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

A ceramic ring segment for a turbine engine that may be used as a replacement for one or more metal components. The ceramic ring segment may be formed from a plurality of ceramic plates, such as ceramic matrix composite plates, that are joined together using a strengthening mechanism to reinforce the ceramic plates while permitting the resulting ceramic article to be used as a replacement for components for turbine systems that are typically metal, thereby taking advantage of the properties provided by ceramic materials. The strengthening mechanism may include a ceramic matrix composite overwrap or plurality of overwraps designed to help prevent delamination of the ceramic plates when the ceramic article is in use by placing the plates in compression.

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 relates to a Re/Ru-containing monocrystal nickel-based superalloy with high temperature resistant capability and high creep resistance, belonging to a new material with a special purpose. The alloy consists of the following components in percentage by weight: 5.6-6.4% of Al, 7.2-8.2% of Ta, 2.2-3.2% of Cr, 2.5-3.5% of Mo, 6.5-7.5% of Co, 3.8-4.6% of W, 4.2-4.8% of Re, 2.8-3.5% of Ru, 0.05-0.15% of Hf and the balance of nickel. The monocrystal nickel-based superalloy has good high-temperature oxidation resistance and the advantages of high temperature resistant capability, high creep strength, long service life and the like, and is applicable to the production of blades of the hot-end components of aero-engines and gas turbines.

The invention provides a nickel-based alloy. The nickel-based alloy comprises 7-8wt% of cobalt, 12-13wt% of chromium, 6.35-6.65wt% of aluminum, 5.25-5.75wt% of tantalum, 5.25-5.75wt% of tungsten, 0.57-0.63wt% of hafnium, 0.04-0.06wt% of carbon, 0.003-0.005wt% of boron, 0.02-0.10wt% of silicon and the balance nickel. According to the invention, the alloy has excellent oxidization resistance, corrosion resistance and temperature bearing performance by balancing the contents of strengthening elements such as W, Mo, Ta, Al and Co in the alloy and improving the content of Cr. The nickel-based alloy can maintain good structure stability in a high-temperature environment and does not contain Re, and the cost of the alloy is lowered.

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 a high-temperature bearing structural member, such as an air inlet channel structural member, of a ramjet engine with the wall surface temperature reaching 1200 DEG C. The alloy comprises the following components of, by mass, 0.1%-0.25% of C, 7.5%-10.7% of Cr, 8%-12% of Co, 8%-12% of W, larger than 6.25% of Al, 0.75%-2% of Ti, 2%-3% of Ta, 0.8%-2.5% of Hf, 0.01%-0.15% of Zr and 0%-0.2% of B, and the balance a matrix element Ni and impurity elements. The nickel-based casting alloy is produced through adopting an investment casting method, and has higher temperature bearing capacity and durability than similar casting high-temperature alloys after being subjected to 870 DEG C/16 h of standard heat treatment.

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 high-strength creep-resistant high-temperature alloy and a preparation method thereof, and belongs to the technical field of metallurgy. The alloy comprises the following components in percentage by mass: 10.00%-12.00% of Cr, 12.00%-18.00% of Co, 5.50%-7.50% of W, 1.50%-3.50% of Mo, 3.00%-4.20% of Al, 3.00%-4.20% of Ti, 1.00%-2.20% of Nb, 0.40%-1.50% of Ta, 0.01%-0.04% of C, 0.01%-0.04% of B, 0.09%-1.20% of Zr, less than 0.10% of Hf and the balance of Ni, and the total mass percentage of gamma'phase forming elements Al, Ti, Nb and Ta in the high-temperature alloy is as follows: 9.5% < = (Al + Ti + Nb + Ta) < = 10.3%; the mass percentage content of a gamma'phase in the high-temperature alloy is 50%-55%, and the mass ratio of Al to Ti in the high-temperature alloy is that (Al/Ti) is larger than or equal to 0.9 and smaller than or equal to 1.0. The alloy and the disc piece of the alloy can be manufactured through the method, and the disc piece of the alloy can meet the requirements of future aviation turboshaft engines for high temperature resistance, high strength and creep resistance.

The invention relates to the technical field of high-temperature alloys, in particular to a high-temperature alloy with low stacking fault energy, a structural part and application of the high-temperature alloy. The high-temperature alloy comprises, in percentage by mass, 0.01%-0.09% of C, 23.5%-27.5% of Co, 11%-15% of Cr, 0.1%-1.8% of W, 2.2%-2.6% of Al, 3.5%-5.5% of Ti, 0%-2% of Nb, 0%-2% of Ta, 2.1%-3.5% of Mo, 0.0001%-0.05% of B, 0.0001%-0.05% of Zr, 0%-2.5% of Fe, 0%-0.04% of Mg and the balance of Ni, wherein the sum of the mass fractions of Nb and Ta is greater than or equal to 0.8%. The high-temperature alloy has both service performance at 750 DEG C or above and good hot working characteristics, and can be applied to structural parts such as a turbine disc, a blade, a casing and a combustion chamber for long-time use.

The invention provides a material for casting an exhaust manifold. The material for casting the exhaust manifold is composed of the following chemical ingredients of, in percentage by mass, 0.2-0.6% of C, 1.2-2.6% of Si, 0.1-0.5% of Al, 0.1-0.3% of Mn, 20-24% of Cr, 22-26% of Ni, 0.6-0.8% of Mo, 0.7-1.1% of Ba, 4-7% of Ce, 0.9-1.6% of N, 1.5-1.9% of Nb, 0.02-0.05% of P, 0.11-0.16% of S, 5-7% of Ti, 6-8% of V and the balance ferrum. The material for casting the exhaust manifold has the beneficial effects that (1), an appropriate amount of alloying elements of chromium, nickel, molybdenum, nitrogen, aluminum and silicon and the like are added in the exhaust manifold material, and the abrasive resistance and oxidation corrosion resistance of final exhaust manifold products are improved and enhanced to a certain extent; (2), automobile exhaust manifolds fabricated by the material for casting the exhaust manifold have higher temperature bearing capacity and durability, the quality of products is improved, the service life of products is prolonged, and to some extent, the cost is also saved.