443 results about "Bond coat" patented technology

The invention discloses an integrated preparation method of a SiC-based composite material environment barrier coating in the technical field of aviation thermal structure materials, which comprises the following steps: cleaning a substrate, carrying out vacuum impregnation of phenolic resin and curing, coating Si slurry to form a bonding layer, coating rare earth silicate slurry to form a barrier layer, and drying to obtain the SiC-based composite material environment barrier coating. And finally carrying out high-temperature heat treatment in an inert atmosphere. According to the method, through an integrated slurry coating and gradient curing process, the performance of a base body is protected, and meanwhile efficient preparation of the coating is achieved; by adopting an integrated slurry coating and gradient curing technology and combining with an optimized medium-temperature sintering process, the matrix performance is effectively protected while the compactness of the coating is ensured, the bonding strength and interface stability of the coating are improved through the design of the phenolic resin transition layer and the silicon bonding layer in cooperation with the rare earth silicate barrier layer, and the bonding strength of the coating is improved. And the coating shows excellent protection performance in a high-temperature corrosion environment.

The invention relates to the field of batteries, in particular to a long-circulation persistent adhesion type negative electrode composite electrode and a preparation method and application thereof. The long-circulation persistent adhesive type negative electrode composite electrode comprises a current collector, and a first adhesive layer, an active slurry coating and a second adhesive layer which are sequentially coated on two sides of the current collector, according to the invention, through the bonding effect between the second bonding layer and the diaphragm, the pole piece is uniformly stressed during cyclic expansion, the wrinkles of the pole piece are improved, the electrolyte infiltration is better in combination with the oil-absorbing conductive agent, the lithium ion transmission efficiency is improved, and the cycle life is prolonged; an interface structure formed by multi-layer coating can buffer lithium ion intercalation / deintercalation stress, so that the pole piece can still keep good binding power after circulation, and the cycle performance of the lithium ion battery can be effectively improved; the conductive agent contents of the first bonding layer, the active slurry coating and the second bonding layer are distributed in a concave gradient manner, so that the resistance is reduced, and the conductivity is enhanced.

The invention discloses a preparation method of a toughening environmental barrier coating, and relates to a preparation method of a coating. The invention aims to solve the problem of poor fracture toughness of the existing environmental barrier coating. The method comprises the following steps: 1, pretreating a base material; 2, preparing a bonding layer; and 3, preparing the environmental barrier layer. The high-melting-point metal silicide prepared on the surface of the base material or the bonding layer compounded by the high-melting-point metal silicide and the rare earth silicate has excellent temperature resistance and good interface bonding strength, and due to the addition of the rare earth silicate, the expansion coefficient of the bonding layer is highly matched with that of the base material; according to the prepared yttrium oxide stabilized zirconia fiber, mullite fiber or silicon carbide fiber reinforced rare earth silicate environmental barrier layer, the fracture toughness of pure Yb2SiO5 is improved to 6.5 MPa.m < 1 / 2 >-8.0 MPa.m < 1 / 2 > from about 1.85 MPa.m < 1 / 2 >. The strengthening and toughening environmental barrier coating prepared by the invention has very important significance on development of thermal protection coatings of hot end parts of aircrafts with high thrust-weight ratios in China.

The invention discloses a colored photovoltaic module which comprises a transparent colored glaze panel, a transparent bonding layer A, a battery layer, a bonding layer B and a back plate which are sequentially packaged in a stacked mode. The transparent colored glaze panel comprises a glass substrate, a transparent colored coating covering the outer side surface of the glass substrate, and a transparent glaze layer covering the outer side surface of the transparent colored coating; the transparent glaze layer is combined with the transparent colored coating through a covalent bond; the main component of the transparent glaze layer is silicon dioxide. The transparent colored coating of the colored photovoltaic module is positioned on the outer surface of the glass panel of the photovoltaic module, so that the defect of glass texture of a traditional photovoltaic module serving as a building material product is overcome; a transparent glaze layer with silicon dioxide as a main component is further arranged outside the transparent colored coating to serve as a protective layer, the adhesion fastness is high, the excellent performance of high hardness, high transparency, super weather resistance, acid and alkali resistance, scratch resistance and stain resistance is achieved, and the colored coating is effectively protected against color fading, falling off and external erosion such as acid rain, ultraviolet and sand wind.

The invention provides a thermal barrier coating with an interface three-dimensional bionic structure and a preparation method and application of the thermal barrier coating, and belongs to the technical field of thermal barrier coatings. By means of 3D printing, preparation of a complex, special and arrangement-distribution-controllable three-dimensional texture component with a complex geometrical shape and an internal structure can be achieved, and therefore the coating interface residual stress, the contact area and the pinning effect are improved; 3D printing can avoid internal oxidation of the bonding layer, and meanwhile it is ensured that the structure of the multi-level interface is uniform and stable; and then the ceramic layer is prepared by combining the spraying technology, preparation of the interface three-dimensional bionic structure thermal barrier coating is achieved, interface mechanical engagement of the bonding layer and the ceramic layer can be increased through the structure, an interlocking mechanism is achieved, the coating interface structure and residual stress are improved, and therefore the service life of the coating is greatly prolonged, and the bonding strength of the coating is greatly improved.

The invention relates to the technical field of transfer films, in particular to a graphene-containing far-infrared warm-keeping polyurethane transfer film and a preparation method thereof. The far-infrared warm-keeping polyurethane transfer film containing graphene comprises a three-layer structure including a supporting layer, a polyurethane transfer layer and a bonding layer, the polyurethane transfer layer is located on one side of the supporting layer, and the bonding layer is located on the other side of the polyurethane transfer layer; the polyurethane transfer layer is prepared from polyurethane resin, an organic solvent, an organic pigment and a composite modifier, the composite modifier is prepared from alkenyl modified graphene oxide, chloropropenyl modified hindered phenol and 4-allyloxy-2-hydroxybenzophenone, and the composite modifier is added, so that the polyurethane transfer layer is formed. The polyurethane transfer film has far infrared thermal insulation performance and good oxidation resistance and hydrolysis resistance.

The invention provides a gradient self-repairing sealing coating and a preparation method thereof, and relates to a high-temperature protection material. The gradient self-repairing sealing coating comprises a bonding layer, a gradient middle layer, a transition layer and an abradable surface layer which are sequentially arranged from a base body to the surface. A bonding layer in the gradient self-repairing sealing coating contains silicate, so that the bonding strength and the heat-resistant stability of a matrix are improved; rare earth silicate and Ir elements are introduced into the gradient intermediate layer, so that high-temperature corrosion resistance is enhanced, and thermal stress is relieved; the transition layer contains zirconium oxide and graphene and has the functions of thermal isolation and stress regulation; the abradable surface layer is formed by combining rare earth silicate and graphite, low friction and preferential abrasion are achieved, and effective sacrifice protection is provided. The overall structure can have multiple properties of heat, corrosion resistance and abrasion resistance, and is suitable for the surface protection requirement under the complex hot end working condition.

The invention relates to the technical field of thermal barrier coating preparation, in particular to a double-ceramic-layer thermal barrier coating and a preparation method thereof. The double-ceramic-layer thermal barrier coating comprises a base body and further comprises a bonding layer, a ceramic middle layer and a ceramic top layer which are sequentially deposited on the base body, the ceramic middle layer and the ceramic top layer are both doped with pore-forming agents, and the pore-forming agents are aluminum oxide hollow microspheres. The aluminum oxide hollow microspheres are doped into the double ceramic layers to serve as a pore forming agent, the pore content is increased, meanwhile, the stability and the mechanical property of the coating structure are guaranteed, the high-temperature heat insulation performance of the coating structure is further improved due to the increased pore content, the ceramic layers can still keep stable at the temperature of 1400 DEG C or above, and the service life of the coating structure is prolonged. The obtained thermal barrier coating system can be used for hot end components of devices such as gas turbine engines, so that the heat energy loss is reduced, the kinetic energy efficiency is improved, and the service life is prolonged.

The invention relates to the technical field of thermal protection coatings, and discloses a high-reflection thermal protection coating and a preparation method thereof.LSTN0.125 powder is subjected to spray granulation and then pre-sintered and sieved, and spherical LSTN0.125 ceramic powder is obtained; the alloy substrate is subjected to roughening treatment, and a bonding layer is prepared on the surface of the alloy substrate through the atmosphere plasma spraying technology; the spherical LSTN0.125 ceramic powder obtained in the step S1 is sprayed on the bonding layer through the atmosphere plasma spraying technology, and an LSTN0.125 ceramic layer is obtained; and the LSTN0.125 ceramic layer is subjected to heat treatment, and the LSTN0.125 thermal protection coating is obtained. According to the invention, the LSTN0.125 with high reflectivity is used as a powder raw material of the coating, so that the high reflection performance of the coating in a near-infrared band can be remarkably enhanced, and the effect of isolating high temperature is achieved.

The invention relates to the technical field of deposition of wear-resistant and corrosion-resistant coating materials on metal surfaces, in particular to a high-toughness CrNbZrNiSiBN high-entropy nitride coating and a preparation method thereof. A bonding layer formed by a Cr layer, a transition layer formed by a CrN layer and a functional layer coated with CrNbZrNiSiBN high-entropy nitride are sequentially arranged on the surface of a base material. And the total thickness of the coated functional layer is 2-10 microns. The method is completed by adopting an ion beam assisted arc ion plating technology, and the prepared composite coating has the advantages of relatively high hardness, relatively good toughness, wear resistance, corrosion resistance, high-temperature oxidation resistance and the like. The coating can be used for strengthening and protecting the surfaces of cutters, molds, aerospace, marine ship parts and the like.

The invention discloses a recoverable high-barrier-property multilayer composite film and a preparation method thereof. The composite film adopts a five-layer symmetrical structure, namely a heat sealing layer, a first bonding layer, a blocking layer, a second bonding layer and a surface protection layer. Wherein the barrier layer is a montmorillonite modified ethylene-vinyl alcohol copolymer, and montmorillonite is modified by a carboxyl functionalized ammonium bromide intercalator; the bonding layer is maleic anhydride grafted polylactic acid; the heat sealing layer contains modified composite filler; the surface protection layer is a polyethylene / graphene modified coupling agent composite system. The preparation method comprises the steps of intercalation modified montmorillonite preparation, barrier layer material melt blending, five-layer co-extrusion casting, gradient hot pressing and curing treatment. The problems that a traditional high-barrier film is unrecyclable, the interlayer binding force is weak and the high-temperature stability is poor are solved, the ultrahigh barrier performance that the oxygen transmission rate is smaller than or equal to 0.5 cm < 3 > / (m < 2 >. 24 h) and the water vapor transmission rate is smaller than or equal to 1.0 g / (m < 2 >. 24 h) is achieved, and the mechanical property retention rate is larger than or equal to 85% after recycling and re-pelletizing.

The invention relates to the technical field of material science, and discloses a slurry valve erosion-resistant multi-layer coating with gradient function design and a preparation method thereof.The coating comprises a bonding layer, a gradient function layer and an erosion-resistant surface layer which are sequentially arranged from inside to outside, the bonding layer is composed of nickel-based alloy or cobalt-based alloy, the thickness of the bonding layer is 50-100 micrometers, and the thickness of the gradient function layer is 50-100 micrometers. The gradient functional layer is made of composite powder of metal and ceramic, the metal is nickel or cobalt, the ceramic is tungsten carbide or chromium carbide, and the components of the gradient functional layer are from the bonding layer side to the erosion-resistant surface layer side; the bonding layer is arranged and forms firm metallurgical bonding with the matrix, the interface stress is reduced, the basic reliability of bonding of the coating and the matrix is guaranteed, meanwhile, the gradient functional layer with the metal and ceramic volume fraction gradually changing continuously is adopted, the problem that the thermal expansion coefficients of the coating and the matrix are not matched is solved, and the service life of the coating is prolonged. And the crack initiation and expansion risk caused by internal stress concentration is reduced, so that the long-term stability of the coating structure is ensured.

The invention relates to the technical field of thermal barrier coatings for gas turbines or aero-engines, and particularly discloses an ultra-thick and strong-bonding double-ceramic-layer thermal barrier coating and a preparation method thereof.The thermal barrier coating is composed of an MCrAlY bonding layer, a YSZ ceramic layer bottom layer and a high-entropy rare earth zirconate ceramic layer surface layer; the MCrAlY bonding layer is prepared through atmospheric plasma or hypersonic flame spraying, YSZ and high-entropy rare earth zirconate spherical powder serve as spraying raw materials, and the thermal barrier coating is prepared through an axial powder feeding high-energy plasma spraying system. The thermal barrier coating has the characteristics of super thickness (the coating thickness is 600-1200 microns), high bonding strength (gt; 19 MPa) and the like.

The invention discloses a composite environmental barrier coating as well as a preparation method and application thereof, and relates to the technical field of high-temperature protective coatings. The composite environmental barrier coating comprises a bonding layer, a barrier layer and a ceramic layer, wherein the bonding layer comprises Si and HfO2 in a molar ratio of (1: 10)-(1: 5); the ceramic layer is (Lux, Yby) 2SiO5, and 0.1 lt; xlt; 0, 0.4, 0.6 lt; yt; Yt; 0.9, 0.9; the thickness of the composite environmental barrier coating is not greater than 200 [mu] m. The composite environmental barrier coating can resist CMAS corrosion for up to 100 h in the atmospheric environment of 1300-1500 DEG C, the coating does not peel off after being corroded by water and oxygen for 300 h, and the composite environmental barrier coating has excellent heat insulation performance, bonding strength and thermal cycle performance and is expected to be applied to preparation of aero-engine hot end components.

The invention relates to the technical field of metal surface coating preparation, in particular to a high-temperature thermal cycle impact resistant yttrium oxide composite coating on the surface of refractory metal and a preparation method of the yttrium oxide composite coating. The refractory metal composite coating material is composed of a refractory metal matrix and a coating. The coating comprises a bonding layer, a middle layer and a surface layer which are arranged in a contact manner; the bonding layer is composed of the refractory metal and yttrium oxide, and the porosity of the bonding layer is 1%-5%; the middle layer is a pure yttrium oxide layer with the porosity of 5%-10%; the porosity of the surface layer is 1t; 2% of a pure yttrium oxide layer; the melting point of the refractory metal is 2470 DEG C or higher. According to the refractory metal composite coating material and the preparation method and application thereof, the refractory metal coating structure is optimized, the porosity of the coating is further adjusted, the high-temperature molten metal corrosion resistance and the high-temperature thermal shock resistance of the coating are improved, meanwhile, the bonding strength between the coatings is guaranteed, and the service life of the coating is prolonged. The method is expected to be applied to high-melting-point metal smelting equipment.

The invention belongs to the technical field of energy storage devices, and particularly relates to a high-pressure and high-temperature resistant battery diaphragm, a battery and a preparation method thereof. The diaphragm comprises a base membrane and a functional coating coated on at least one side of the base membrane, the coating comprises a bonding layer, a reinforcing layer and an interface layer which are sequentially distributed, the reinforcing layer comprises a two-dimensional vermiculite nanosheet, the transverse size of the two-dimensional vermiculite nanosheet is 0.5-10 microns, and the thickness of the two-dimensional vermiculite nanosheet is 1-5 nm, so that the thickness of the two-dimensional vermiculite nanosheet is 1-5 nm. Through the two-dimensional vermiculite nanosheets, the puncture strength of the strengthened layer is improved by 140%, and zero deformation is achieved under the pressure of 10 MPa; the strengthening layer blocks heat conduction, and the shrinking percentage at 250 DEG C is smaller than 5%; the contact angle of the electrolyte is reduced to 8 degrees by the interface layer, so that the ion mobility is improved; the cost of the vermiculite ore raw material is only 1 / 5 of that of aluminum oxide.

The invention provides a preparation method and application of ceramic slurry for high-temperature bonding of aluminum nitride ceramics, and relates to the technical field of high-temperature ceramic materials.The preparation method comprises the following steps that firstly, an organic carrier is prepared, a polymer binder, an organic solvent, a plasticizer and a dispersing agent are weighed according to the weight ratio and stirred at the temperature of 60-70 DEG C till complete dissolution and clarification are achieved for use; 2, an inorganic functional phase is prepared, aluminum nitride powder, yttrium oxide powder and alkaline earth metal oxide powder are weighed according to the weight proportion and placed in a ball milling tank to be evenly mixed, the obtained ceramic slurry serves as a bonding layer, the tolerable temperature can reach 1000 DEG C or above and is far higher than that of metal brazing filler metal, and the ceramic slurry is suitable for severe environments such as aerospace and high-temperature sensors. The main components of the bonding layer are consistent with the base material, and the thermal expansion coefficient is highly matched, so that the thermal stress can be greatly relieved, and the failure of the device caused by thermal fatigue in the temperature cycle is avoided.

The application discloses a kind of low thermal conductivity high reflectivity five-element co-doped ceramic laser protection coating and preparation method thereof, belong to high-energy laser protection technical field.The protective coating includes the adhesive layer and the reflective heat insulation layer of laminated arrangement, adhesive layer is arranged on the surface of base material, reflective heat insulation layer is arranged on the surface of adhesive layer;Wherein, adhesive layer is formed by spraying one of Ni-Al self-bonding powder, Ni-Mo-Al, NiCrAlY, CoCrAlY and NiCoCrAlY;Reflective heat insulation layer is the ceramic coating of five-element co-doped ZrO2, in ceramic coating, base element is ZrO2, doping component is:Y2O3, Gd2O3, Yb2O3, TiO2 And Ta2O5, after doping, material is single cubic phase structure at 25 ℃-1600 ℃.By multiple oxide doping to ZrO2, the coating can maintain cubic phase at room temperature while having lower thermal conductivity and higher reflectivity, can solve the problems of oxidation reflectivity reduction of metal material, mass loss of ablation material and insufficient heat insulation capacity of heat insulation material in laser protection field, prolong service life.

A gas turbine engine component includes a substrate having first surface and a second surface disposed opposite the first surface, a plurality of holes extending through the substrate from the first surface to the second surface, the holes defined by a plurality of respective walls each extending from the first surface to the second surface, a metallic bond coat disposed on the first surface, and an aluminide coating disposed on the first surface, the second surface, and the walls. The metallic bond coat is disposed between the first surface and the aluminide coating and the walls are free of the metallic bond coat.

The invention relates to a method for preparing a diffusion bonding layer on a nickel-based alloy and YSZ ceramic coating interface, and belongs to the technical field of metal material surface protection and ceramic coatings. According to the preparation method, a YSZ composite ceramic coating is deposited on the surface of the nickel-based alloy by adopting an electrophoretic deposition method, and then an MCr2O5 (M is Zr, Y, Ce, Yb and Al) diffusion bonding layer is prepared on the interface of the nickel-based alloy and the YSZ composite ceramic coating by adopting a pressureless discharge sintering and thermal diffusion treatment method. The bonding layer prepared through the diffusion method is good in interface bonding, the thermal stress between the nickel-based alloy and the YSZ ceramic coating is effectively buffered, the defects that a bonding layer prepared through a traditional method is large in pore impurity amount and the like can be overcome, and the bonding force between the ceramic coating and a base body and the high-temperature anti-oxidation and anti-stripping performance are remarkably improved.

The invention provides a ceramic-based low-frequency wave-absorbing coating and a preparation method and application thereof.The preparation method of the ceramic-based low-frequency wave-absorbing coating comprises the steps that after a metal substrate is subjected to chamfering, deoiling and sand blasting treatment, a bonding layer is prepared on the metal substrate through a plasma spraying technology; preparing a ceramic layer on the bonding layer by adopting a plasma spraying process, and then pasting an aluminum film adhesive tape on the surface of the ceramic layer and flattening the aluminum film adhesive tape; a laser marking machine is used for cutting the aluminum film adhesive tape according to a surface periodic structure unit, and the surface periodic structure unit is of a square and round combined structure; after cutting is completed, the square aluminum film adhesive tape and the round aluminum film adhesive tape are torn down, and then a structural layer is prepared on the ceramic layer through a plasma spraying technology; and tearing off the rest of the aluminum film adhesive tape, placing the coating in a muffle furnace, sintering for a set time at a set temperature, and cooling to obtain the ceramic-based low-frequency wave-absorbing coating. The low-frequency wave-absorbing performance of the coating can be improved.

The invention discloses a thermal barrier coating with a double-bonding-layer structure and a preparation method thereof, and belongs to the field of thermal barrier coatings. According to the thermal barrier coating, nickel-based high-temperature alloy serves as a substrate, the thermal barrier coating sequentially comprises an MCrAlY lower bonding layer, a Cr2AlC upper bonding layer and an 8YSZ ceramic layer, the MCrAlY lower bonding layer and the Cr2AlC upper bonding layer are prepared through the high velocity oxy-fuel spraying technology, and the 8YSZ ceramic layer is prepared through the atmosphere plasma spraying technology. According to the thermal barrier coating system, through the synergistic effect of the oxidation resistance of the Cr2AlC upper bonding layer and the mutual diffusion inhibition characteristic of the MCrAlY lower bonding layer, the comprehensive performance of the thermal barrier coating is optimized, meanwhile, the anti-stripping capacity of the thermal barrier coating system is remarkably improved, and the thermal barrier coating system is suitable for various high-temperature alloy substrates, is not limited by alloy component differences, can further adapt to workpieces in complex geometrical shapes and is suitable for industrial production. The method can be used for protecting hot-end components such as aero-engine turbine blades and the like.

The invention belongs to the technical field of refrigerator van plates, and particularly relates to a high-strength low-heat-bridge refrigerator van plate which comprises a plate body of a multi-layer composite structure, and the plate body sequentially comprises an outer skin layer, a first bonding layer, a polyurethane rigid foam heat preservation layer, a second bonding layer and an inner skin layer from outside to inside. The polyurethane rigid foam thermal insulation layer is filled with polyurethane glue; a plurality of hollow reinforcing channels extending longitudinally are formed in the polyurethane rigid foam heat preservation layer; the first bonding layer and the second bonding layer are fiber reinforced composite material layers, and the fiber reinforced composite material layers are formed by compounding and curing fiber materials and polyurethane foam. A metal framework is completely replaced by the integrally-formed hollow reinforced channel, a heat conduction path is cut off fundamentally, the heat preservation performance is remarkably improved, and cold chain transportation energy consumption is reduced.

The invention provides a temperature-resistant radar infrared compatible stealth coating and a preparation method thereof. The problems that an existing radar infrared compatible stealth coating is insufficient in temperature resistance and poor in low-frequency wave absorbing performance are solved. The temperature-resistant radar and infrared compatible stealth coating sequentially comprises a bonding layer, a wave absorbing layer and an infrared stealth layer from bottom to top, the bonding layer is made of NiCrAlY or NiCoCrAlY, and the bonding layer is made of NiCoCrAlY; the material of the wave absorbing layer is 20 wt%-65 wt% of a ceramic matrix and 80 wt%-35 wt% of an absorbent; the chemical formula of the absorbent is Fe0. 7Al0. 3Ti (1-x) RxO3, in the formula, x is equal to 0.2-0.55, and R is Ni, Nb or Ta; the infrared stealth layer is a precious metal layer arranged in a periodic structure.

The invention discloses a CMAS-corrosion-resistant thermal barrier coating and a preparation method thereof, and belongs to the technical field of thermal barrier coatings. The preparation method comprises the steps that a bonding layer is prepared; preparing a YSZ coating on the bonding layer; the Gd2O3 coating is prepared on the YSZ coating through micro-flow extrusion molding of Gd2O3 ceramic slurry, and the conditions of micro-flow extrusion molding are as follows: the extrusion pressure is 2-3 kPa, the extrusion speed is 6-10 mm / s, and the extrusion temperature is 60-80 DEG C; and the bonding layer, the YSZ coating and the Gd2O3 coating are subjected to heat treatment. The thermal barrier coating prepared through the method has a compact structure and excellent heat insulation performance, the heat conductivity ranges from 0.85 W / (m.K) to 1.1 W / (m.K), the bonding strength of the coating ranges from 35 MPa to 50 MPa, compared with a conventional thermal barrier coating material, the thermal barrier coating is more excellent in CMAS corrosion resistance effect, and in a CMAS corrosion experiment, after the coating is subjected to a molten salt corrosion test at 900 DEG C / 100 h, the appearance of the coating is free of peeling and cracking phenomena.

The invention discloses a preparation method of a high-toughness low-conductivity anti-radiation thermal barrier coating. The invention belongs to the technical field of thermal barrier coating materials. Aiming at the problems of thermal expansion mismatch of a precious metal second phase, failure of a multilayer structure interface and insufficient toughness of a glass ceramic-based coating in an existing coating, the invention provides a composite gradient structure design. By introducing the glass ceramic intermediate layer and the gradient functional surface layer and combining plasma spraying and high-temperature sintering processes, the characteristics of high toughness, low heat conductivity, radiation resistance and high-temperature self-healing of the coating are realized. The method comprises the following specific steps: step 1, substrate pretreatment; step 2, bonding layer preparation; step 3, glass ceramic intermediate layer deposition; step 4, functional surface layer gradient spraying; the thermal conductivity of the obtained coating is lower than 0.8 W / (m.K), the bonding strength is larger than 35 MPa, the fracture toughness reaches 4.0 MPa.m < 1 / 2 >, the infrared reflectivity at the waveband of 0.3-10 microns is larger than 0.85, and microcrack self-healing can be achieved at the temperature of 1200 DEG C. The method is suitable for ultra-high-temperature service environments such as aero-engine turbine blades.

The invention provides a multi-layer composite board and a manufacturing process thereof, a refrigerator door body and a household appliance shell, and relates to the technical field of composite materials. The invention provides a multi-layer composite board. The multi-layer composite board comprises a base board, a magnetic sheet and a bonding layer. And the substrate is made of a glass material. And the magnetic sheet is compounded on one side of the substrate and can be attracted with a metal material or a magnetic material. The bonding layer is arranged between the substrate and the magnetic sheet and is used for bonding the substrate and the magnetic sheet; the bonding layer comprises raw material components which can be formed through light curing. The multi-layer composite board provided by the invention has the characteristics of magnetic attraction and corrosion resistance, also has the characteristics of simple process, easiness in manufacturing and low energy consumption, and is relatively high in structural stability.

The invention provides a method for prolonging the high-temperature service life of a thermal barrier coating of a hydrogen-doped gas turbine. The method comprises the steps that Ni, Co, Cr, Fe, Al, Hf, Si and Y are smelted and cast into master alloy according to the proportion; preparing the mother alloy into high-entropy alloy powder through an inert gas atomization process; high-entropy alloy powder is deposited on the surface of the high-temperature alloy substrate by adopting a high velocity oxy-fuel spraying process, and a bonding layer of the thermal barrier coating is obtained; and preparing a thermal barrier coating on the bonding layer by adopting a plasma spraying process, and carrying out vacuum heat treatment on the thermal barrier coating in advance. The high-entropy alloy bonding layer provided by the invention has better thermal stability, and can still keep strong bonding force between the ceramic layer and the bonding layer alloy after water quenching high-temperature thermal cycle service. And the transition group high-entropy alloy bonding layer is beneficial to formation of a thermal growth oxide layer, has an inhibition effect on diffusion of metal elements and coating degradation in the hydrogen-induced corrosion and high-temperature steam corrosion processes, and can prolong the high-temperature thermal shock service time of the hydrogen-doped gas turbine.

The invention relates to a thermal barrier coating with composite vertical crack collaborative design and a preparation method, and belongs to the technical field of thermal barrier coatings. The coating is composed of a nickel-based high-temperature alloy matrix, an MCrAlY bonding layer, a YSZ first ceramic layer and a multi-element rare earth doped zirconium oxide second ceramic layer containing composite vertical cracks. The second ceramic layer is provided with a penetrating type (the depth is 100%) and non-penetrating type (the depth is 60%-80%) composite crack structure, and preparation can be accurately regulated and controlled by optimizing atmospheric plasma spraying process parameters (such as the preheating temperature of a base body, the powder feeding rate and the moving speed of a spray gun) and controlling the process. According to the double-ceramic-layer thermal barrier coating with the composite vertical crack structure, thermal stress release of the coating can be remarkably improved through collaborative design of the crack structure and material optimization, the thermal shock life can be prolonged by nearly two times at the temperature of 1300 DEG C, CMAS molten salt permeation is effectively inhibited, and excellent heat insulation performance and long-term service stability are achieved.

The invention belongs to the technical field of high-temperature protective coatings, and particularly discloses a La2Zr2O7-NiCoCrAlTaY composite gradient multi-layer coating suitable for surface protection of high-temperature parts such as gas turbines of ocean vessels and a preparation method of the La2Zr2O7-NiCoCrAlTaY composite gradient multi-layer coating. According to the composite gradient multilayer coating, a bonding layer, a gradient transition layer and an outer layer are sequentially arranged on the surface of a base body. Wherein the bonding layer is a NiCoCrAlY alloy layer, the gradient transition layer is a multi-layer composite coating formed by gradient change of NiCoCrAlTaY alloy and La2Zr2O7 components, and the outer layer is a La2Zr2O7 ceramic layer. Due to gradient change of NiCoCrAlTaY alloy and La2Zr2O7 components of the gradient transition layer, slow transition of the coefficient of thermal expansion in the whole coating from a metal base material to a ceramic layer can be achieved, and therefore thermal stress between the coating and a base body and thermal stress between all layers in the coating are remarkably reduced. Meanwhile, the coating is prepared through laser cladding, metallurgical bonding is formed among the base body, the bonding layer, the gradient transition layer and the ceramic layer, and the bonding force of the metal base body and the ceramic coating can be enhanced.