32results about How to "Improve thermal cycle life" patented technology

The invention relates to an anti-CMAS-corrosion ultrahigh-temperature-resistant long-service-life thermal barrier coating and a preparation method thereof. The thermal barrier coating is sequentially provided with a binding layer, a first ceramic layer and a second ceramic layer on a matrix from bottom to top, the binding layer is made of an MCrAlX alloy, M refers to Ni, or Co or a composition of Ni and Co, X refers to one of or a composition of two of Y, Hf, Si and Pt, the first ceramic layer is made of YSZ, and the second ceramic layer is rare earth zirconate with Sc2O3. The preparation method includes that an electron beam physical vapor deposition method or an atmosphere plasma spraying method are adopted. Sc2O3 is doped in a rare earth zirconate coating, so that heat conductivity of the coating can be further lowered, toughness of the coating is improved, anti-CMAS-corrosion capability of the coating is improved, thermal cycling life of the coating can be prolonged, and high-temperature stability of the coating under CMAS coupling action can be improved.

The invention belongs to the field of thermal spraying, and relates to a high-temperature oxidation resistant coating on a niobium alloy surface and a preparation method of the high-temperature oxidation resistant coating. The coating is in a dual-layer structure with a bottom coating Mo1-xWx(Si1-y-zAlyBz)2 and a surface coating Mo1-xWx(Si1-y-zAlyBz)2-(10-20)%wt HfSi2, and prepared on a niobium alloy matrix surface by a high-energy plasma spraying process, wherein a bottom coating powder material Mo1-xWx(Si1-y-zAlyBz)2 is prepared by a self-propagating process, and the spherical particles meeting the requirements of the spraying process are obtained by applying a plasma spheroidizing process; surface coating powder materials Mo1-xWx(Si1-y-zAlyBz)2 and HfSi2 are mixed evenly in a mechanical mixing manner. The coating has excellent high-temperature oxidation resistance at 1500-1800 DEG C, and can be applied to high-temperature protection of niobium alloy parts.

The invention discloses a pyrochlore structural rare-earth zirconate material system capable of being used for a heat barrier coating. The chemical composition of the material is (0.5-x)R'2O3-0.5Sm2O3-xR''2O3-2ZrO2, wherein x is more than 0 and less than or equal to 0.25; the R' is rare-earth elements or composition thereof, the ion radius of which is greater than that of Sm; and R'' is rare-earth elements or composition thereof, the ion radius of which is smaller than that of Sm. The material provided by the invention has low thermal conductivity, high thermal stability and high-temperature sintering resistance; the thermal expansion performance of the material is stable compared with a single pyrochlore structural material; and the material is favorable for reducing thermal stress generated by mismatching of thermal expansion coefficients in the thermal cycle process, and can prolong the thermal cycle life of the coating. Because of good high-temperature phase stability, the pyrochlore structural rare-earth zirconate material can be used for designing and preparing a novel high-temperature heat barrier coating material, the use temperature of which is below 1,550 DEG C.

A method for optimizing the thermal cycle and random vibration life of an LCCC chip solder joint of car networking is provided. The thermal fatigue life and random vibration life of LCCC solder jointsare calculated by establishing the finite element simulation model of LCCC solder joints and performing solder joint thermal cyclic loading and random vibration loading stress-strain finite element analysis simulation analysis. The method further comprises the steps of selecting the pad width, pad length, clearance height and steel net thickness as design variables, in order to maximize the thermal fatigue life and random vibration life of solder joints, carrying out the multi-objective reliability optimization design of LCCC solder joints by means of orthogonal test and grey relational analysis, and finally designing the parameter combinations making both the thermal cycle life and random vibration life of solder joints optimal. The method is simple and facilitates the later parameter optimization design and the optimized calculation results are ideal, and the method provides scientific guidance for the LCCC solder joint structure parameter design.

The invention relates to an aluminum-silicon carbide composite material with ultrahigh volume fraction and a preparation method thereof. The aluminum-silicon carbide composite material reaches ultrahigh silicon carbide volume fraction, has low preparation cost, convenient process, good combination property and high reliability and can realize the near-net-shape forming of complex shapes and largesizes. The aluminum-silicon carbide composite material comprises the following components by volume percent: 46%-55% of green silicon carbide coarse powder, 16%-23% of green silicon carbide fine powder, 8%-12% of green silicon carbide micro powder, 8%-27% of metallic aluminum, 1.9%-2.7% of metallic silicon and 0.1%-0.3% of metallic magnesium, wherein the green silicon carbide coarse powder, the green silicon carbide fine powder and the green silicon carbide micro powder respectively have the grain diameters of 120-210 micrometers, 30-63 micrometers and 6-12 micrometers.

The invention relates to a high-performance Sc-Y-co-doped zirconium oxide thermal protection coating and a preparing method thereof. The coating is prepared on a base body by spraying Sc-Y-co-doped zirconium oxide powder through a supersonic plasma spraying technology, wherein the parameters of the supersonic plasma spraying technology are as follows: the current is 300-600A, the voltage is 100-180V, the primary gas argon flow rate is 50-200slpm, the secondary gas hydrogen flow rate is 8-30slpm, the spraying distance is 80-150mm, the powder delivery amount is 20-60g/min, and the moving speed of a spray gun is 500-800mm/s. The prepared coating has a single tetragonal structure with even components, is more stable than a yttrium oxide part which is widely applied at present, has heat conductivity which is lower than that of the zirconium oxide coating and has better high-temperature stability. The coating can greatly increase the working efficiency and service life of the metal hot-end components of high-end equipment, such as aircraft engines and heavy-duty gas turbines.

The invention discloses a double-layer anti-oxidation bonding bottom layer high-temperature sealing coating and a preparation method thereof, and belongs to the technical field of aero-engine coatings. The double-layer anti-oxidation bonding bottom layer high-temperature sealing coating structurally comprises a CoNiCrAlY anti-oxidation bottom layer, a CoNiCrAlY middle bonding transition layer anda ZrO2.Y2O3 ceramic sealing layer. CoNiCrAlY system materials with two particle sizes are adopted to spray the anti-oxidation bottom layer and the middle bonding coating, ZrO2.Y2O3 ceramic system materials containing hexagonal boron nitride and polyester are adopted to spray a wearable sealing surface layer, the high-temperature sealing coating is obtained, the bonding strength can be improved by10MPa or above, the high-temperature oxidation resistance can be improved by 15% or above, and the thermal cycle life can be prolonged by 25% or above; and the problems that layers of an existing high-temperature sealing coating are not matched, the bonding performance is poor, the erosion resistance and the scraping resistance are poor, and large coating blocks are peeled off are solved.

A bond coating material providing unexpectedly high thermal cyclic fatigue resistance and sulfidation resistance, and unexpectedly prolonged thermal cycle life in high temperature environments of gas turbine engine components with and without the presence of sulfur contains: a) 10% to 30% by weight chromium, b) at least one of tantalum and molybdenum in a total amount of 3% to 15% by weight, c) 5% to 13% by weight aluminum, d) 0.1% to 1.4% by weight silicon, e) 0.1% to 0.8% by weight yttrium, f) 0% to 1.2% by weight carbon, g) 0% to 1% by weight dysprosium, h) 0% to 1% by weight cerium, i) the balance being nickel, and the percentages of a) to i) adding up to 100% by weight. The total amount of tantalum and molybdenum, and the amounts of aluminum and silicon are each critical for avoiding delamination of a top coat from a bond coat.

The invention relates to a preparation method of a high-entropy rare earth aluminate thermal protection coating, and belongs to the technical field of thermal protection coatings. The preparation method comprises the following steps: firstly, preparing a NiCrCoAlY bonding layer on a substrate with the surface roughness of 4-8 microns by adopting a thermal spraying process, and then, directly preparing a high-entropy rare earth aluminate layer on the NiCrCoAlY bonding layer by adopting an atmospheric plasma spraying process, or firstly, preparing a YSZ or Al2O3 intermediate layer on the NiCrCoAlY bonding layer by adopting the thermal spraying process, and then, preparing the high-entropy rare earth aluminate layer on the NiCrCoAlY bonding layer by adopting the high-entropy rare earth aluminate layer on the NiCrCoAlY bonding layer by adopting the high-entropy rare earth aluminate layer. And preparing a high-entropy rare earth aluminate layer on the intermediate layer by adopting an atmospheric plasma spraying process, so as to form the high-entropy rare earth aluminate thermal protection coating on the substrate. According to the method disclosed by the invention, the high-entropy rare earth aluminate ceramic thermal protection coating with low porosity, high deposition rate and good thermal shock resistance can be obtained by optimizing process conditions, and the requirement of long-term use under a high-temperature service condition can be met.