243 results about "Thermal barrier coating" patented technology

The invention discloses a double-probe film thickness and defect collaborative decoupling method. The method comprises the steps that microwave reflection signals of a thermal barrier coating are synchronously collected through a coaxial resonance probe and a CSRR resonance ring probe; the microwave reflection signal comprises reflection coefficient amplitude, reflection coefficient phase and resonant frequency; constructing a frequency deviation model based on the microwave reflection signal; training the dual-channel deep learning network based on the frequency deviation model to obtain a trained dual-channel deep learning network; and obtaining film thickness information and a defect positioning result based on the trained dual-channel deep learning network. According to the method, collaborative decoupling of the film thickness and the defect signal is achieved through a physical-data fusion method, effective decoupling and independent recognition of the coating film thickness change and the defect response signal are achieved, and the resolution ratio, the accuracy rate and the practicability of a detection system are improved.

The invention relates to the field of suspension plasma spraying, in particular to a long-service-life suspension plasma spraying thermal barrier coating based on a platinum-aluminum coating and a preparation method of the long-service-life suspension plasma spraying thermal barrier coating. The preparation method comprises the following steps: preparing a vertical crack or columnar-like structure ceramic layer on the surface of a platinum modified aluminide bonding layer with lower roughness by using suspension slurry prepared from fully-stable tetragonal phase yttrium oxide stabilized zirconium oxide powder and adopting suspension plasma spraying suspension, so as to obtain a thermal barrier coating system with long service life. The problems that in the prior art, due to stress existing between a ceramic layer prepared through plasma spraying and a low-roughness platinum modified aluminide bonding layer, cracks are continuously formed and expanded at an interface, and the service life of a thermal barrier coating system is short are solved. The long-life thermal barrier coating system can be prepared on the platinum modified aluminide bonding layer through suspension plasma spraying.

The invention discloses a double-ceramic-layer thermal barrier coating of a differentiated columnar crystal structure and a preparation method, and belongs to the technical field of thermal barrier coating corrosion and protection. The invention innovatively discovers and utilizes the double influence of the columnar crystal size on the performance of the coating; the YSZ layer adopts a fine grain structure of 1-1.5 microns, so that the bonding strength and thermal shock resistance of the coating can be obviously improved; and the modified gadolinium zirconate layer adopts a 2-3 [mu] m coarse grain structure, so that the heat conductivity can be reduced, the permeation path of CMAS along a grain boundary can be effectively inhibited, and meanwhile, the modified gadolinium zirconate layer reacts with CMAS to form a compact barrier layer to prevent further permeation of CMAS. Through accurate regulation and control of electron beam physical vapor deposition (EB-PVD) process parameters, differential control of the sizes of the two layers of ceramic columnar crystals is realized, and under the synergistic effect of the two columnar crystal structures with different sizes, the thermal cycle life and CMAS corrosion resistance of the whole coating system in an ultra-high-temperature environment are remarkably prolonged and improved.

The invention relates to the technical field of thermal barrier coatings, in particular to a gadolinium oxide and aluminum oxide co-doped modified YSZ: Dy thermal barrier sensing coating material as well as a preparation method and application thereof. The invention provides a thermal barrier sensing coating material. The chemical composition of the thermal barrier sensing coating material is Y Gd Al < c > Zr < d > DeyOf, wherein a is equal to 0.01 to 0.04, b is equal to 0.15 to 0.35, c is equal to 0.40 to 0.60, d is equal to 0.35 to 0.70, e is equal to 0.01 to 0.02, and f is equal to 1.50 to 1.70. The temperature measurement upper limit of the thermal barrier sensing coating material is 1200 DEG C, and the average thermal expansion coefficient is increased by 18% at the room temperature of 1200 DEG C, so that the thermal shock resistance of the thermal barrier sensing coating is effectively improved, and the service life of the thermal barrier sensing coating is prolonged.

The application belongs to the field of turbine blade thermal barrier coating of an aero-engine. Specifically, it is a structure design, a preparation method and a prepared coating of a double-layer radiation-resistant thermal barrier coating with a high-reflection layer and a high-absorption layer. The coating comprises a high-absorption layer and a high-reflection layer. The high-absorption layer can absorb part of the energy of photon radiation and re-emit it into the environment, while relying on a cooling gas film to quickly remove heat. Part of the energy of the photon radiation is reflected by the high-reflection layer again to the high-absorption layer after passing through the high-absorption layer, and the process of absorption-emission-cooling gas film heat dissipation is repeated. Within a set temperature range, the absorption rate of the high-absorption layer is determined based on the temperature difference requirement between the inner and outer surfaces of the thermal barrier coating, and the high-absorption layer material is determined based on the absorption rate. The application greatly reduces the radiation heat flow penetrating the coating, avoids the direct heating of the high-temperature alloy by infrared radiation, and significantly improves the heat insulation capacity of the thermal barrier coating and the service life of the turbine blade.

The application provides a heat insulation performance testing device for thermal barrier coating, which comprises a hollow cavity with a through mold loading groove, a cylindrical graphite mold placed in the mold loading groove, and a temperature rising device and a first temperature measuring device which are opposite to each other and face one end surface of the cylindrical graphite mold; wherein one end surface of the cylindrical graphite mold is sprayed with a thermal barrier coating to be measured, and the side surface of the cylindrical graphite mold is sprayed with a heat insulation coating. The heat insulation condition of the heat insulation performance testing device for thermal barrier coating is set by spraying the heat insulation coating on the side surface of the graphite mold, and the heat insulation condition is set ingeniously so that the device can meet the Fourier heat transfer law under one-dimensional condition as much as possible, unnecessary heat escape is avoided, the heat flow on the coating surface completely realizes conduction to the back of the substrate, and thus, the measurement error caused by neglecting is avoided, and the result is accurate and reliable.

The invention relates to a combustion system, an engine and a vehicle. The combustion system comprises an air inlet channel, an exhaust channel, an air inlet valve, an exhaust valve, a cylinder cover, a cylinder sleeve and a piston, a cylinder cover combustion chamber is arranged in the combustion system, and at least one of the inner surface of the cylinder cover combustion chamber, the surface, facing the interior of the combustion system, of the air inlet valve, the surface, facing the interior of the combustion system, of the exhaust valve and the top surface of the piston is provided with a thermal barrier coating.

The invention discloses a high-entropy ceramic thermal barrier coating and a preparation method thereof, and relates to the technical field of thermal barrier coating materials. The method comprises the following steps: mixing ZrO2, HfO2, Ta2O5 and various rare earth oxides, and carrying out high-energy wet ball milling, drying, solid solution sintering and crushing to prepare submicron high-entropy ceramic powder; mixing the modified powder with aluminum sol obtained by hydrolyzing aluminum isopropoxide, rare earth nitrate and the like, dispersing, drying and carrying out heat treatment to obtain modified powder coated with aluminum oxide nanoparticles on the surface; carrying out spray drying granulation to obtain spherical agglomerated powder; and finally, a DD6 single-crystal high-temperature alloy matrix is subjected to sand blasting and pre-oxidation treatment, agglomerated powder is deposited on the surface of the matrix through a plasma spraying vapor deposition technology, a columnar crystal coating is formed, and a finished product is obtained through vacuum annealing. The coating prepared through the method is uniform in structure and high in bonding strength, thermal shock resistance and high-temperature phase stability are remarkably improved, and the coating is suitable for surface protection of aero-engine hot end components.

A spark plug for a spark ignited reciprocating internal combustion engine includes a mounting portion and an ignition portion. One or more surfaces of the ignition portion are at least partially coated with a thermal barrier coating.

The application relates to a dual-phase high-entropy ceramic material for high-temperature thermal barrier coatings and a preparation method thereof, in particular to a dual-phase high-entropy ceramic (La 0.2 Nd 0.2 Gd 0.2 Y 0.2 Ho 0.2 )2Zr2O7 with low thermal conductivity and high thermal expansion coefficient, which is mainly used for thermal isolation, thermal barrier coatings and other applications in high-temperature environments. The application is prepared by adopting a solid-phase reaction sintering process through accurate design of the combination of rare earth elements, forms a stable dual-phase structure, effectively inhibits grain growth through grain boundary pinning, and thus maintains a nanoscale grain structure. Meanwhile, the material can efficiently block heat transfer at high temperatures through optimization of phase proportion, and the thermal expansion characteristics are matched with a metal base layer, effectively avoiding the falling risk caused by the difference in thermal expansion of the two, and thus greatly improving the service life and reliability of the material in a high-temperature environment. The high-entropy ceramic material of the application can be widely applied to fields with high demand for high-temperature thermal isolation in aerospace, aviation, automobile industry and the like, is especially suitable for thermal barrier coatings, high-temperature thermal insulation materials and other high-temperature thermal insulation applications, and has important engineering application value.

The present disclosure provides a ceramic material for a thermal barrier coating and a manufacturing method thereof. A chemical composition of the ceramic material is LaYbZrCeO7. The ceramic material is manufactured by doping LaO1.5, YbO1.5 and CeO2 into ZrO2. A mole ratio of LaO1.5, YbO1.5, CeO2 and ZrO2 is 1:1:1:1. The manufactured ceramic material is in a composite phase structure mainly including a pyrochlore phase and a fluorite phase. The ceramic material according to the present disclosure can effectively inhibit corrosion penetration of molten CMAS in a high temperature environment, which reduces or avoids ceramic cracking and peeling. This better maintains microstructural integrity of the ceramic surface, thereby extending service life of ceramics.

A silicone-acrylic adhesive is made from a combination of I) a first aqueous emulsion containing a soft acrylic polymer, II) a second aqueous emulsion containing a hard acrylic polymer, and III) an aqueous emulsion of a silicone resin. The silicone-acrylic binders can be used to prepare thermal insulation coating compositions that can be applied to metal (e.g., steel) substrates or primed substrates. A thermal barrier coating prepared by drying the thermal barrier coating composition provides corrosion resistance under thermal barrier to a metal or primed substrate.

The invention discloses a preparation method of a composite heat insulation baffle for a single crystal furnace. The preparation method comprises the following steps: preparing heat insulation slurry; carrying out compression molding on the heat insulation slurry to form a composite heat insulation baffle pre-blank, and carrying out heating foaming treatment on the composite heat insulation baffle pre-blank to obtain a composite heat insulation baffle pre-body; introducing the reinforcing phase into pores in the composite thermal baffle preform, and drying the composite thermal baffle preform; carrying out carbonization treatment and graphitization treatment on the dried composite heat insulation baffle plate preform; and coating a thermal barrier coating on the outer surface of the carbonized and graphitized composite thermal baffle preform to prepare the composite thermal baffle for the single crystal furnace. According to the composite heat insulation baffle, the low-density porous graphite matrix is used as a main material, the carbon fiber reinforced phase is used as an auxiliary material, the YSZ thermal barrier coating is coated outside the composite heat insulation baffle, the low heat conductivity coefficient and high mechanical stability are achieved by optimizing the pore structure and fiber distribution, and the erosion resistance, oxidation resistance and thermal shock resistance are improved through the surface coating.

The invention relates to the field of data management, in particular to a BRM business rule automatic reasoning method based on a knowledge graph. Comprising the following steps: obtaining a resource description framework triple based on a heterogeneous time series data stream containing a blade CNC machining log and thermal barrier coating process parameters, loading the triple into a graph database, and constructing a manufacturing knowledge graph data model; extracting historical time sequence data, and initializing a completely undirected graph; based on the process mechanism model and condition independence test, determining a data dependence path, and outputting a directed acyclic graph; performing analysis through intervention calculation, and calculating an average causal effect value; forming a causal knowledge graph by taking the average causal effect value as an attribute and the data dependence path as a relationship; and querying thermal spraying parameter nodes with average causal effect values exceeding a threshold value in the causal knowledge graph, and converting the thermal spraying parameter nodes into storage strategy rules. According to the method, the causal knowledge graph is converted into the storage strategy rule, so that automatic and closed-loop management from data acquisition to rule optimization is realized.

The invention relates to the field of high-temperature thermal resistance coatings, in particular to a material selection and preparation process of a low-infrared-transmittance coating, and particularly relates to a preparation method of a high-scattering-rate high-temperature thermal resistance coating, a base material of the high-scattering-rate high-temperature thermal resistance coating is Gd2Zr2O7, and the high-scattering-rate high-temperature thermal resistance coating further comprises a second-phase material; firstly, a required second-phase material is screened on the basis of machine learning in combination with experiments and a first principle, then a PS-PVD gas phase-solid phase codeposition method is adopted, the high-scattering-rate high-temperature thermal resistance coating is prepared, according to the obtained coating, a high-refractive-index-low-refractive-index interface between GdFeO3 particles and Gd2Zr2O7 gas phase columnar crystals can effectively increase scattering of infrared radiation, and the heat resistance of the coating is improved. And the vapor phase and solid phase co-deposited columnar crystals have uniform thermal physical properties, so that excellent coating binding force and excellent anti-sintering performance are provided.

The present disclosure provides a thermal barrier coating powder and a preparation method thereof, and a thermal barrier coating, and relates to the technical field of high-temperature protective coating materials. The method comprises: performing mechanical-chemical grinding and surface hydroxylation treatment on a MAX phase powder; dispersing an activated MAX phase core in a liquid phase, uniformly coating a YSZ precursor on the surface of the core through double titration co-precipitation to obtain a core-shell structure precursor slurry; performing microwave hydrothermal treatment to in-situ crystallize the YSZ precursor to form a YSZ shell layer on the surface of the MAX phase core, thereby obtaining a core-shell structure unit; the core-shell structure unit has a core-shell structure composed of a MAX phase core and a YSZ shell; performing post-treatment and spray drying on the core-shell structure unit to obtain a thermal barrier coating powder; and the powder is obtained by agglomeration of multiple core-shell structure units. The interface between the core and the shell of the powder obtained by the method is firmly combined, can provide oxidation protection for the inner core of the MAX phase in coating preparation processes such as thermal spraying, and significantly improves the fracture toughness and thermal shock resistance of the thermal barrier coating.

The utility model discloses a split mounting type glass structure with a heat insulation coating, which relates to the technical field of glass structures and comprises a glass body, the heat insulation coating is arranged on the surface of the glass body, a frame is arranged on the periphery of the glass body, the glass body is fixed on the inner side of the frame, and split mounting holes are arranged on the peripheral walls of the frame. The adjacent frame bodies are connected through an assembling block, the two ends of the assembling block are inserted into the assembling holes in the two frame bodies respectively, two clamping grooves are formed in the assembling block, and clamping mechanisms are arranged in the assembling holes. The heat insulation and light transmission performance of the glass can be guaranteed, meanwhile, splicing is very convenient, and mutual connection and installation are very convenient.

This invention relates to the field of coating preparation technology and discloses a heat-insulating coating comprising: 15-35 parts of rosin-based derivative, 10-25 parts of auxiliary heat-insulating filler, 8-18 parts of film-forming agent, 1-5 parts of dispersant, 0.5-3 parts of wetting agent, 0.3-2 parts of defoamer, 0.2-2 parts of thickener, 1-4 parts of film-forming aid, and 20-45 parts of deionized water. This invention improves the compatibility of the auxiliary heat-insulating filler through rosin-based maleic anhydride-aminosilane derivative, and forms a three-dimensional cross-linked network through the hydrolysis and condensation of aminosilane, reducing heat loss channels and achieving synergistic heat insulation. The modified derivative has a heat resistance temperature of over 250℃, and the siloxane structure delays aging, ensuring long-term heat insulation performance, thus solving the problems of poor compatibility, insufficient heat resistance, and easy attenuation of heat insulation in existing coatings.

The invention discloses a theoretical prediction method for the heat insulation effect of a thermal barrier coating of a high-speed rotating turbine blade. The method comprises the following steps: step 1, carrying out temperature testing on a turbine blade with a thermal barrier coating and a turbine blade without a coating under the same static service condition; 2, establishing a numerical calculation method for the thermal insulation effect of the thermal barrier coating of the static turbine blade, and obtaining a high-speed rotation correction factor; step 3, establishing heat insulation effect influence factor association based on the static-high-speed rotating turbine blade thermal barrier coating, and obtaining a convective heat transfer total temperature and a convective heat transfer coefficient of the turbine blade thermal barrier coating under high-speed rotation; and 4, establishing a model for evaluating the thermal insulation effect of the thermal barrier coating of the turbine blade under high-speed rotation by fusing static reference data and high-speed rotation working condition correction, and predicting the thermal insulation effect of the thermal barrier coating under high-speed rotation by using a static turbine blade experimental reference. According to the invention, static experiment data can be combined, high-speed rotation influence factors are incorporated, and the heat insulation effect in a high-speed rotation state can be efficiently obtained.

The invention discloses a thermal barrier coating temperature and thickness coupling measurement method, system and device and a storage medium, and relates to the technical field of aeronautical material testing. The method comprises the following steps: calibrating a mapping relation among parameters: preparing a series of standard samples with different thicknesses, collecting phosphorescence spectrums of the samples with the standard thicknesses at different temperatures, and calibrating the mapping relation among the parameters; the phosphorescence spectrum of the to-be-detected sample is collected, the phosphorescence intensity ratio of 457 nm to 483 nm is calculated, and the phosphorescence intensity of 586 nm is read; calculating the temperature of the to-be-measured sample: calculating the temperature of the to-be-measured sample according to the measured phosphorescence intensity ratio and the intensity ratio-temperature mapping relation; and calculating the thickness of the to-be-measured sample: determining a change curve of the phosphorescence intensity along with the thickness according to the calculated temperature of the to-be-measured sample, and calculating the thickness of the phosphorescence coating in combination with the measured phosphorescence intensity. The method and the system can realize non-contact synchronous online measurement of the temperature and the thickness of the thermal barrier coating.

The invention relates to an argon arc welding seam welding method for a lock bottom butt joint with a thermal barrier coating. The argon arc welding seam welding method comprises the following steps that S1, a welding seam joint is machined, specifically, a first groove is machined in a lock bottom at the mounting edge of the inner wall of a large bent pipe to be welded, a truncated edge is reserved, a second groove is machined in the mounting edge of the outer wall of the large bent pipe, and a truncated edge is reserved; the inner wall of the large elbow pipe and the outer wall of the large elbow pipe are combined, the lock bottom of the inner wall of the large elbow pipe is aligned with the mounting edge of the outer wall of the large elbow pipe, and the gap of the to-be-welded position is smaller than or equal to a first threshold value; s2, first-layer backing welding is carried out, during welding, welding wires are not filled, the truncated edge is directly penetrated in a penetration mode, and the step S3 is carried out after cooling; and S3, second-layer cosmetic welding is conducted, the first groove and the second groove are filled with welding wires, and then welding is conducted. According to the method, the welding quality can be guaranteed, heat input during welding can be obviously reduced, the coating is effectively prevented from falling off, and therefore the service life of the aero-engine large elbow is prolonged.

The application discloses a preparation method of super-high-entropy complex oxide powder material for thermal barrier coating and application thereof, and comprises the following steps: S1, uniformly dispersing a rare earth element source and a transition metal element source in deionized water, stirring and treating at 80 DEG C, then adding a complexing agent and a dispersing agent to obtain a mixture A; S2, adjusting the pH of the mixture A system to 4-5 by using ammonia water under stirring at 80 DEG C, continuously stirring and treating to form a gel, and drying to obtain a dry gel; S3, sintering the dry gel at 1400 DEG C for 2h to obtain the super-high-entropy complex oxide powder material. The application makes up the shortcomings of traditional thermal barrier coating YSZ material, can still maintain phase stability near 1500 DEG C, widens the thermal barrier coating material system to the super-high-entropy complex ceramic field, and the material has the characteristics of uniform element distribution, small and uniform powder particle size, high purity and the like, and the method has low requirement on equipment and is simple in synthesis method.

The invention relates to the technical field of thermal barrier coating materials, in particular to an unequal-ratio Ce doped pyrochlore and fluorite double-phase high-entropy rare earth zirconate thermal barrier coating material and a preparation method thereof. The chemical composition formula of the thermal barrier coating material provided by the invention is (La < 0.2 > Ce < 0.1 > Sm < 0.1 > Dy < 0.2 > Yb < 0.2 > Sc < 0.2 >) < 2 > Zr < 2 > O < 7 >, (La < 0.2 > Sm < 0.2 > Yb < 0.2 > Sc < 0.2 > Y < 0.1 > Ce < 0.1 >) < 2 > Zr < 2 > O < 7 >, and (La < 0.2 > Ce < 0.1 > Nd < 0.1 > Yb < 0.2 > Lu < 0.2 > Sc < 0.2 >) < 2 > Zr < 2 > O < 7 >. The thermal expansion performance of the prepared coating material is obviously improved under the conditions that the low thermal conductivity, the high mechanical property and the high sintering resistance are met at the same time, and therefore the high-entropy rare earth zirconate thermal barrier coating material of the Ce-containing double-phase structure is promoted, and it is guaranteed that the material is practically applied to the field of thermal barrier coating materials.

The invention relates to the technical field of tantalate thermal barrier coatings, in particular to a construction method and application of a rare earth tantalate material multi-performance prediction model, and the construction method comprises the following steps: collecting Young modulus, shear modulus, thermal expansion coefficient and thermal conductivity data of a rare earth tantalate material; an initial feature set is constructed based on material component features, and redundant features are deleted by using a Pearson correlation analysis method to reduce the complexity of the model. And modeling and evaluating various machine learning models. And on the basis of each performance optimal model, SFFS sequence floating forward feature subset screening is carried out. And finally, integrating the optimal feature set of each performance, and constructing a multi-performance integrated prediction model of the rare earth tantalate material. According to the method, the high-precision component-multi-performance mapping model can be constructed, the Young modulus, the shear modulus, the thermal expansion coefficient and the thermal conductivity of the rare earth tantalate material can be quickly and accurately predicted, the consumption of experiment resources is reduced, and the experiment progress is accelerated.

The application discloses a kind of multi-element rare earth zirconia materials resistant to molten sand dust erosion and a preparation method thereof, and belongs to the technical field of thermal barrier coating materials of aero-engine.The material is ZrO 2、 The main rare earth oxide Y2O3, the auxiliary rare earth oxide A2O3 and B2O3 are used as base raw materials, precisely proportioned, ball-milled and mixed, and a multi-element rare earth zirconia material is synthesized by a high-temperature solid-phase reaction method.The material exhibits the structural characteristics of a defect fluorite phase, is prepared into a dense ceramic block by dry pressing and high-temperature sintering, and has excellent performance, low thermal conductivity and high-temperature stability after its resistance to molten sand dust corrosion is investigated.The material of the application is suitable for application to thermal barrier coating materials of hot-end components of an aero-engine, significantly improves the resistance to high-temperature molten sand dust corrosion and service life of the components.The application solves the technical problems of high thermal conductivity, insufficient resistance to molten sand dust erosion and poor thermal stability of thermal barrier coating materials.

The application provides a turbine blade thermal barrier coating force-thermal coupling reliability evaluation method, which comprises the following steps: measuring and constructing a density distribution function of a thermal barrier coating microstructure and thermodynamic parameters, completing macroscopic complex turbine blade thermal barrier coating temperature field and strain field simulation, constructing a Monte Carlo sample space of random parameters at different positions of the blade, establishing a micro-scale force-thermal coupling finite element model and obtaining a life data set, building and training a deep learning agent model, and completing turbine blade thermal barrier coating reliability evaluation and sensitivity analysis. The reliability evaluation method provided by the application comprehensively considers the influence of the thermal barrier coating microstructure factor and the force-thermal coupling failure mechanism, solves the problems of high dimension, high nonlinear calculation cost and the like in the reliability evaluation of the complex blade thermal barrier coating, improves the accuracy and efficiency of the reliability evaluation, and provides an evaluation means for the safe application and optimized design of the thermal barrier coating.

The invention discloses a thermal barrier coating temperature and stress coupling test system and method, and belongs to the technical field of temperature and stress non-contact detection. The system comprises an exciting light system, an exciting light transmission system, a phosphorescence / fluorescence light splitting light path and acquisition system and a data processing system, the exciting light system is used for emitting 355 nm and 532 nm laser, and the exciting light transmission system is used for inputting the 355 nm and 532 nm laser to a thermal barrier coating of a sample. The phosphorescence / fluorescence light splitting light path and acquisition system is used for splitting light signals emitted by the thermal barrier coating through excitation, dividing the light signals into phosphorescence and fluorescence and performing acquisition, and the data processing system is used for calculating a temperature field and a stress field of the thermal barrier coating based on the acquired phosphorescence and fluorescence. According to the invention, the problem that the temperature and stress coupling effect of the thermal barrier coating interferes with each other in the test is solved, and the problem that the temperature and stress of the thermal barrier coating cannot be tested in a real-time, in-situ, collaborative and non-contact manner in the prior art is solved.

The invention provides a preparation method of a heat-insulating coating component, the heat-insulating component in a heat-insulating material is (Sn-Sb) Ox, the heat-insulating material has an extremely high specific surface area, the pore diameter is intensively distributed at 20-50 nm, the specific surface area is 323-478 g / cm < 2 >, the heat-insulating material can be highly uniformly mixed and dispersed with the coating, and the prepared heat-insulating coating has a good heat-insulating effect.

The invention provides a production method of lanthanum zirconate, and belongs to the technical field of inorganic non-metallic materials. According to the invention, an electric smelting method is adopted, during high-temperature smelting, a zirconia material and lanthanum oxide / lanthanum carbonate are fully subjected to a high-temperature liquid phase chemical reaction at high temperature, an all-La2Zr2O7-phase electric smelting lanthanum zirconate product can be obtained, and the all-La2Zr2O7-phase electric smelting lanthanum zirconate product can be processed into particle size sand and fine powder with various particle sizes or can be processed into crushing and grading powder for a high-temperature thermal barrier coating material according to the requirements of users. Compared with a La2Zr2O7 material prepared by a solid-phase reaction method, a precipitation method, a sol-gel method, a self-propagating combustion method, a hydrothermal synthesis method and the like, the lanthanum zirconate prepared by the method provided by the invention is high in volume density and low in porosity, can be processed into particles and fine powder / graded powder with various particle size levels, is good in high-temperature volume stability, and can be used for preparing the lanthanum zirconate material. As an electric melting material, the material has the characteristics of small reheating shrinkage and small high-temperature creep deformation.

This invention belongs to the field of thermal insulation materials technology and discloses a composite thermal insulation coating based on an ethanol evaporation-induced stable covalent crosslinked adhesive phase and its preparation method. The composite thermal insulation coating includes a crosslinked adhesive phase and hollow glass microspheres dispersed and fixed within the crosslinked adhesive phase. The crosslinked adhesive phase is obtained by ethanol evaporation-induced crosslinking of a reactive precursor formed by the reaction of thioctic acid and amino-functionalized polydimethylsiloxane. During the drying process of the precursor, ethanol evaporation gradually forms an adhesive network containing polydimethylsiloxane segments and a covalently crosslinked structure derived from thioctic acid. The preparation method includes reactive precursor preparation, slurry compounding, and drying and curing steps, requiring no additional crosslinking agent or high-temperature curing, and can complete crosslinking and film formation at room temperature or under moderate heating conditions. The thermal conductivity of the composite thermal insulation coating can be as low as 0.025–0.030 W / (m·K), and it possesses good adhesion, waterproof and moisture-proof properties, mechanical stability, and environmental durability.