31 results about "Inconel 625" patented technology

The present invention provides methods and apparatus to restore a blade leading edge on a gas turbine engine component such as an airfoil of a turbine blisk. The method utilizes welding image technology and power control systems in order to provide effective welding with superalloy materials such as Inconel 713 and Inconel 625. The method includes machining away a damaged leading edge and providing a repaired region through successive depositions of superalloy powder filler through laser fusion welding. Deposition material is added until the repaired region exceeds the original dimensions of the airfoil. The airfoil is then machined and finished to return it to original airfoil dimensions.

In the invention, a fixed-point temperature change curve is acquired through recording a temperature change when a molten pool passes through a middle position of a single-channel cladding layer during laser additional material forming process of Inconel 625 alloy. According to the fixed point temperature change curve, a peak temperature T of the fixed-point temperature change curve, an interceptt of a liquid phase line and a temperature curve, and an average cooling rate xi of a molten pool cooling stage are calculated. A laser additional material forming parameter of the Inconel 625 alloy is optimized, and finally a process parameter of columnar dendrites and the process parameter of equiaxed dendrites are obtained so as to realize adjustment and control of the Inconel 625 alloy dendrite morphology. A mechanical property of a formed part can be effectively increased.

The aging heat treatment process comprises the following steps that S1, the furnace temperature is increased to 1100-1160 DEG C, an Inconel 625 alloy is put in, heat preservation is conducted for (d * 0.6 + 30)-(d * 0.6 + 70) min, d is the straight product of the cross section of the Inconel 625 alloy, and the unit is mm; s2, the Inconel 625 alloy is taken out and put into water to be quenched, and the quenching water temperature ranges from 10 DEG C to 25 DEG C; s3, the Inconel 625 alloy subjected to primary quenching is put into the furnace at the temperature of 750 DEG C to 800 DEG C again, tensile stress is applied, heat preservation is conducted for 20 h to 40 h, and the stress level ranges from 100 MPa to 250 MPa; and S4, the Inconel 625 alloy is taken out, secondary quenching is conducted, and the quenching water temperature ranges from 10 DEG C to 25 DEG C. According to the method, the tensile stress is applied to the Inconel 625 alloy subjected to solution strengthening, creep aging heat treatment is conducted, the generation efficiency of the delta phase is improved, hundreds of and thousands of hours of heating is not needed, the practicability of the alloy is effectively improved, in the heat treatment process, due to application of the tensile stress, the forming speed of the delta phase is higher, the number of the delta phase is larger, and distribution is more uniform; the size is smaller, and the tensile strength is greatly improved.

The invention discloses a separation method for nonmetallic inclusions in an Inconel625-series high-temperature alloy, and belongs to the technical field of methods for researches on nonmetallic inclusions in metallic materials. A proper electrolyte is selected to electrolyze a high-temperature alloy test sample; a collected extract mixture is separated by virtue of a chemical method after electrolysis, and carbides are dissolved to completely and nondestructively extract fine oxide inclusions in the Inconel625-series high-temperature alloy; the obtained oxide inclusions are observed to have obvious particle shapes under a scanning electron microscope, and are proven to be Al and Mg containing composite oxide inclusions by energy spectrum analysis.

The invention relates to a preparation method of Inconel625 nickel-based alloy powder used for laser selective melting technology. The method combines vacuum electrode induction melting technology and ultrasonic tight-coupling atomization technology, adopts ultrasonic vibration classification and airflow classification, and The powders of different particle sizes are mixed to prepare Inconel625 nickel-based alloy powder suitable for laser selective melting technology. Compared with the prior art, the Inconel625 nickel-based alloy powder prepared by the present invention has the performance characteristics of high sphericity, uniform particle size distribution, low oxygen content, low impurity content, etc., and meets the performance requirements of laser selective melting technology for powder materials, Promote the development of metal additive manufacturing technology.

The invention relates to the technical field of arc-added metal materials, in particular to a high-strength and high-plastic single-phase Inconel 625 nickel-based alloy and a preparation method thereof. The invention discloses a high-strength and high-plasticity single-phase Inconel 625 nickel-based alloy, wherein the structure of the Inconel 625 nickel-based alloy is a single-phase columnar coarse-grained structure, and its grain size is 45-360 μm. In percentage terms, the grains have small-angle grain boundaries in a proportion of 15-33%. The invention also discloses a preparation method of the Inconel 625 nickel base alloy. The tensile strength of the Inconel 625 nickel-based alloy obtained according to this method is 720-730MPa, the yield strength is 390-415MPa, and the elongation is 54-63%. Compared with the traditional cast 625 nickel-based alloy, it significantly improves the strength and plasticity.

The invention relates to a surfacing welding wire, in particular to an Inconel 625 modified alloy surfacing welding wire and a preparation method thereof, and belongs to the technical field of anti-corrosion and anti-wear materials. The wire material comprises the following chemical components in percentage by mass: 18.0 to 25.0 percent of Cr, 6.0 to 12.0 percent of Mo, 0 to 3.0 percent of Fe, 0 to 1.0 percent of Co, 0 to 1.0 percent of Nb, 0 to 0.5 percent of Ti, 0 to 0.5 percent of Al, 0 to 0.5 percent of Mn, 0 to 0.5 percent of Si, 0 to 0.2 percent of La, 0 to 0.2 percent of Ce, 0 to 0.1 percent of C and the balance of Ni. The wire has good forging and cold-drawing process properties, the prepared surfacing layer has excellent high-temperature corrosion resistance and wear resistance, and the corrosion resistance, high-temperature oxidation resistance and wear resistance of boilers, especially garbage incinerator boilers, can be greatly improved.

The invention belongs to the technical field of alloy materials, and in particular relates to a novel high temperature resistant Cl ‑ Corroded nitrogen-containing low-nickel alloy and preparation method. A new type of high temperature resistant Cl ‑ The corroded nitrogen-containing low-nickel alloy, measured by mass percentage, comprises the following components: Ni: 42.0-46.0wt%, Cr: 20.0-26.0wt%, Mn: 7.0-8.0wt%, Si: 1.6wt% and below, Mo: 6.0‑8.0wt%, Cu: 0.5wt% or less, Co: 0.8‑1.0wt%, N: 0.12‑0.21wt%, Ti+Al=2.8‑3.0wt%; Ti / Al=1.0‑1.3, Nb: 6-7%, W: 2.0-3.0wt%, V: 1.25-1.55wt%, and the rest are Fe and inevitable impurities. The optimization of the alloy composition of the present invention enables the nitrogen-containing low-nickel alloy to have excellent Cl resistance at high temperature ‑ Corrosive, can replace Inconel 625 alloy, used in high temperature, high pressure chemical, energy and marine engineering fields, such as facing 900 ℃, Cl ‑ Corrosion of the energy storage medium in the solar heat storage tube.

The invention discloses a repair material and a repair method for directional solidification crystal turbine blade tip deep cracks, relates to the field of aero-engine blade maintenance, and solves the problem that existing repair materials are likely to generate micro-cracks. According to the technical scheme, the repair material for the directional solidification crystal turbine blade tip deep cracks is formed by fully mixing 35%-45% of Inconel 625 alloy powder and 55%-65% of Rene 142 alloy powder by mass. The repair method for the directional solidification crystal turbine blade tip deep cracks comprises the steps that after a high-pressure turbine working blade is decomposed, flaw detection is conducted firstly, the crack position is determined, and a groove is formed; then, the aboverepairing material is adopted for laser additive manufacturing; a repair area is polished, and the blade is placed in a vacuum furnace for annealing treatment; and finally, flaw detection is conductedon the blade. The repair material and the repair method are suitable for repairing the deep cracks of the blade tip of the directional solidification nickel-based superalloy DZ125 turbine rotor blade.

The invention discloses a preparing method for a composite valve. A metal material Inconel 625 pipe is arranged in the inner wall of the valve to be combined, and a certain gap is kept between the Inconel 625 pipe and the inner wall of the valve; an explosive layer is laid in the Inconel 625 pipe, the explosive layer is attached to the inner wall of the Inconel 625 pipe, the amount of explosive is gradually reduced from bottom to top, the explosive dosage is controlled, the Inconel 625 pipe can sequentially move towards the inner wall of the valve in an accelerated mode from bottom to top through the function of the explosive energy in the explosive combining process, a certain bent angle is formed when the outer wall of the Inconel 625 pipe makes contact with the inner wall of the valve, and then the outer wall of the Inconel 625 pipe and the inner wall of the valve are combined. The preparing method has the advantages that the inner wall of the valve can be combined with abrasion resisting materials, the combination effect is good, and cost is low.