37results about How to "High temperature capacity" patented technology

The invention belongs to the field of nickel-based high-temperature alloys, and particularly discloses a nickel-cobalt-based high-temperature alloy with favorable structure stability (no Ni3Ti phase separation) and easiness for processing. The nickel-cobalt-based high-temperature alloy can be processed by using a casting and forging (C and W) process and a powder metallurgy process and is mainly suitable for bearing parts with high stress at the high temperature of 750DEG C, such as a turbine disc and a blade material in an aeroengine. The nickel-cobalt-based high-temperature alloy comprises the following chemical components in percentage by weight: 0.1-10 percent of Ru, 22-35 percent of Co, 10-20 percent of Cr, 0.10-5 percent of Ta, 0.10-5 percent of W, 0.10-5 percent of Mo, 3-10 percent of Ti, 0.2-5 percent of Al, 0.01-0.10 percent of Zr, 0.10-1 percent of V, 0.10-5 percent of Nb, 0.1-2 percent of Hf, 0.005-0.15 percent of C, 0-2 percent of Fe, 0.01-0.1 percent of Mg, 0.05-0.50 percent of Mn, 0.005-0.1 percent of B and the balance Ni. According to the nickel-cobalt-based high-temperature alloy disclosed by the invention, the Ru element is added under the existence of a TMW alloy containing Co and Ti with high contents; and under the condition that the high temperature bearing capacity of the alloy is ensured, the structure stability (no Ni3Ti phase separation) and the processability of the alloy can be remarkably improved.

The invention discloses gamma'-phase intensified cobalt-based superalloy and a preparation method thereof, and belongs to the field of superalloy. The gamma'-phase intensified cobalt-based superalloyis prepared from the following alloy chemical components in percentage by weight: 3 to 6 percent of Al, 6 to 20 percent of W, 2 to 6 percent of Ti, 2 to 6 percent of Ta, 18 to 38 percent of Ni, 0 to 10 percent of Cr, 0 to 5 percent of Mo, 0 to 2 percent of Nb, 0 to 2 percent of Si and the balance of Co. The preparation method is characterized by melting by adopting a vacuum arc furnace, carrying out solid solution heat treatment at 1250 to 1300 DEG C, and carrying out aging heat treatment at 900 to 1150 DEG C. The gamma'-phase intensified cobalt-based superalloy disclosed by the invention is intensified by a gamma' phase having an L12 crystal structure and has a cubic shape, the volume fraction is greater than 65 percent, and the gamma'-phase intensified cobalt-based superalloy is uniformly distributed in a gamma matrix having an A1 crystal structure. A Gamma / gamma' two-phase structure of the gamma'-phase intensified cobalt-based superalloy disclosed by the invention stably exists at 900 to 1150 DEG C, no secondary phase is separated out, and the gamma'-phase intensified cobalt-based superalloy is a candidate material for hot end components of an aircraft engine and an industrial gas turbine.

The invention provides a nickel-based alloy, comprising: 7wt%-8wt% cobalt; 12wt%-13wt% chromium; 6.35wt%-6.65wt% aluminum; 5.25wt%-5.75wt% tantalum; 5.25wt% %~5.75wt% tungsten; 0.57wt%~0.63wt% hafnium; 0.04wt%~0.06wt% carbon; 0.003wt%~0.005wt% boron; 0.02wt%~0.10wt% silicon; balance of nickel. In this application, by balancing the content of strengthening elements W, Mo, Ta, Al, Co and other elements in the alloy, and increasing the content of Cr, the alloy has excellent oxidation resistance, corrosion resistance and temperature-bearing performance. It can maintain good structural stability and does not contain Re, which reduces the cost of the alloy.

The invention discloses a high-strength refractory nickel-based superalloy and a preparation method thereof. By optimizing the alloy composition, vacuum induction smelting, electroslag remelting, vacuum consumable remelting, forging and heat treatment are adopted, and the processes of each process are controlled. The parameters ensure the feasibility of the engineering application of the high-strength refractory nickel-based superalloy, so as to obtain a high-strength refractory nickel-based superalloy with high strength, high microstructure stability and good hot workability. , its tensile strength and durability at 650 °C are better than those of GH4169 alloy, and its tensile strength and durability at 750 °C are better than those of GH738 alloy.

The invention belongs to the technical field of new materials, and provides a heat-resistant cast austenitic stainless steel with excellent high-temperature comprehensive properties, which is mainly used in automobile engine exhaust system components of which the exhaust temperature exceeds 1000 DEG C, including exhaust manifolds, turbine casings and the like. The heat-resistant cast austenitic stainless steel comprises the following alloy components in percentage by mass: 0.1%-0.6% of C, 0.1%-0.5% of N, 0.4%-1.5% of Si, less than 1.5% of Mn, 17.5%-22.5% of Cr, 8.0%-13.0% of Ni, 1.0%-3.0% of Nb, less than 5.0% of W, less than 6.5% of Mo and the balance of matrix element Fe and impurity elements, including less than 0.04% of P, less than 0.03% of S, less than 0.04% of O and less than 0.05% of Al. The heat-resistant austenitic stainless steel is produced by a casting method without later-period heat treatment, and has the advantages of lower production cost, higher temperature resistance and higher durability as compared with like heat-resistant cast steel.

The invention discloses an Al-Re-Nb ternary alloy containing elements with high melting point and low boiling point and a preparation method thereof, wherein the melting point of the Re element is 3180°C, the melting point of the Nb element is 2467°C, and the boiling point of the Al element is 2467°C ℃. Al-Re-Nb ternary alloys are smelted by using three elements of Al, Re and Nb with a purity of 99.99%. The preparation process of the alloy of the invention is simple and convenient, and the price is low. The amount of melting loss of the alloy prepared by the invention is greatly reduced, the actual density of the obtained alloy is close to the theoretical density, and the melting loss rate of the alloy is less than 1.9%.

The patent of the present invention relates to a process method for improving the quality of GH4151 inertial friction welding seam, which belongs to the field of welding technology of GH4151 alloy used for core rotor parts and disk shaft parts of aero-engines; the process method includes three-stage pressure method of inertial friction welding , Before welding, the machining allowance is reserved for the inside and outside of the welding boss and the final part size. After the welding is completed, the flash removal and heat treatment are completed within a limited time, and the defect detection is carried out in sequence. The three-stage pressure process method can prevent the tip cracks of the welding flash from penetrating into the weld matrix and make the flash continuous. Before the welding, the machining allowance is reserved on the inside and outside of the welding boss and the final part size, which can completely remove the possible flash edge defects and ensure the final weld seam quality of the parts. The invention also utilizes different detection sequences to carry out overall quality inspection on the surface of the weld seam, the shallow surface and the inside of the weld seam, thereby effectively improving the quality of the weld seam and the level of defect detection.

The invention provides nickel-base superalloy and a preparation method thereof, and in particular relates to powder metallurgy nickel alloy with high stability, and articles made from the powder metallurgy nickel alloy. The nickel-base superalloy is prepared from the following components by mass percent: 18.5-19.5% of Co, 12.75-13.25% of Cr, 2.8-3.2% of Al, 3.5-3.9% of Ti, 3.75-4.25% of W, 3.75-4.25% of Mo, 0.9-1.1% of Ta, 1.1-1.3% of Nb, 0.17-0.23% of Hf, 0.04-0.06% of C, 0.003-0.015% of B, 0.03-0.07% of Zr and the balance of Ni. The superalloy designed by the invention has better structure stability and high-temperature strength, and the temperature tolerance of the alloy is further improved.

The invention provides a nickel-based high temperature alloy and a preparing method thereof, and specifically a metallurgical nickel alloy with powder not containing the element Nb and objects manufactured from the metallurgical nickel alloy. The nickel-based high temperature alloy comprises, by mass, 12.5-13.5% of Co, 13.75-14.25% of Cr, 2.8-3.2% of Al, 3.8-4.2% of Ti, 3.75-4.25% of W, 3.75-4.25% of Mo, 2.8-3.2% of Ta, 0.17-0.23% of Hf, 0.04-0.06% of C, 0.003-0.015% of B, 0.03-0.07% of Zr and the balance Ni. The high temperature alloy has better structure stability and high-temperature strength, and temperature capability of the alloy is further improved.

The invention relates to the technical field of high-temperature alloys, in particular to a high-temperature alloy with low stacking fault energy, structural parts and applications thereof. The superalloy includes: C0.01%~0.09%, Co23.5%~27.5%, Cr11%~15%, W0.1%~1.8%, Al2.2%~2.6%, Ti3.5 %~5.5%, Nb0%~2%, Ta0%~2%, Mo2.1%~3.5%, B0.0001%~0.05%, Zr0.0001%~0.05%, Fe0%~2.5%, Mg0%~ 0.04%, the balance is Ni; the sum of the mass fractions of Nb and Ta≥0.8%. The superalloy of the present invention can take into account the service performance above 750°C and good thermal processing characteristics, and can be used as structural parts such as turbine disks, blades, casings, and combustion chambers for a long time.

The invention belongs to the technical field of new materials, and provides a nickel-based casting alloy and a preparation method thereof, which are mainly applied to high-temperature load-bearing structural parts of ramjet engines whose wall surface temperature reaches 1200°C, such as air intake structural parts. The alloy composition contains C: 0.1‑0.25%, Cr: 7.5‑10.7%, Co: 8‑12%, W: 8‑12%, Al: more than 6.25%, Ti: 0.75‑2%, Ta: 2‑3%, Hf: 0.8‑2.5%, Zr: 0.01‑0.15%, B: 0‑0.2%, and the remainder is matrix element Ni and impurity elements. The nickel-based casting alloy of the invention is produced by investment casting method, and after being subjected to standard heat treatment at 870°C / 16h, it has higher temperature bearing capacity and durability than similar casting superalloys.