working principle of the invention is as follows: the invention adopts high silica cloth and high temperature resistant single-component epoxy resin adhesive, improves the comprehensive performance of heat insulation materials by adding auxiliary agents, adopts modified heat insulation materials to prepare a mixture, spreads the high silica cloth in a heat insulation cover mould cavity, coats the mixture prepared by the heat insulation materials for compression molding, trims the mixture after cooling and shaping, and obtains the finished product of the heat insulation cover of the aircraft engine after secondary coating and baking of the mixture;
compared with the traditional aircraft engine heat shield, the heat-insulating effect is ensured, the heat-insulating intermediate layer is reduced, the heat-insulating material is modified by adding the auxiliary agent, the oxidation resistance and high-temperature resistance of the aircraft engine heat shield are effectively improved, and the obtained aircraft engine heat shield is light in weight, good in heat-insulating and cold-proof effects, wide in temperature-resistant range, simple in preparation process and worthy of popularization.
The above description is only for illustrating the technical solution of the present invention and not for limiting, and other modifications or equivalent substitutions made by the technical solution of the present invention by those of ordinary skill in the art should be covered within the scope of the claims of the present invention as long as they do not depart from the spirit and scope of the technical solution of the present invention.
Claims (8)
1. A formulation for an aircraft engine heat shield, characterized by: the formula comprises the following components in percentage by weight: 45-70 parts of silicone paint, 35-55 parts of diluent, 10-15 parts of epoxy resin adhesive and 5-10 parts of fine powder aluminum powder.
2. The formulation for an aircraft engine heat shield of claim 1, wherein: the epoxy resin adhesive is an aluminum-filled, thixotropic, single-component epoxy resin adhesive.
3. A method of making an aircraft engine heat shield, comprising: taking 45-70 parts of silicone paint and 35-55 parts of diluent, and stirring and mixing the raw materials in percentage by weight at the temperature of 10-35 ℃ at the stirring speed of 100-600 r/min to prepare a mixture A;
step two: taking 10-15 parts of epoxy resin adhesive and 5-10 parts of fine powder aluminum powder, stirring and mixing the raw materials in percentage by weight at the temperature of 10-35 ℃, and preparing a mixture B, wherein the stirring speed is 20-50 r/min;
step three: taking 80-85 parts of the mixture A obtained in the step one and 15-20 parts of the mixture B obtained in the step two, and stirring and mixing at the temperature of 10-35 ℃ at the stirring speed of 100-600 r/min to obtain a mixture C;
step four: spreading high silica cloth with the thickness of 0.5-0.75 mm in a cavity of a heat shield mould, uniformly coating the mixture C obtained in the step three on the upper surface and the lower surface of the high silica cloth by using a brush, and coating the mixture C with the thickness of 0.2-0.3 mm; then closing the mold, placing the mold into a hot pressing table for molding, cooling to below 60 ℃, opening the mold to obtain a molded semi-finished product, and performing trimming treatment;
step five: and (4) uniformly brushing the mixture C obtained in the third step on the upper surface and the lower surface of the semi-finished product obtained in the fourth step by using a brush, repairing surface pores, then placing the semi-finished product into a secondary forming mold, locking the mold, placing the semi-finished product into an oven for baking, and cooling to obtain a finished product of the heat insulation cover.
4. The method of making an aircraft engine heat shield of claim 3, wherein: and the size of the fine powder aluminum powder in the second step is more than or equal to 200 meshes.
5. The method of making an aircraft engine heat shield of claim 3, wherein: the viscosity of the epoxy resin adhesive in the second step is 150,000-300,000cP, and the collapse degree is less than or equal to 0.3mm.
6. The method of making an aircraft engine heat shield of claim 3, wherein: in the fourth step, the molding temperature is 100-180 ℃, the pressure of a molding machine is 30-70T, and the molding time is 120-180 min.
7. The method of making an aircraft engine heat shield of claim 3, wherein: in the fifth step, the baking temperature is 140-180 ℃, and the baking time is 60-120 min.
8. The method of making an aircraft engine heat shield of claim 3, wherein: and D, the finished product of the heat shield obtained in the fifth step has pores or surface defects, the fifth step can be repeated for repairing to obtain the finished product of the heat shield, and then the gluing surface of the product is coated with the mixture and then is put into a jig for adaptation and fixation.
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018045622A1 (en) * | 2016-09-09 | 2018-03-15 | 东南大学 | Micro powder-reinforced, polyurethane-based, high-strength, waterproof, thermal-insulation decorative integrated material and preparation method therefor |
| CN111253753A (en) * | 2020-03-24 | 2020-06-09 | 霍山汇能汽车零部件制造有限公司 | Heat-insulating composite material and application thereof to engine heat shield |
| CN111454018A (en) * | 2020-04-22 | 2020-07-28 | 黄河水利水电开发总公司监测维修分公司 | High-toughness wear-resistant epoxy resin polymer mortar and application method thereof |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018045622A1 (en) * | 2016-09-09 | 2018-03-15 | 东南大学 | Micro powder-reinforced, polyurethane-based, high-strength, waterproof, thermal-insulation decorative integrated material and preparation method therefor |
| CN111253753A (en) * | 2020-03-24 | 2020-06-09 | 霍山汇能汽车零部件制造有限公司 | Heat-insulating composite material and application thereof to engine heat shield |
| CN111454018A (en) * | 2020-04-22 | 2020-07-28 | 黄河水利水电开发总公司监测维修分公司 | High-toughness wear-resistant epoxy resin polymer mortar and application method thereof |
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