CN105130500A - Deformation control method in rigid heat-insulating tile coating forming process - Google Patents
Deformation control method in rigid heat-insulating tile coating forming process Download PDFInfo
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- CN105130500A CN105130500A CN201510535953.2A CN201510535953A CN105130500A CN 105130500 A CN105130500 A CN 105130500A CN 201510535953 A CN201510535953 A CN 201510535953A CN 105130500 A CN105130500 A CN 105130500A
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Abstract
The invention relates to a deformation control method in a rigid heat-insulating tile coating forming process, belongs to the technical field of a porous ceramic heat-insulating material, and can be used for preparing a heat shielding material of an aircraft such as a space shuttle and the like. The method comprises: applying coating slurry to the surface of a rigid heat-insulating tile ceramic base body which is initially processed to a certain thickness and shape; after drying, putting the coated base body material at a high temperature to be sintered for thermal treatment; after sintering for thermal treatment, taking out the base body material from the high-temperature environment and cooling the base body material to room temperature; and finally carrying out secondary processing to reduce the base body material to the finally required thickness. Compared to a conventional method which directly processes the base body material to the finally required thickness and then carries out coating forming, deformation of the rigid heat-insulating tile in the coating forming process can be effectively controlled.
Description
Technical field
The present invention relates to the deformation control method in a kind of rigidity thermal insulation tile coating moulding process, belong to porous ceramics lagging material technical field, can be used for the preparation of the aircraft thermally protective materials such as space shuttle.
Background technology
Aerospacecraft will stand serious Aerodynamic Heating when getting through the earth's atmosphere or fly in atmospheric layer, its surface temperature sharply raises, therefore thermally protective materials must be relied on internally to transmit with block heat, thus ensure that internal staff and equipment are within safety, reasonably temperature range.Such as, succeeding in developing of space shuttle just has benefited from the advanced thermally protective materials reliably such as carbon/carbon, rigidity thermal insulation tile and flexible heat insulation felt to a great extent.Wherein, rigidity thermal insulation tile is the important thermally protective materials being applied to the positions such as space shuttle windward side.With regard on its structure composition, it is formed primarily of the ceramic matrix material of high porosity and the high radiation coating on its surface.During military service, rigidity thermal insulation tile relies on the high radiation coating on its surface to be gone out by the heat radiation of more than 90%, and the excellent thermal insulation performance simultaneously by body material stops all the other heats internally to transmit.In addition, coating also has other functions such as waterproof and anti-airflow scouring concurrently.Therefore, high radiation coating is most important for rigidity thermal insulation tile.
Because rigidity thermal insulation tile is mainly used in the military fields such as space flight, therefore its technical information has certain confidentiality.From current disclosed data, in the publication mainly concentrating on the U.S. about the documents and materials report of rigidity thermal insulation tile coating abroad and technical report.Such as, the coating that disclosed in 1976, US Patent No. 3953646 " Two-componentceramiccoatingforsilicainsulation " describes is made up of barrier layer and radiating layer.Wherein, barrier layer, between body material and radiating layer, prevents from reacting between matrix and radiating layer, and regulate coating to mate with the heat between matrix, control the consumption of radiation coating, it is sintered by melten glass and forms at 927-1371 DEG C; Radiating layer has radiation and moisture-proof function concurrently, and it is by radiation agent, high silica glass and borosilicate glass (B
2o
3siO
2) sinter at 927-1371 DEG C equally and form.Similar with it, in another patent US3955034 " Three-componentceramiccoatingforsilicainsulation " disclosed in 1976, coating is made up of barrier layer, radiating layer and glaze layer, difference is not containing borosilicate glass in radiating layer, and glaze layer is then sintered by high silica glass and borosilicate glass and forms.With above-mentioned two patents unlike, coating only one deck disclosed in 1978 described in patent US4093771 " Reactioncuredglassandglasscoatng ", sinter at 1000-1400 DEG C the complex phase glass formed by frit, intermetallic or metallic compound (such as four silicon borides, silicon hexaboride, boron silicide, boron) etc. next time, thus avoid because layering repeatedly sinters the too much contraction and deformation effect caused body material, and the stability of coating is improved.Wherein, frit is prepared from by boron oxide and the higher borosilicate glass of silicone content, also by adding glass fusing assistant to reduce sintering temperature or to regulate the coefficient of expansion.By comparison, the coating described in patent US4381333 disclosed in nineteen eighty-three " Hightemperatureglassthermalcontrolstructureandcoating " is except using above-mentioned coating as except radiating layer, turn increase the scattering layer that one deck thermal expansivity is low compared with radiating layer on its surface, it is prepared from by thermally-stabilised higher frit (such as melten glass, pyrex that silicone content is higher).The coating ingredients described in patent US5079082 " Tougheneduni-piecefibrousinsulation " disclosed in 1992 is substantially identical with US4093771, increase only molybdenum disilicide radiation agent, and coating has immersed part of matrix material internal, bonding force between matrix is strengthened, and its waterproof and heat-shock resistance etc. obtain further improvement.Because above-mentioned coating is all that therefore maximum operation (service) temperature is limited between 1482-1538 DEG C using silicon oxide as main ingredient.In order to solve the problem, patent US20010051218A1, US6444271B2 and US6749942B1 " Durablerefractoryceramiccoating " disclosed in calendar year 2001,2002 and 2004 using the refractory metal (molybdenum, tantalum, niobium, vanadium, chromium, tungsten) of silicon and fusing point more than 1650 DEG C as main coating ingredients, under the high temperature of 982-1427 DEG C, sintering obtains silicide coating, and it is similar with US5079082, coating has also immersed part of matrix material internal, and the fusing point of coating and softening temperature reach 1949 DEG C and 1593-1649 DEG C respectively.Coating ingredients disclosed in 2010 described in patent US7767305B1 " Highefficiencytantalum-basedceramiccompositestructures " is mainly tantalum silicide, borosilicate glass, also molybdenum disilicide etc. can be added, sintering temperature is between 1220-1315 DEG C, and resistance to elevated temperatures reaches 1650 DEG C.
The domestic documents and materials about rigidity thermal insulation tile coating are then relatively less, only briefly touched upon component and the moulding technique of rigidity thermal insulation tile coating in Chinese patent CN101691138B " preparation method of heat insulation tile of shuttle ".Guo Jinhua is in its academic dissertation " the fabrication & properties optimization of thermal insulation tile surface high emission coating ", significant exploratory development has been carried out to thermal insulation tile coating, but its work mainly concentrates on the aspects such as coating ingredients proportioning and moulding process, the emittance of main concern coating and heat-shock resistance etc.Technical paper " the ceramic insulation watt surperficial SiO that Wu Yongbin etc. deliver
2-B
2o
3-MoSi
2-SiB
4the fabrication & properties research of coating " prepare thermal insulation tile coating, and the sign of fundamental property has been carried out to it.
Make a general survey of above-mentioned open source information can know, rigidity thermal insulation tile coating moulding process is similar, specifically be exactly: the ceramic matrix material first preparing rigidity thermal insulation tile, then also dry at its surface application coating paste, be finally placed in High Temperature Furnaces Heating Apparatus and obtain rigidity thermal insulation tile through high temperature sintering thermal treatment.It should be noted that, sintering temperature in rigidity thermal insulation tile coating preparation process is general all more than 1000 DEG C, such as, the clear and definite coating sintering temperature of patent US3953646, US3955034 is 927-1371 DEG C, patent US4093771 specifies that sintering temperature is between 1000-1400 DEG C, the sintering temperature of patent US20010051218A1, US6444271B2 and US6749942B1 coating is 982-1427 DEG C, and the sintering temperature of patent US7767305B1 is between 1220-1315 DEG C.
In general, rigidity thermal insulation tile there will be and shrinks and distortion in the high-temperature sintering process of coating, especially comparatively large for size and the ceramic matrix material that thickness is less, and situation is more serious.Such as patent US4093771 just mentions in its background technology, the high temperature sintering of more than 1260 DEG C that coating technology adopts before this can make body material produce distortion, and reduce by adding glass fusing assistant by sintering temperature in its technology described, and it is once sintered shaping, distortion and the contraction of matrix make moderate progress, but do not provide the data such as concrete size and deflection of exemplar.In addition, in disclosed patent and document, all do not mention the problem on deformation of rigidity thermal insulation tile in coating moulding process specially, the deformation control method of more not mentioned rigidity thermal insulation tile in coating moulding process.But, because the rigidity thermal insulation tile of distortion all can produce very large disadvantageous effect in the process procedures such as follow-up assembling and military service process, effective control method of its distortion therefore must be developed.
Summary of the invention
The technical problem that the present invention solves is: overcome the deficiencies in the prior art, deformation control method in a kind of rigidity thermal insulation tile coating moulding process is provided, the method technique is simple, body material is machined to final desired thickness carries out being coated with compared with the ordinary method of formable layer again with direct, after adopting the method, the distortion of rigidity thermal insulation tile in coating moulding process can be effectively controlled.
Technical scheme of the present invention is: the deformation control method in a kind of rigidity thermal insulation tile coating moulding process, described rigidity thermal insulation tile is rectangular parallelepiped or parallelepiped, comprises the steps:
(1) roughing is carried out to rigidity thermal insulation tile ceramic matrix material blank, its external form is made to be rectangular parallelepiped or parallelepiped, length after the roughing of rigidity thermal insulation tile ceramic matrix material blank and width are all between 100-500mm, thickness is not less than 20mm, and the large 5mm of at least more final desired thickness of thickness after roughing;
(2) coating paste that a surface application configures is selected in the surface that rigidity thermal insulation tile ceramic matrix material two areas after roughing are maximum, and dry;
(3) carry out sintering thermal treatment under the body material through step (2) coating being placed in high temperature, take out from hot environment after sintering thermal treatment and be cooled to room temperature;
(4) secondary processing is carried out to the surface of uncoated coating paste in the maximum surface of rigidity thermal insulation tile ceramic matrix material two areas, rigidity thermal insulation tile is thinned to final required thickness, realizes the Deformation control in rigidity thermal insulation tile coating moulding process.
In described step (2), if to the surface application coating beyond the maximum surface of two areas, be then 0-4/5 of final desired thickness in the coating dimension scale of thickness direction.
Described rigidity thermal insulation tile ceramic matrix material is by one or more in silica fiber, mullite fiber, sapphire whisker, silicic-boric acid aluminum fiber, Zirconium oxide fibre for starting material are prepared from, and the density of described rigidity thermal insulation tile ceramic matrix material is at 0.15-1.00g/cm
3between.
Carry out in described step (3) sintering heat treated implementation and be: surface maximum for the rigidity thermal insulation tile ceramic matrix material area of coating is carried out unilateral heating or the rigidity thermal insulation tile ceramic matrix material of coating is put into high-temperature burner hearth carrying out entirety heating at the stove gate of High Temperature Furnaces Heating Apparatus.
Carry out in described step (3) sintering heat treated temperature between 800-1400 DEG C, sintering heat treatment time is no less than 5min.
In described step (2), the application pattern of coating paste is for spraying or brush or spin coating, drying mode after having applied is seasoning or dry in an oven, and drying temperature is room temperature-150 DEG C, and after dry, the area density of coating paste is 0.01-0.25g/cm
2.
Described coating paste comprises solid ingredient and thinner, and the mass ratio of solid ingredient and thinner is 1:8-8:1; Wherein solid ingredient comprises borosilicate glass powder, radiation agent, sintering aid and stablizer, and thinner is the mixture of deionized water or dehydrated alcohol or deionized water and dehydrated alcohol.
The mass fraction of borosilicate glass powder in described solid ingredient, radiation agent, sintering aid and stablizer is: borosilicate glass powder: 10-90; Radiation agent: 0.5-20; Sintering aid: 0-50; Stablizer: 0-10, and the granularity of borosilicate glass powder, radiation agent, sintering aid and stablizer is all not less than 400 orders.
Compared with prior art, the present invention has following beneficial effect:
(1) the rigidity thermal insulation tile ceramic matrix material that the present invention first adopts thickness larger carries out painting formable layer, carry out secondary processing subsequently again and be thinned to final required thickness, the exemplar larger due to thickness is stronger for the thermal stresses opposing in high temperature sintering heat treatment process, therefore can control in less degree by the deformation preliminary of exemplar, after secondary processing, the distortion of exemplar is also controlled thus.Ceramic matrix material is machined to final desired thickness carries out being coated with compared with the ordinary method of formable layer with direct, the distortion in coating moulding process can be effectively controlled.
(2) one side maximum for the rigidity thermal insulation tile ceramic matrix material area of coating is carried out unilateral heating at the stove gate of High Temperature Furnaces Heating Apparatus by the present invention, the thermal stresses of rigidity thermal insulation tile ceramic matrix material in coating sintering process is reduced, thus distortion can be reduced further compared to integral sintered thermal treatment.
(3) the present invention by the length after the roughing of rigidity thermal insulation tile ceramic matrix material blank and width control system between 100-500mm, its deformation amount controlling can either be met the service requirementss such as assembling in less degree, can meet again generally for the use dimensional requirement of rigidity thermal insulation tile.
(4) if the present invention is to the surface application coating beyond the maximum surface of rigidity thermal insulation tile ceramic matrix material two areas, it is restricted to 0-4/5 of final desired thickness in the coating dimension scale of thickness direction, can effectively avoid secondary processing to the damage and fracture of molded coating, ensure that while controlling rigidity thermal insulation tile deflection rigidity thermal insulation tile shaping after quality.
(5) density of rigidity thermal insulation tile ceramic matrix material of the present invention is at 0.15-1.00g/cm
3between, Deformation control successful, is simultaneously unlikely to again to cause coating cracking, ensure that while controlling rigidity thermal insulation tile deflection rigidity thermal insulation tile shaping after quality.
(6) the present invention makes the area density of dry rear coating paste be 0.01-0.25g/cm by the component and coating number of times controlling coating paste
2, such area density is conducive to by the Deformation control of rigidity thermal insulation tile in rational degree, is unlikely to again that coat-thickness is too small to be difficult to meet performance requriements or thickness is excessive causes coating cracking etc. simultaneously.
Accompanying drawing explanation
Fig. 1 is the inventive method schema;
Fig. 2 is the schematic diagram after rigidity thermal insulation tile coating, and wherein, 1 is upper surface coating, and 2 is coating side;
Fig. 3 is the schematic diagram in rigidity thermal insulation tile unilateral heating sintering process, and wherein, 3 is High Temperature Furnaces Heating Apparatus, and 4 is rigidity thermal insulation tile;
Fig. 4 is the schematic diagram in the overall heat-agglomerating process of rigidity thermal insulation tile, and wherein, 3 is High Temperature Furnaces Heating Apparatus, and 4 is rigidity thermal insulation tile;
Fig. 5 is the distortion schematic diagram of rigidity thermal insulation tile;
Fig. 6 is rigidity thermal insulation tile deflection instrumentation plan.
Embodiment
The present invention proposes the deformation control method in a kind of rigidity thermal insulation tile coating moulding process, as shown in Figure 1, concrete steps are as follows:
1. rigidity thermal insulation tile ceramic matrix material blank processing
Adopt milling machine or grinding machine the roughing of rigidity thermal insulation tile ceramic matrix material blank to be become rectangular parallelepiped or the parallelepiped of rule, length and width are all between 100-500mm, and thickness is not less than 20mm.The large 5mm of at least more final desired thickness of thickness after the roughing of rigidity thermal insulation tile ceramic matrix material blank.Rigidity thermal insulation tile body material is the rigidity lagging material that main raw material(s) is prepared from by one or more fibers in silica fiber, mullite fiber, sapphire whisker, silicic-boric acid aluminum fiber, Zirconium oxide fibre.The density of rigidity thermal insulation tile ceramic matrix material is at 0.15-1.00g/cm
3between.This density makes Deformation control successful, is unlikely to again to cause coating cracking simultaneously.
2. coating paste coating and drying
Adopt the modes such as spraying, brushing or spin coating the coating paste configured to be coated on rigidity thermal insulation tile ceramic matrix surface, carry out seasoning subsequently or put into oven drying.Coating number of times is more than 1 time or 1 time.Wherein coating paste comprises solid ingredient and thinner, the mass ratio of solid ingredient and thinner is 1:8-8:1, solid ingredient comprises borosilicate glass powder, radiation agent, sintering aid and stablizer, and thinner is the mixture of deionized water or dehydrated alcohol or deionized water and dehydrated alcohol.
Coating paste collocation method is: utilize mechanical stirring or ball milling, and by borosilicate glass powder, radiation agent, sintering aid, stablizer and thinner mixing, mixing time is no less than 30min.Wherein the mass fraction of borosilicate glass powder, radiation agent, sintering aid and stablizer is: borosilicate glass powder: 10-90; Radiation agent: 0.5-20; Sintering aid: 0-50; Stablizer: 0-10.And the granularity of borosilicate glass powder, radiation agent, sintering aid and stablizer is all not less than 400 orders.Borosilicate glass powder is made up of silicon oxide, boron oxide, aluminum oxide and impurity, and mass percent is: silicon oxide 65-97%, boron oxide 2-30%, aluminum oxide 1-5%, and all the other are impurity.Radiation agent is molybdenum disilicide, silicon carbide, chromic oxide, nickel oxide, cobalt oxide, nickel chromium triangle spinel, silicon nitride, four silicon borides, silicon hexaboride, tantalum silicide, zirconium boride 99.5004323A8ure, the mixture of one or more in the sinter of iron, chromium, cobalt.Sintering aid is the mixture of one or more in norbide, boron nitride, boron oxide, four silicon borides, silicon hexaboride.Stablizer is clay or methylcellulose gum or both mixtures.
The surface of rigidity thermal insulation tile ceramic matrix material coating is between 1-5.If the upper and lower surface of the rigidity thermal insulation tile ceramic matrix material face that to be area maximum, side is the face that area is relatively little.As shown in Figure 2, the surface of rigidity thermal insulation tile ceramic matrix material coating has at least 1 face to be the maximum face (as upper surface) of area, and all the other are side.When the side coating of rigidity thermal insulation tile ceramic matrix material, the coating dimension scale of thickness direction be final desired thickness 0-4/5 between.1 be wherein upper surface coating in Fig. 2,2 is coating side.
The drying temperature of rigidity thermal insulation tile coating slurry is room temperature-150 DEG C.Time of drying is no less than 30min.After the drying of rigidity thermal insulation tile coating paste, density is 0.01-0.25g/cm
2.
3. coating sintering thermal treatment
By the rigidity thermal insulation tile upper surface of coating complete for drying in the face of the stove gate (as shown in Figure 3) of high temperature sintering furnace or entirety put into the high temperature sintering thermal treatment that high-temperature burner hearth (as shown in Figure 4) carries out certain hour, take out subsequently and naturally cool to room temperature.The heat treated temperature of high temperature sintering is between 800-1400 DEG C.High temperature sintering heat treatment time is no less than 5min.
4. the rigidity thermal insulation tile processing of molded coating
Adopt milling machine or the maximum surface (if at upper surface coating, then at lower surface) of the area of grinding machine to the rigidity thermal insulation tile uncoated coating of molded coating to carry out secondary processing and be thinned to final desired thickness.
The present invention also proposes a kind of deformation measurement metering method of rigidity thermal insulation tile, as shown in Figure 5 and Figure 6, vernier callipers 1 and 2 is utilized to test the deflection (see Fig. 5) in EG (length and width direction 1), FH (length and width direction 2), AC (diagonal 1) and BD (diagonal 2) direction respectively.Wherein, E, F, G, H are respectively the stupefied central point of AB, BC, CD and DA tetra-, and O is the central point of rigidity thermal insulation tile coat side.Be measured as example (see Fig. 6) with EG Direction distortion, vernier callipers 1 be placed in rigidity thermal insulation tile coat side, adopt vernier callipers 2 measure respectively E, O and G tri-place distance vernier callipers 1 upper end distance h
eE', h
oO' and h
gG', then the maximum deformation quantity (hereinafter referred to as " deflection ") in length and width direction 1 is h
oO'-(h
eE'+h
gG')/2.FH direction, AC direction, BD direction are identical with EG direction measurement method, obtain the maximum deformation quantity of length and width direction 2, diagonal 1, diagonal 2 respectively.The average maximum deformation quantity (hereinafter referred to as " average deformation amount ") of length and width direction and diagonal is the deflection mean value in its direction 1 and 2.Wherein the measuring accuracy of vernier callipers 1 and 2 is 0.02mm.
Measuring method of the present invention characterizes the deflection of product quantitatively.
Embodiment 1:
The thickness requirement of exemplar is 10mm, and high temperature sintering thermal treatment adopts integral sintered heat treatment mode.
Rigidity thermal insulation tile ceramic matrix material adopts the blend fiber of the oxidized fibre of 80% and the mullite fiber of 20% to be prepared from, and density is 0.33g/cm
3roughing becomes the exemplar of 200 × 200 × 20mm, in coating paste, the mass ratio of each component is: borosilicate glass powder: boron oxide: tantalum silicide: clay: water=60:30:8:2:500, adopt ball mill mixing 3h, through coating in the upper surface (upper and lower surface area is maximum) of body material and side, and side coating 6mm, the spraying also dry rear coat side density obtained is 0.025g/cm
2, in high-temperature burner hearth, 1150 DEG C are carried out integral sintered thermal treatment 15min, after being cooled to room temperature, adopt milling machine that the rigidity thermal insulation tile of molded coating is machined to thickness 10mm.Make six products according to the method described above, utilize deformation measurement metering method of the present invention, get six products and carry out deflection mensuration, and calculate the mean value of the average deformation amount of six product length and width directions and diagonal, be respectively 188 μm and 343 μm.By comparison, directly body material is machined to final desired thickness and carries out painting formable layer again, the mean value of the average deformation amount of six product length and width directions and diagonal is respectively 360 μm and 623 μm.
Embodiment 2:
The thickness requirement of exemplar is 15mm, and high temperature sintering thermal treatment adopts integral sintered heat treatment mode.
Rigidity thermal insulation tile ceramic matrix material adopts the blend fiber of the oxidized fibre of 80% and the mullite fiber of 20% to be prepared from, and density is 0.33g/cm
3be processed into the exemplar of 200 × 200 × 20mm, the mass ratio of each component in coating paste is: borosilicate glass powder: boron oxide: tantalum silicide: clay: water=60:30:8:2:500, adopt ball mill mixing 3h, through coating in the upper surface (upper and lower surface area is maximum) of body material and side, and side coating 10mm, the spraying also dry rear coat side density obtained is 0.025g/cm
2, in high-temperature burner hearth, 1150 DEG C are carried out integral sintered thermal treatment 15min, after being cooled to room temperature, adopt milling machine to be finally machined to thickness 15mm.Make six products according to the method described above, utilize deformation measurement metering method of the present invention, get six products and carry out deflection mensuration, and calculate the mean value of the average deformation amount of six product length and width directions and diagonal, be respectively 178 μm and 256 μm.By comparison, directly body material is machined to final desired thickness and carries out painting formable layer again, the mean value of the average deformation amount of six product length and width directions and diagonal is respectively 197 μm and 338 μm.
Embodiment 3:
The thickness requirement of exemplar is 10mm, and high temperature sintering thermal treatment adopts unilateral heating processing mode.
Rigidity thermal insulation tile ceramic matrix material adopts the blend fiber of the oxidized fibre of 80% and the mullite fiber of 20% to be prepared from, and density is 0.33g/cm
3be processed into the exemplar of 200 × 200 × 20mm, the mass ratio of each component in coating paste is: borosilicate glass powder: boron oxide: tantalum silicide: clay: water=60:30:8:2:500, adopt ball mill mixing 3h, through coating in the upper surface (upper and lower surface area is maximum) of body material and side, and side coating 6mm, the spraying also dry rear coat side density obtained is 0.025g/cm
2, by upper surface on High Temperature Furnaces Heating Apparatus doorway 1150 DEG C of sintering thermal treatment 15min, after being cooled to room temperature, adopt milling machine to be finally machined to thickness 10mm.Make six products according to the method described above, utilize deformation measurement metering method of the present invention, get six products and carry out deflection mensuration, and calculate the mean value of the average deformation amount of six product length and width directions and diagonal, be respectively 157 μm and 303 μm.By comparison, directly body material is machined to final desired thickness and carries out integral sintered heat-treating profiled coating again, the mean value of the average deformation amount of six product length and width directions and diagonal is respectively 360 μm and 623 μm.
As can be seen from above-described embodiment, adopt method of the present invention, ceramic matrix material is machined to final desired thickness carries out being coated with compared with the ordinary method of formable layer with direct, the distortion in coating moulding process can be effectively controlled.And can be found out by the contrast of embodiment 1 and 3, unilateral heating can reduce distortion further compared to integral sintered thermal treatment.
The unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.
Claims (8)
1. the deformation control method in rigidity thermal insulation tile coating moulding process, described rigidity thermal insulation tile is rectangular parallelepiped or parallelepiped, it is characterized in that comprising the steps:
(1) roughing is carried out to rigidity thermal insulation tile ceramic matrix material blank, its external form is made to be rectangular parallelepiped or parallelepiped, length after the roughing of rigidity thermal insulation tile ceramic matrix material blank and width are all between 100-500mm, thickness is not less than 20mm, and the large 5mm of at least more final desired thickness of thickness after roughing;
(2) coating paste that a surface application configures is selected in the surface that rigidity thermal insulation tile ceramic matrix material two areas after roughing are maximum, and dry;
(3) carry out sintering thermal treatment under the body material through step (2) coating being placed in high temperature, take out from hot environment after sintering thermal treatment and be cooled to room temperature;
(4) secondary processing is carried out to the surface of uncoated coating paste in the maximum surface of rigidity thermal insulation tile ceramic matrix material two areas, rigidity thermal insulation tile is thinned to final required thickness, realizes the Deformation control in rigidity thermal insulation tile coating moulding process.
2. the deformation control method in a kind of rigidity thermal insulation tile coating moulding process according to claim 1, it is characterized in that: in described step (2), if the surface application coating beyond the surface maximum to two areas, be then 0-4/5 of final desired thickness in the coating dimension scale of thickness direction.
3. the deformation control method in a kind of rigidity thermal insulation tile coating moulding process according to claim 1, it is characterized in that: described rigidity thermal insulation tile ceramic matrix material is by one or more in silica fiber, mullite fiber, sapphire whisker, silicic-boric acid aluminum fiber, Zirconium oxide fibre for starting material are prepared from, the density of described rigidity thermal insulation tile ceramic matrix material is at 0.15-1.00g/cm
3between.
4. the deformation control method in a kind of rigidity thermal insulation tile coating moulding process according to claim 1, is characterized in that: carry out in described step (3) sintering heat treated implementation and be: surface maximum for the rigidity thermal insulation tile ceramic matrix material area of coating is carried out unilateral heating or the rigidity thermal insulation tile ceramic matrix material of coating is put into high-temperature burner hearth carrying out entirety heating at the stove gate of High Temperature Furnaces Heating Apparatus.
5. the deformation control method in a kind of rigidity thermal insulation tile coating moulding process according to claim 1, it is characterized in that: carry out in described step (3) sintering heat treated temperature between 800-1400 DEG C, sintering heat treatment time is no less than 5min.
6. the deformation control method in a kind of rigidity thermal insulation tile coating moulding process according to claim 1, it is characterized in that: in described step (2), the application pattern of coating paste is for spraying or brush or spin coating, drying mode after having applied is seasoning or dry in an oven, drying temperature is room temperature-150 DEG C, and after dry, the area density of coating paste is 0.01-0.25g/cm
2.
7. the deformation control method in a kind of rigidity thermal insulation tile coating moulding process according to claim 6, it is characterized in that: described coating paste comprises solid ingredient and thinner, the mass ratio of solid ingredient and thinner is 1:8-8:1; Wherein solid ingredient comprises borosilicate glass powder, radiation agent, sintering aid and stablizer, and thinner is the mixture of deionized water or dehydrated alcohol or deionized water and dehydrated alcohol.
8. the deformation control method in a kind of rigidity thermal insulation tile coating moulding process according to claim 7, is characterized in that: the mass fraction of borosilicate glass powder in described solid ingredient, radiation agent, sintering aid and stablizer is: borosilicate glass powder: 10-90; Radiation agent: 0.5-20; Sintering aid: 0-50; Stablizer: 0-10, and the granularity of borosilicate glass powder, radiation agent, sintering aid and stablizer is all not less than 400 orders.
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| CN107266086A (en) * | 2017-06-13 | 2017-10-20 | 长兴华悦耐火材料厂 | A kind of steel fiber refractories |
| CN107500789A (en) * | 2017-08-24 | 2017-12-22 | 浙江科屹耐火材料有限公司 | A kind of mullite pouring material and preparation method thereof |
| CN107603286A (en) * | 2017-09-11 | 2018-01-19 | 山东工业陶瓷研究设计院有限公司 | Rigid thermal insulation tile coating of unburned 1500 DEG C of heatproof and preparation method thereof |
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| CN114517022A (en) * | 2022-01-27 | 2022-05-20 | 上海联净电子科技有限公司 | Wear-resistant anti-adhesion coating and preparation method and application thereof |
| CN116444297A (en) * | 2023-06-12 | 2023-07-18 | 烟台奥森制动材料有限公司 | Refining process of silicon-carbon composite brake disc |
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| CN106083115A (en) * | 2016-06-12 | 2016-11-09 | 山东工业陶瓷研究设计院有限公司 | Thermal insulation tile coating of resistance to 1500 DEG C of high temperature and preparation method thereof |
| CN106083115B (en) * | 2016-06-12 | 2019-07-02 | 山东工业陶瓷研究设计院有限公司 | The thermal insulation tile coating and preparation method thereof of resistance to 1500 DEG C of high temperature |
| CN108383391A (en) * | 2016-09-14 | 2018-08-10 | 航天特种材料及工艺技术研究所 | The alumina fibre rigidity thermal insulation tile multilayer materials of surface toughening, coating composition, preparation method and applications |
| CN108455978A (en) * | 2016-09-14 | 2018-08-28 | 航天特种材料及工艺技术研究所 | The alumina fibre rigidity thermal insulation tile multilayer materials of surface toughening, coating composition, preparation method and applications |
| CN108455978B (en) * | 2016-09-14 | 2021-01-22 | 航天特种材料及工艺技术研究所 | Surface-toughened alumina fiber rigid heat-insulating tile multilayer composite material, coating composition, preparation method and application thereof |
| CN107266086A (en) * | 2017-06-13 | 2017-10-20 | 长兴华悦耐火材料厂 | A kind of steel fiber refractories |
| CN107500789A (en) * | 2017-08-24 | 2017-12-22 | 浙江科屹耐火材料有限公司 | A kind of mullite pouring material and preparation method thereof |
| CN107603286A (en) * | 2017-09-11 | 2018-01-19 | 山东工业陶瓷研究设计院有限公司 | Rigid thermal insulation tile coating of unburned 1500 DEG C of heatproof and preparation method thereof |
| CN107603286B (en) * | 2017-09-11 | 2019-08-09 | 山东工业陶瓷研究设计院有限公司 | Rigid thermal insulation tile coating of 1500 DEG C of unburned heatproof and preparation method thereof |
| CN114517022A (en) * | 2022-01-27 | 2022-05-20 | 上海联净电子科技有限公司 | Wear-resistant anti-adhesion coating and preparation method and application thereof |
| CN116444297A (en) * | 2023-06-12 | 2023-07-18 | 烟台奥森制动材料有限公司 | Refining process of silicon-carbon composite brake disc |
| CN116444297B (en) * | 2023-06-12 | 2023-08-25 | 烟台奥森制动材料有限公司 | Refining Process of Silicon-Carbon Composite Brake Disc |
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