124results about How to "Good heat matching" patented technology

The invention provides a combined cycle thermoelectric conversion system utilizing multi-grade waste heat of an internal combustion engine. According to the system, combined organic Rankine cycle is formed by high-temperature grade cycle and low-temperature grade cycle, heat is supplied by exhaust waste heat of the internal combustion engine, supercharged and mid-cooling waste heat, exhaust gas recirculation waste heat and cooling water waste heat, a cooling quantity is provided by cold wind, and the system comprises a high-temperature grade working medium pump, a high-temperature grade heat regenerator, a high-temperature grade exhaust heater, a high-temperature grade EGR (exhaust gas recirculation) heater, a high-temperature grade expansion engine, a high-temperature grade condenser, a low-temperature grade working medium pump, a low-temperature grade heat regenerator, a low-temperature grade cooling water heater, a low-temperature grade supercharged air heater, a low-temperature grade exhaust heater, a low-temperature grade EGR heater, a low-temperature grade expansion engine, a low-temperature grade condenser, a low-temperature grade condenser fan and a power generator. According to the combined cycle thermoelectric conversion system utilizing multi-grade waste heat of the internal combustion engine, comprehensive and efficient utilization of multi-grade waste heat of the internal combustion engine can be achieved, further, irreversible loss is smaller when both the high temperature and the low temperature adopt supercritical expanding cycle, and the integral efficiency of the internal combustion engine can be effectively improved.

The invention discloses a high temperature anti-oxidation coating molybdenum material and a preparation method thereof. The surface of a product is provided with a Mo-N-Si-B anti-oxidation coating which is synthesized by adopting a three-step in situ synthesis method. Compared with the prior art, the product has good high temperature anti-oxidation performance and is good in material compactness, and hot matching performance between the coating and a base body is good. The preparation method does not need expensive devices such as plasma spraying, chemical vapor deposition or infiltration, avoids a complex process of a slurry method and is simple in preparation process, low in production cost and easy in controlling of coating structures and phase states.

The invention discloses a preparation method of a heat-insulating ceramic phenolic resin-based gradient composite material. Fiber cloth is used as a reinforcing phase, and the fiber cloth is respectively dipped in different gum dipping solutions with the phenolic resin as a matrix and contents of ceramic components and hollow microbeads in gradient distribution to prepare a prepreg; laminating, die pressing and thermal curing molding at 150-200 DEG C to obtain the gradient composite material comprising a heat-proof layer, a gradient transition layer and a heat-insulating layer. When the temperature of the gradient composite material is as high as 1000 DEG C, the heat-proof layer can be converted into a ceramic phase with higher strength and can resist heat flow erosion; the gradient transition layer can relieve stress concentration and reduce stress; and hollow microspheres are added to guarantee that the heat-insulating layer has good thermal matching performance.

The invention discloses a preparation method of a titanium substrate surface high-temperature antioxidant composite coating. The preparation method comprises the following steps: I, carrying out the surface polishing treatment for a titanium substrate, oxidizing the titanium substrate subjected to the surface polishing treatment to obtain a titanium substrate with a titanium dioxide ceramic layer on the surface, and depositing metal aluminum on the titanium dioxide ceramic layer to obtain the titanium substrate with a titanium dioxide ceramic layer and an aluminum coating on the surface; and II, carrying out the vacuum heat treatment for the titanium substrate with the titanium dioxide ceramic layer and the aluminum coating on the surface, and obtaining a high-temperature antioxidant composite coating on the surface of the titanium substrate. The high-temperature antioxidant composite coating consisting of Ti and Al intermetallic compounds and oxide ceramics can be prepared on the surface of the titanium substrate, and the high-temperature antioxidant composite coating structure is continuous and compact and has no hole defect; moreover, the surface of the high temperature antioxidant composite coating is provided with an Al2O3 membrane, the Al2O3 membrane can prevent an oxygen element from diffusing into the titanium substrate, and the high temperature antioxidant capability of the titanium substrate can be improved.

The invention relates to a yttrium modified chromium aluminium carbonitride/silicon nitride nano composite coating and a deposition method thereof. Chromium aluminium carbonitride and silicon nitride are subjected to nano composite design to form a nano composite structure with nanocrystal chromium aluminium carbonitride implanted into amorphous silicon nitride, so that the rigidity of the coating is improved; the toughness of the coating and bonding strength of the coating and a matrix are both considered; a rare earth element Y is introduced simultaneously, so that the mechanical property and high-temperature oxidation resistance of the coating are further improved; and the nano composite coating which is strong in bonding force, high in rigidity, good in toughness, low in friction coefficient and prominent in thermostability and is used for high-speed steel and hard alloy cutters and molds is obtained. The coating comprises a chromium-aluminum-yttrium bonding layer, a chromium-aluminum-yttrium nitride transition layer and a nano composite layer; the membrane/matrix bonding strength of the obtained coating reaches 40-90N; the surface composite strength under 10g load reaches 40-65 GPa; and the friction coefficient is 0.2-0.5 when matched with GCr15.

The invention relates to a low-density carbon-tile surface oxidation-resistant coating capable of resisting the temperature of 1700 DEG C and a preparation method thereof, and belongs to the technical field of heat protective materials. For the requirement of heat protective systems of novel near-space aerocrafts and reusable launch vehicles for the heat protective materials with integrated functions of high-temperature resistance, light weight and heat insulation, the invention provides a low-density carbon-tile surface oxidation-resistant coating system capable of resisting the temperature of 1700 DEG C and a preparation method thereof. The coating is a composite coating with a gradient transition structure. The composite coating comprises an oxidation-resistant layer and a surface high-temperature-resistant oxidation-resistant layer, wherein the oxidation-resistant layer is formed by doping oxidation-resistant components such as Si, B, C and O and the like in a porous carbon-fiber skeleton; and the surface high-temperature-resistant oxidation-resistant layer is composed of compact M(M is Hf, Zr)B2-MoSi2 ultrahigh-temperature ceramic components.

The invention relates to a ceramic metal composite substrate and a production method thereof. The substrate mainly comprises an ultrathin ceramic sheet, a heat conduction glue and a metal substrate; the ceramic powder of the ultrathin ceramic sheet is a micropowder and a nanopowder mixture, and the volume proportion of nanopowder in the ceramic powder is 15-25%; and the heat conduction glue comprises, by volume, 20-30% of a one-dimensional high heat conduction material. The production method mainly comprises the following steps: making the ultrathin ceramic sheet; carrying out surface treatment on the metal substrate, coating the metal substrate with the heat conduction glue through a coating technology, and carrying out drying semi-solidification; and carrying out hot pressing on the ultrathin ceramic sheet and the glued metal substrate. The ceramic metal composite substrate has a good heat conduction performance, and has a good heat matching performance with chips, and the method has a high production efficiency, and is in favor of realizing development of the substrate to a small, light and thin direction. Tape casting makes the production efficiency of the ultrathin ceramic sheet be high; and the heat conduction glue comprises the one-dimensional high heat conduction material, so thermal resistance between the ultrathin ceramic sheet and the metal substrate is reduced.

The invention discloses an anti-coking and anti-slagging coating material for four tubes of a boiler as well as a preparation method and a construction process of the anti-coking and anti-slagging coating material. The anti-coking and anti-slagging coating material comprises the components in percentage by mass: 30-50% of high-temperature-resistant binder, 5-40% of lubricating nonstick material, 5-30% of heat-resistant filler, 0.5-5% of auxiliaries and 0-50% of dispersion medium. The coating material is prepared by using a special preparation method and is better in homogenization and stable in storage. The coating material is not only good in anti-coking and anti-slagging properties, good in long-term heat resistance and good in heat matching property with a substrate, but also good in binding adhesion for a metal substrate.

The invention belongs to the technical field of composite material preparation, and particularly relates to a high-strength and high-toughness ultrahigh-temperature ceramic matrix composite material and a preparation method thereof. The preparation method comprises the following steps: alternately depositing two coatings on the surface of the carbon fiber material by adopting a chemical vapor deposition method to obtain the carbon fiber material with the multilayer CVD composite coating, wherein the two coatings are one of a pyrolytic carbon layer or a layered ceramic coating and an ultrahigh-temperature ceramic coating; adopting a phenolic resin/epoxy resin solution and ceramic powder to form ceramic slurry, coating the CVD composite coating carbon fiber material with the ceramic slurry, performing alternately staggered stacking and needling to obtain a stacked fiber felt, and after vacuum drying, performing warm-pressing curing and carbonization treatment, and obtaining a porous prefabricated body; and finally, carrying out densification treatment to obtain the ceramic-based composite material. The material has high strength, high fracture toughness, oxidation resistance, ablation resistance and corrosion resistance, and can be applied to high-temperature and ultrahigh-temperature structural materials, oxidation-resistant and corrosion-resistant materials and aerospace ablation-resistant materials.

The invention discloses a metal ceramic film obtained from the surface of the aluminum alloy and a preparation method thereof. The preparation method of the film includes the steps: polishing an aluminum alloy surface, removing impurities of greasy dirt, dust and the like on the surface, conducting microarc oxidation treatment to the surface of the aluminum alloy; and then adopting a high current pulse electron beam to conduct of bombardment processing on the microarc oxidation surface for a plurality of times to prepare the metal ceramic reinforcing film. The preparation method can prepare a high-hardness abrasion-resistant coating on the surface of the aluminum alloy, can greatly improve combination strength of the coating by introducing a metal phase from a base body, improves toughness of ceramic layers, and obtains a metal ceramic coating with good mechanical property.

The invention relates to an MAX phase coating for resisting molten CMAS corrosion of a thermal barrier coating and a thermal spraying preparation method. The thermal barrier coating system adopting the MAX phase ceramic coating as a corrosion protection layer comprises an alloy matrix, a bonding layer, a YSZ ceramic layer, an MAX phase ceramic layer and a pre-oxidation layer. The method comprisesthe steps that firstly, MAX phase Ti2AlC or Ti3AlC2 powder or suspension for thermal spraying is prepared, the particle size of the powder is 10-100 microns, and the suspension is a water base or an ethanol base and is neutral or acidic; then, a hypersonic flame spraying method or a suspension plasma spraying method or a plasma spraying-physical vapor deposition method is adopted for preparation;and heat treatment is carried out to form a pre-oxidation layer on the surface. The thickness of the prepared ceramic layer is 10-20[mu]m, and the porosity is 3-10%. The thermal barrier coating, whichcomprises the MAX phase coating and is resistant to molten CMAS corrosion, is used for surface protection of aero-engine hot-end components, and the adaptability of the hot-end components in severe high-temperature and corrosive environments can be effectively improved.

The invention provides a hafnium silicate environment barrier coating for a ceramic-based composite material matrix and a preparation method thereof. The preparation method comprises the following steps: (1) mixing HfO2 and SiO2, carrying out wet mixing and ball milling on a ball mill, drying, grinding, sieving, sintering, and carrying out a high-temperature solid-phase reaction; (2) after the high-temperature solid-phase reaction is finished, adding deionized water for slurry preparation, then performing ball milling, and performing spray granulation to obtain an HfSiO4 powder material; (3) firstly spraying a Si layer on the surface of a ceramic-based composite matrix as a priming coat, and then spraying the HfSiO4 powder material on the surface of the priming coat as a surface layer to form a multi-layer coating; and (4) carrying out a heat treatment on the multi-layer coating to obtain the environmental barrier coating. Due to the added heat treatment, the crystallinity of the HfSiO4 surface layer is improved, the binding force of each layer of the coating is better, the stability is higher, and the water and oxygen resistance of the environment barrier coating is greatly improved. The provided preparation method is simple and easy to control, and is easy for industrial production and application.

The invention discloses a heat preventing and insulating integrated thermal protection structure suitable for a negative curvature shape, and belongs to the technical field of thermal protection of hypersonic-speed near space aircrafts. The thermal protection structure includes a force bearing shell and a thermal protection layer; the thermal protection layer includes a heat insulating layer and aheat preventing layer, the inner wall of the heat preventing layer is provided with grid-like heat-preventing layer reinforcement ribs, the heat insulating layer is arranged in the grids of the heat-preventing layer reinforcement ribs, and the surface of the heat insulating layer is provided with a heat insulating layer covering skin; the heat preventing layer, the heat insulating layer coveringskin, and the heat-preventing layer reinforcing ribs are sewed together with the heat insulating layer through a sewing line in a prepreg state, and the whole is subjected to high-temperature curing to form the heat preventing and insulating integrated structure; and an adhesive layer is located between the force bearing shell and the thermal protection layer, and the adhesive layer is an adhesivewith high-temperature resistance and heat matching performance. The thermal protection structure provided by the invention adopts the heat preventing and insulating integrated thermal protection layer, and the thermal protection layer is bonded to the force bearing shell by using the high-temperature-resistant adhesive, so that interface separation at the negative curvature part of the thermal protection structure of an aircraft can be avoided.

The invention relates to a C/SiC composite material, an oxidation resistant coating for the C/SiC composite material and a preparation method thereof. The oxidation resistant coating is used for alternatively forming an HfB2 coating and a SiC coating on a C/SiC composite base material. The preparation method comprises the following steps: coating a layer of HfB2 ceramic precursor solution on the surface of the C/SiC composite base material; forming the HfB2 coating after splitting decomposition; depositing the SiC coating, thereby acquiring an HfB2-SiC compound coating. The invention relates to the C/SiC composite material prepared according to the preparation method. The preparation method is simple in process, low in preparation cost, capable of solving the problems of uniform distribution of HfB2 and SiC and combination with a substrate and promoting the ablation resistance and oxidation resistance of the C/SiC composite material.

The invention discloses a parallel optical assembly. The PCB of the parallel optical assembly comprises a rigid PCB part and a flexible PCB part; the flexible PCB part can be folded or bended; an optical connector is arranged on a metal reinforcement plate in fixed connection with the flexible PCB part. In a packaging process, the optical connector and the metal reinforcement plate can bend or fold with the flexible PCB part, allowing the optical connector of an optical port packaging part to arrive at a most convenient assembling angle and position so as to realize rapid assembling, meanwhile helping reducing a packaging dimension, facilitating component high density distribution, and enhancing an adaptive capacity to environment. The parallel optical assembly can utilize the bending characteristic of the flexible PCB part to realize the overlapping installation of the parallel optical assembly, and guarantee optical connector and electric connector assembling precision so as to realize a compact structure of the parallel optical assembly; the packaging dimension is small, thereby facilitating the application of a parallel optical assembly high density integration communication system.

The invention relates to the technical field of preparation of rare metal materials, specifically to a preparation method for veneering porcelain used for an alumina all-ceramic crown. The preparation method comprises the following steps: weighing a variety of compounds by using an electronic balance and respectively converting the amounts of desired B2O3, K2O, Na2O and CaO into the amounts of H3BO3, K2CO3, Na2CO3 and CaCO3; adding raw materials into deionized water and carrying out ball milling; drying slurry, putting dried slurry into an alumina crucible, delivering the alumina crucible into an electric furnace, carrying out heating, taking out a melt and pouring the melt into cold water for cold quenching; grounding glassy mass obtained after quenching and carrying out sieving with sieve with a bore diameter of 61 [mu]mm so as to obtain baked porcelain powder; weighing 0.2 g of the baked porcelain powder, uniformly blending the baked porcelain powder with deionized water, smearing an alumina ceramic bottom crown with the obtained mixture, delivering the alumina ceramic bottom crown to the electric furnace for heating and carrying out cooling to room temperature in the furnace; and carrying out sintering so as to form the veneering porcelain with a thickness of about 1.5 mm. The microstructure of the baked porcelain powder obtained after sintering is microcrystalline glass, and the thermal expansion coefficient of the baked porcelain powder is 7.2 * 10 <-6>/K. The baked porcelain powder and alumina ceramic have good thermal matching performance; and thermal shock resistance temperature reaches 240 DEG C.

The invention relates to aggregation-type composite powder for a high-temperature abradable seal coating layer and a preparing method of the aggregation-type composite powder. The aggregation-type composite powder which has good spraying technology adaptability is prepared through the method of mechanical milling, room-temperature binding and aggregation. The powder comprises MCrAlY alloy powder, alloy powder with beta-NiAl intermetallic compounds as a main phase, polybenzoate powder, boron nitride, binding agents and the like. Raw materials can be the combination of the materials, and the binding agents can be inorganic matter or organic matter. The powder comprises beta-NiAl intermetallic compound high-temperature-resisting components, heat-resisting temperature of an existing metal-based seal coating layer can be raised, and compared with a ceramic seal coating layer, the coating layer has great thermal shock resistance and can be used under the working condition of the high temperature of 1000 DEG C for a long time. The powder has wide application in gas channel sealing of a combustion gas turbine high-temperature part, especially of a high-pressure turbine.

The invention relates to a molybdenum-alloy-material MoSi2-ZrO2-Y2O3 coating, a preparation method therefor and an application of the molybdenum-alloy-material MoSi2-ZrO2-Y2O3 coating and belongs to the technical field of preparation of ultrahigh-temperature oxidation-resistant coatings. The coating disclosed by the invention contains the following ingredients in percentage by mass: 60% to 80% of MoSi2, 10% to 30% of ZrO2, 5% to 10% of Y2O3 and 1% to 3% of additive, wherein the additive is at least one selected from Si powder and SiC powder. The preparation method comprises the steps: weighing the raw materials according to the designed ingredients, then, carrying out wet-process ball-milling so as to prepare slurry; and then, coating the surface of molybdenum alloy with the slurry, and carrying out vacuum sintering for 40 to 100 minutes at the temperature of 1,550 DEG C to 1,650 DEG C, thereby preparing the coating. According to the coating disclosed by the invention, the ingredient design is reasonable, the preparation process is simple, the production cost is low, the coating is dense and uniform and has high bonding strength with the molybdenum alloy and a coefficient of thermal expansion matched with the molybdenum alloy, and thus the ultrahigh-temperature oxidation resistance of the molybdenum alloy can be effectively improved.

The invention provides a cathode material for a proton conductor SOFC (solid oxide fuel cell) and a preparation method and belongs to the field of SOFCs. According to the material, BaCo(1-y)FeyO(3-delta) with high catalytic activity is selected, material stability is improved by doping the position A with trivalent oxygen ions La<3+>, the electronic structure of transition metal ions Co/Fe is adjusted by introducing Zr<4+> and Y<3+> in the position B, thermal matching with a proton conductor electrolyte is increased, and a single-phase cathode material is obtained. The method comprises steps as follows: preparing powder with an improved citric acid combustion method, weighing chemical raw materials corresponding to the elements in a molar ratio of Ba, La, Co, Fe, Zr and Y being (1-x):x:0.4:0.4:0.1:0.1, adding two complexing agents including citric acid and EDTA, dissolving the two complexing agents with nitric acid and ammonium hydroxide, adjusting PH to be approximately equal to 7, preparing primary powder by sintering, and pre-sintering the primary powder for 3 h at 1000 DEG C to prepare cathode powder. The cathode material has advantages that excellent electrocatalytic activityis kept, cathode oxygen vacancy solubility, material stability and low-temperature performance are increased, and better thermal matching with the proton conductor electrolyte material is achieved, sothat the proton conductor SOFC is endowed with excellent low-temperature performance and stability.

The invention relates to an infrared stealth thin film with spectral selectivity and low emission rate. The infrared stealth thin film is of a multi-layer superimposed structure; the multi-layer superimposed structure contains a periodically-laminated structure which is formed by alternately superimposing high-refractive index material layers and low-refractive index material layers; the thicknesses of the film layers in the multi-layer superimposed structure are randomly distributed between 100 and 900nm; and the optical thicknesses of a certain number of film layers in the multi-layer superimposed structure are approximate to lambda/4, wherein lambda is an arbitrarily wavelength in infrared window bands. The preparation method of the thin film includes the following steps that: a substrate is cleaned; a Ge thin film is plated on the substrate by means of sputtering and through adopting a radio frequency magnetron sputtering method; and a MgF2 thin film is plated on the high-refractive index material layer by means of sputtering and through adopting a radio frequency magnetron sputtering method; the previous steps are repeated for a plurality of periods, and alternate control on designed thicknesses is utilized in combination, and therefore, the infrared stealth thin film with spectral selectivity and low emission rate can be obtained. The preparation method of the infrared stealth thin film of the invention has the advantages of simple preparation process, high repeatability, low equipment requirements, excellent product performance and favorable application effect.