94results about How to "Increased superplasticity" patented technology

The invention relates to a nanometer zirconium oxide thermal barrier coating and a preparation method thereof. The nanometer zirconium oxide thermal barrier coating is characterized by comprising an adhesive layer and a ceramic layer, wherein NiCrAlY is prepared on the adhesive layer by adopting supersonic flame spraying and comprises the following components in percentage by weight: 20-30% of Cr, 4.0-10% of Al, 0.3-0.7% of Y, and the balance of Ni; a ZrO2/Y2O3 layer is prepared as the ceramic layer by adopting plasma spraying, the ceramic layer is a nanometer zirconium oxide layer comprising5%-8% of partially stable yttrium oxide, and zirconium oxide powder is at a nanometer grade. The oxidation-resisting thermal barrier coating is prepared on a metal surface by combining the supersonic flame spraying with the plasma spraying, has better combining capacity with a base body and both thermal shock resistance and thermal insulation superior to those of a common ZrO2/Y2O3 thermal barrier coating.

Disclosed is an electroplating diamond tool with high hardness and high wear resistance. The invention is formed by covering a coating of nano nickel-cobalt material on a green body of the diamond tool. The method of the tool comprises preparing electroplating liquid, preparing before electroplating of the green body of the diamond tool, and electroplating the green body of the diamond tool after the preparation. When electroplating the green body of the diamond tool after the preparation, the green body of the diamond tool is electroplated with the nano nickel-cobalt material by the utilization of the method of impulse electroplating. The electroplating liquid of the invention is formed by components of nickel sulfate, nickel chloride, cobalt sulfate, grain refiner, dodecyl sodium sulfate, boracic acid and the like. The tool has high hardness and high wear resistance, and thereby the service life is long. Further, the invention has the advantages of short manufacture period.

The invention provides a preparation process of a Ti2AlNb/TA15 bi-metal titanium alloy composite hollow structure part. The Ti2AlNb/TA15 bi-metal titanium alloy composite hollow structure wing type component is prepared through the steps of blank preparation, surface treatment, welding stop agent coating, superplastic forming/diffusion bonding, cooling, out of a furnace and the like. The superplastic forming/diffusion bonding process method of the dissimilar material hollow structure part breaks through the key technology of the multi-layer hollow structure prepared by combining a Ti2AlNb intermetallic compound and an ordinary titanium alloy, the high-temperature resisting characteristic of the Ti2AlNb intermetallic compound and the good superplasticity of the TA15 titanium alloy are givento full play, structure weight losing is achieved, the guided missile thrust-weight ratio is increased, the application of the Ti2AlNb intermetallic compound to types is promoted, the material application range is expanded, the material utilization rate is increased, and the cost is reduced.

The invention discloses a Mo-Si-B-W multi-phase composite material, which is prepared with raw materials of the following atom percentages: 5-25 percent of silicon, 1-10 percent of tungsten, 5-30 percent of boron, and the resting being molybdenum. The mass purity of the silicon is no less than 98 percent, the mass purity of the tungsten is no less than 99 percent, the mass purity of the boron is no less than 99 percent, and the mass purity of the molybdenum is no less than 99 percent. The invention also discloses a preparation method of the Mo-Si-B-W multi-phase composite material. Mechanicalalloy and hot pressure sintering are adopted in the method to prepare the Mo-Si-B-W composite material, the method has the advantages of low energy consumption, short cycle and the like, and tungstenpowder is introduced into an Mo-Si-B composite material system so as to increase the high-temperature strength of the material and improve the reliability of the material in use. The composite material prepared in the method has a uniform and fine microstructure, the tensile strength of the composite material at 1400 DEG C is 400-460MPa, and the tensile elongation of the composite material is up to 400 percent.

The invention discloses a titanium alloy capable of resisting high temperature higher than 600 DEG C. The chemical elements of the titanium alloy are 5.5 to 7.0 percent by weight of Al, 2.5 to 4.0 percent by weight of Sn, 1.0 to 3.0 percent by weight of Zr, 1.0 to 3.0 percent by weight of Mo, 1.5 to 3.0 percent by weight of Nb, 0.10 to 0.40 percent by weight of Si, 0.05 to 1.0 percent by weight of Ce, 0.1 to 5.0 percent by weight of Ta, 0.1 to 2.0 percent by weight of C, 0.1 to 2.0 percent by weight of B and the balance of Ti and other inevitable impurities. The titanium alloy can be used under the temperature higher than 600 DEG C, and guarantees excellent mechanical properties under the high temperature at the same time.

Disclosed is a process for preparing short process fine crystalline superplasticity materials, which is characterized in that: cast alloy is used as a starting material for carrying out the agitation and friction processing after the homogenization heat treatment, and a bulky, loose and uneven cast structure is changed into an even and compact fine crystalline superplasticity structure.

The invention discloses a nanophase ceramic heat-insulation window membrane which is of a composite structure. The nanophase ceramic heat-insulation window membrane comprises a wear-resistant layer (1), a base membrane layer (2), a nanophase ceramic heat-insulation adhesive layer (3), a function membrane layer (4), a pressure sensitive adhesive layer (5) and a protection membrane layer (6), and the layers are composited into a whole; the wear-resistant layer (1) is combined on one surface of the base membrane layer (2) through ultraviolet light polymerization; the nanophase ceramic heat-insulation adhesive layer (3) is combined on the other surface of the base membrane layer (2) through thermocuring; one surface of the function membrane layer (4) is composited on the outer surface of the nanophase ceramic heat-insulation adhesive layer (3); the pressure sensitive adhesive layer (5) is combined on the other surface of the function membrane layer (4) through thermocuring; the protection membrane layer (6) is composited on the outer surface of the function membrane layer (4). The layers produce a synergistic effect, infrared rays can be selectively blocked, the thermal radiation of sun is blocked in summer to reduce the energy consumption of refrigeration of an air conditioner, and the loss of internal heat is blocked in winter to lower the heating cost, so that the nanophase ceramic heat-insulation window membrane has a green energy-saving effect.

The invention relates to the technical field of aluminum alloy processing, in particular to a preparation method of an aluminum alloy plate for aviation. The aluminum alloy comprises the following chemical components of, in percentage by mass, 0.05%-0.2% of zirconium, 0.05%-0.2% of scandium, 3.0%-6.0% of zinc, 3.0%-6.0% of magnesium, 3.0%-4.0% of copper, 0.2%-0.4% of silver, 0.05%-0.2% of lithium,1.0%-1.5% of manganese, 0.8%-1.5% of silicon, 0.20%-0.40% of titanium, 0.05%-0.1% of ruthenium, and the balance aluminum and inevitable impurities, and the content of the impurities is controlled tobe 0.15% or below; and an aluminum alloy melt is prepared according to pre-prepared materials, ultrasonic vibration is adopted in a refining process to refine grains, and then the aluminum alloy platefor the aviation is obtained through pouring, homogenization, extrusion, solid solution treatment, pre-stretching and three-stage aging treatment. According to the corrosion resistance aluminum alloyplate for the aviation and the preparation method of the corrosion resistance aluminum alloy plate, the Vickers hardness of the prepared aluminum alloy plate ranges from 175 Hv to 190 Hv, the yield strength ranges from 520 MPa to 562 MPa, the tensile strength ranges from 605 MPa to 656 MPa, the elongation ranges from 9.4% to 12%, the overall performance is excellent, and the aluminum alloy plateis particularly suitable for being used in the aerospace field.

The invention relates to a superplastic magnesium alloy and a preparation method thereof and belongs to the technical field of magnesium alloys. The magnesium alloy comprises the following components in percentage by weight: 10-30wt.% of Zn, 10-15wt.% of Er, and the balance of Mg, wherein Zn and Er are taken as main alloying elements and the ratio of Zn/Er is 1-2. The magnesium alloy is prepared by a melting process and an extruding process. The alloy has good plasticity at an initial strain rate of 0.5-5mm/min at 100-150 DEG C and shows good superplasticity in a low temperature range from 175 to 300 DEG C. The alloy is a potential magnesium alloy material which can be applied to superplastic forming and processing.

The invention discloses a preparation method of a superplastic aluminum-based composite material plate. The method comprises the following steps: carrying out pre-rolling heat treatment including solid solution and overaging on a to-be-processed aluminum-based composite material, and turning and peeling the surface of the aluminum-based composite material after heat treatment until the surface is flat; and then carrying out multi-pass medium-temperature rolling, conducting homogenizing heat treatment before each pass of rolling, and stretching and straightening the rolled plate. According to the method, heat treatment before rolling and medium-temperature rolling machining forming are combined so that matrix grains are substantially refined, and the material forming rate is increased; the in-situ nano-particle reinforced phase TiB2 is added into aluminum alloy for pinning and rolling a grain boundary to prevent grain growth, the thermal stability is good, and the effect of suppressing the grain growth and cavity generation of grains in high-temperature deformation is achieved; and the longitudinal elongation of the plate can reach 350%-600% under the deformation process conditions of 400-475 DEG C and 10<-3>-10<-4>/s, and the high-temperature superplasticity is excellent.

The invention provides a method for improving superplasticity of a semi-stable beta titanium alloy. The method is used for preageing treatment of the semi-stable beta titanium alloy. According to the method, the semi-stable beta titanium alloy is subjected to preageing treatment for 20-70 min at the temperature of 440-545 DEG C, a certain quantity of alpha phases are separated out from the semi-stable beta titanium alloy, the alpha phases are separated out in a beta crystal boundary position firstly, the hardness of the alpha phases is higher than that of beta phases, the alpha phases with high hardness perform stress concentration relative to matrix beta phases, beta-phase grains are fined to a certain extent, the finer the crystal grains are, the better the superplasticity is, and the superplasticity of the semi-stable beta titanium alloy is further improved. The elongation of the treated semi-stable beta titanium alloy reaches 361.8% and is increased by 167.8% by comparison with the elongation of an untreated semi-stable beta titanium alloy.

The invention relates to a preparation method of a high-temperature memory alloy, in particular to a preparation method of a superplastic Ni-Mn-Ga-Ta high-temperature memory alloy. According to the method, the high-temperature superplastic Ni53Mn25Ga21Ta1 alloy is obtained by material taking, vacuumizing, smelting, adding of an Mn element for continuous smelting, cleaning, heat insulation and quenching in water. The Ni53Mn25Ga21Ta1 alloy prepared through the preparation method has the advantages of high toughness, high intensity, high phase change temperature and the like, and a new idea is expanded for application of high-temperature and high-plasticity shape memory alloys.

The invention relates to a magnesium alloy plate manufacturing technology. Based on existing mature conventional magnesium alloy which is good in comprehensive performance but cannot completely meet the plate requirement of an automobile body, a micron quasi-crystal intermediate alloy online mixed melting technology, a magnesium alloy plate cast rolling technology and a dynamic recrystallization hot rolling technology are adopted to modify the magnesium alloy and enable the performance of the magnesium alloy to be improved. By means of the producing method, the production cost can be remarkably reduced, the performance of the plate can be improved, and index can be closer to the requirement for sheet metal parts in the automobile industry.

A technology for producing superfine refined steel includes such steps as tempering the martensitic steel, plastic deforming and annealing to fine the ferrite grains. The resultant steel features high strength and toughness and low cost of production.

The invention discloses a processing method for realizing super high plasticity performance of a titanium alloy welded joint, and belongs to the technical field of titanium alloy welding. The processing method includes the steps that firstly, hydrogenation treatment is conducted on a titanium board to be welded in a pure hydrogen atmosphere; then stirring friction welding is conducted on the titanium board subjected to the hydrogenation treatment to make a welding nugget to be of a tiny laminated structure; and super plasticity tensile deformation is conducted on a joint welding nugget after stirring friction welding, a part of a base metal and the entire welded joint, so that entire super plasticity processing of a titanium alloy workpiece is realized. Through the processing method for realizing the super high plasticity performance of the titanium alloy welded joint, the super plasticity of the titanium alloy welded joint can be obviously improved, the super plasticity temperature and flow stress are lowered, the difficulty of super plasticity forming and the welding cost are lowered greatly, the mechanical performance of a super plasticity forming component is improved, and thesuper plasticity forming of the whole joint is realized; and the processing method for realizing the super high plasticity performance of the titanium alloy welded joint particularly adapts to the super plasticity forming and high temperature forming of the titanium alloy welded joint, and can be applied to manufacture large-scale titanium alloy entire components, partial forming components and the like in space flight and aviation field.

The present invention provides a superplastic aluminum alloy in which fine particles not substantially dispersion hardening are dispersed in a sufficient amount to effect grain boundary pinning to suppress crystal grain growth during hot working thereby ensuring manifestation of superplasticity over wide ranges of working temperature and strain rate. According to the present invention, a superplastic aluminum alloy contains ceramic particles having an average particle size of from 10 nm to 500 nm in an amount of from 0.1 vol % to 5 vol % and a process of producing a superplastic aluminum alloy, comprises the steps of: hot working an aluminum alloy ingot containing ceramic particles having an average particle size of from 10 nm to 500 nm in an amount of from 0.1 vol % to 5 vol % with a working degree of from 10% to 40% at a temperature of 400° C. or higher; heat-treating at a temperature of 400° C. or higher; and hot-working with a working degree of 40% or more at a temperature of lower than 400° C.