CN111607720A - Powder nickel-based high-temperature alloy and preparation method thereof - Google Patents

Powder nickel-based high-temperature alloy and preparation method thereof Download PDF

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CN111607720A
CN111607720A CN202010407369.XA CN202010407369A CN111607720A CN 111607720 A CN111607720 A CN 111607720A CN 202010407369 A CN202010407369 A CN 202010407369A CN 111607720 A CN111607720 A CN 111607720A
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percent
alloy
temperature
extrusion
powder
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李云平
滕剑威
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Central South University
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Central South University
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/04—Making non-ferrous alloys by powder metallurgy
    • C22C1/0433—Nickel- or cobalt-based alloys
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C30/00—Alloys containing less than 50% by weight of each constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon

Abstract

The invention discloses a powder nickel-based high-temperature alloy and a preparation method thereof, wherein the alloy comprises the following elements in percentage by mass: 15.0 to 25.0 percent of Cr; 15.0 to 25.0 percent of W; 9.0 to 15.0 percent of Co; 0.5 to 3.0 percent of Mo; 0.5 to 4.0 percent of Al; 0.5 to 1.5 percent of Ti; 0.001 to 0.20 percent of C; sc is 0.001 to 0.20 percent; 0.001 to 0.50 percent of Y; the balance being Ni. The invention fully utilizes the coordination among the strengthening elements, the antioxidant elements and the trace elements of the alloy, optimizes the content of other alloy elements by balancing thermodynamic calculation, comprehensively improves the mechanical property of the alloy on the basis of ensuring the oxidation resistance of the alloy, particularly synchronously improves the strength and the plasticity in high-temperature property, and meets the requirements of a turbine disc and a hot end part of a new generation of aeroengine.

Description

Powder nickel-based high-temperature alloy and preparation method thereof
Technical Field
The invention belongs to the technical field of alloys, and particularly relates to a powder Ni-based high-temperature alloy and a preparation method thereof.
Background
The Ni-based high-temperature alloy is a key material of important parts such as a turbine disc, a hot-end part and the like on an aeroengine. With the continuous development and improvement of thrust level of an aircraft engine and the flight speed of a missile, the currently used Ni-based high-temperature alloy gradually cannot meet the requirements of higher and higher service temperature and the like, and is easy to have defects of oxidation, cracks and the like, so that the service life and the service performance of the aircraft engine are influenced. Therefore, research and development of a Ni-based superalloy with excellent mechanical properties are required to meet the higher use requirements of an aircraft engine.
Disclosure of Invention
The invention aims to solve the technical problem of overcoming the defects and shortcomings in the background art and provide a Ni-based high-temperature alloy with excellent mechanical property and oxidation resistance and a preparation method thereof.
In order to solve the technical problems, the technical scheme provided by the invention is as follows:
the powder nickel-based high-temperature alloy comprises the following elements in percentage by mass: 15.0 to 25.0 percent of Cr; 15.0 to 25.0 percent of W; 9.0 to 15.0 percent of Co; 0.5 to 3.0 percent of Mo; 0.5 to 4.0 percent of Al; 0.5 to 1.5 percent of Ti; 0.001 to 0.20 percent of C; sc is 0.001 to 0.20 percent; 0.001 to 0.50 percent of Y; the balance being Ni.
Further, the contents of Mo and W are as follows: 1.3 to 1.9 percent of Mo; 16.0 to 19.0 percent of W.
Further, the contents of Al and Ti are as follows: 1.9 to 2.3 percent of Al; 0.5 to 0.7 percent of Ti.
Further, the contents of Cr and Y are as follows: 19.0 to 24.0 percent of Cr; 0.03 to 0.12 percent of Y.
Further, the contents of Sc and C are as follows: sc is 0.02 to 0.05 percent; 0.11 to 0.14 percent of C.
Further, the content of Co is 11.0% -13.0%.
The invention provides a preparation method of the powder nickel-based superalloy, which comprises the following steps: (1) smelting an alloy ingot with a target component by an induction heating method; (2) preparing alloy powder from the alloy ingot by an atomization method; (3) putting the alloy powder into a sheath, and performing hot isostatic pressing treatment to obtain a hot isostatic pressing material; (4) carrying out hot extrusion on the hot isostatic pressing material to obtain an extruded bar; (5) removing the sheath of the extruded bar to obtain a nickel-based superalloy bar; (6) and annealing the nickel-based high-temperature alloy bar to obtain the powder nickel-based high-temperature alloy.
Further, alloy atomization in the step (2) is adoptedAtomizing nitrogen or inert gas with gas flow of 0.02-0.24m3The gas pressure is 0.5-0.9MPa, and the temperature of the atomized melt is 1400-1500 ℃; the granularity of the alloy powder in the step (2) is 10-150 mu m.
Further, the hot isostatic pressing treatment in the step (3) comprises the following specific operation steps: firstly, alloy powder is put into a package sleeve and pumped at the temperature of 550 ℃ under the temperature of 450--4Compacting the powder under Pa; and then carrying out hot isostatic pressing treatment in an inert gas protective environment, wherein the hot isostatic pressing pressure is 150MPa-180MPa, the temperature is 1100-1200 ℃, and the heat preservation time is 120-300 min.
Further, the hot extrusion treatment in the step (4) comprises the following specific operation steps: firstly, preheating a hot isostatic pressing material to an extrusion temperature, preheating an extrusion cylinder to the temperature of 300-; then carrying out extrusion treatment, wherein the extrusion temperature is 1130-1200 ℃, and the extrusion ratio is 13-16: 1, the extrusion pressure is 950-1100MPa, and the extrusion speed is 170-260 mm/s; the temperature of the annealing treatment in the step (6) is 1100-1200 ℃, and the time is 30-120 min.
Compared with the prior art, the invention has the advantages that:
on the basis of the research of the existing polycrystalline Ni-based high-temperature alloy, the invention provides a component design idea of a novel Ni-based high-temperature alloy simultaneously added with Co and Sc, fully utilizes the coordination among strengthening elements, antioxidant elements and trace elements of the alloy, optimizes the contents of other alloy elements by balancing thermodynamic calculation, comprehensively improves the mechanical property of the alloy on the basis of ensuring the antioxidant property of the alloy, particularly synchronously improves the strength and plasticity in the high-temperature property, and meets the requirements of a turbine disc and a hot end part of a new-generation aero-engine.
Detailed Description
In order to facilitate an understanding of the present invention, the present invention will be described more fully and in detail with reference to the preferred embodiments, but the scope of the present invention is not limited to the specific embodiments below.
Unless otherwise defined, all terms of art used hereinafter have the same meaning as commonly understood by one of ordinary skill in the art. The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the scope of the present invention.
Unless otherwise specifically stated, various raw materials, reagents, instruments, equipment and the like used in the present invention are commercially available or can be prepared by existing methods.
The powder Ni-based high-temperature alloy with excellent mechanical property and complete oxidation resistance, which is disclosed by the invention, comprises the following elements in percentage by mass: 15.0 to 25.0 percent of Cr; 15.0 to 25.0 percent of W; 9.0 to 15.0 percent of Co; 0.5 to 3.0 percent of Mo; 0.5 to 4.0 percent of Al; 0.5 to 1.5 percent of Ti; 0.001 to 0.20 percent of C; sc is 0.001 to 0.20 percent; 0.001 to 0.50 percent of Y; the balance being Ni.
According to the invention, the solid solution strengthening effect is achieved by adding elements such as Mo and W, but the stability of the structure is reduced and the oxidation resistance of the alloy is damaged due to the excessively high content of the element Mo, so that the content of the Mo in the invention is 0.5-3.0%, and more preferably 1.3-1.9%; too high a content of element W similarly reduces the stability of the alloy, but too low a content will not fully dissolve in the matrix to exert the solid solution strengthening effect, so the content of element W in the present application is 15.0% to 25.0%, more preferably 16.0% to 19.0%.
Since addition of Ti, Al, etc. elements to form a precipitate strengthens the precipitate, and excessive content of Al and Ti elements is detrimental to the workability of the alloy and affects the stability of the structure, the Al and Ti contents in the present application are 0.5% to 4.0% (more preferably 1.9% to 2.3%) and 0.5% to 1.5% (more preferably 0.5% to 0.7%), respectively.
Elements such as Cr, Al and Y are added to ensure the oxidation resistance of the alloy, but the high-temperature strength of the alloy is influenced by the excessively high Cr element, so that the content of the Cr element is 15.0-25.0%, more preferably 19.0-24.0%, and the content of the Y element is 0.001-0.50%, more preferably 0.03-0.12%.
The addition of trace elements Sc and C can improve the grain boundary strength by segregation in the grain boundary, wherein the element C forms M6C improves the strength of the alloy at high temperature, and Sc can refine grains to improve the strength of the alloy. The content of C in the application is 0.001-0.20%,more preferably 0.11 to 0.14%, and the Sc content is 0.001 to 0.20%, more preferably 0.02 to 0.05%.
The addition of Co element to reduce the stacking fault can improve the creep and plasticity of the alloy and improve the processing performance of the alloy, but the high content of Co can reduce the strength of the alloy and influence the stability of the alloy, so that the content of Co is 9.0-15.0%, and more preferably 11.0-13.0%.
Meanwhile, the addition of the alloy element Co and the alloy element Sc can simultaneously improve the tensile strength and the elongation after fracture of the Ni-based high-temperature alloy at room temperature and high temperature, and has no obvious influence on the oxidation resistance.
In one embodiment, the method for preparing the Ni-based superalloy of the present invention comprises the steps of: (1): firstly, smelting an alloy ingot with a target component by an induction heating method; (2): preparing alloy powder from the alloy ingot by an atomization method; (3): putting the alloy powder into a stainless steel sheath, and performing hot isostatic pressing treatment to obtain a hot isostatic pressing material; (4): carrying out hot extrusion on the hot isostatic pressing material at high temperature to obtain an extruded bar; (5): removing the sheath of the extruded bar to obtain a Ni-based high-temperature alloy bar; (6): and carrying out short-time annealing treatment on the obtained extruded bar to finally obtain the Ni-based high-temperature alloy with excellent mechanical property and complete oxidation resistance.
Preferably, the smelting process of the target master alloy in the step (1) is carried out in a vacuum or argon protection mode.
Preferably, the alloy atomization in the step (2) adopts nitrogen or argon atomization, and the gas flow is 0.02-0.24m3The gas pressure is 0.5-0.9MPa, and the temperature of the atomized melt is 1400-1500 ℃.
Preferably, the particle size of the alloy powder in step (2) is selected to be 10-150 μm.
Preferably, the hot isostatic pressing treatment in step (3) comprises the following specific operation steps: firstly, alloy powder is put into a package sleeve and pumped at the temperature of 450--4Compacting the powder under Pa; and then carrying out hot isostatic pressing treatment in an argon protective environment, wherein the hot isostatic pressing pressure is 150MPa-180MPa, the temperature is 1100-1200 ℃, and the heat preservation time is 120-300 min.
Preferably, the hot extrusion treatment in the step (4) comprises the following specific operation steps: firstly, preheating a hot isostatic pressing material to an extrusion temperature, preheating an extrusion cylinder to the temperature of 300-; then carrying out extrusion treatment, wherein the extrusion temperature is 1130-1200 ℃, and the extrusion ratio is 13-16: 1, the extrusion pressure 950-.
Preferably, the sheath treatment in the step (5) adopts a wire-cut electric discharge machine to cut off the stainless steel sheath on the outer layer of the sample after the hot extrusion.
Preferably, the temperature of the annealing treatment in the step (6) is 1100-1200 ℃, and the time is 30-120 min.
Example 1:
a method for preparing a Ni-based superalloy with excellent mechanical properties and complete oxidation resistance comprises the following steps:
(1): according to the proportion of Cr of 19.40 percent; 17.54 percent of W; 12.01 percent of Co; 1.50 percent of Mo; 2.07 percent of Al; 0.55 percent of Ti; 0.11 percent of C; 0.03 percent of Sc; 0.03 percent of Y; and preparing alloy according to the mass percentage of the balance of Ni, performing induction melting in a vacuum environment, controlling the melting temperature to be 1547 ℃ in the melting process, and finally pouring into an alloy ingot. (2): atomizing the alloy ingot obtained in the step (1) by adopting argon to prepare powder, wherein the gas flow is 0.14m3(3) sieving 10-150 μm alloy powder, loading into stainless steel sheath, and pumping at 480 deg.C for 12 hr to 8 × 10-5Pa, hot isostatic pressing in an argon environment, wherein the pressure is 160 MPa; keeping the temperature at 1180 ℃ for 240 min. (4): preheating the hot isostatic pressing material to the extrusion temperature of 1200 ℃, keeping the temperature for 120min, preheating an extrusion cylinder to the temperature of 360 ℃, carrying out hot extrusion, wherein the extrusion ratio is 16: 1, the extrusion pressure is 1025Mpa, the extrusion speed is 215mm/s, and carrying out air cooling to the room temperature after the hot extrusion. (5): and (4) cutting off the sheath of the hot extrusion material obtained in the step (4) by using a wire cut electrical discharge machine to obtain the alloy after hot extrusion. (6): and (4) annealing the hot extruded alloy obtained in the step (5) at 1100 ℃ for 60min to obtain the final target alloy.
Example 2:
a method for preparing a Ni-based superalloy with excellent mechanical properties and complete oxidation resistance comprises the following steps:
(1): according to the proportion of 20.14 percent of Cr; 17.21 percent of W; 11.84 percent of Co; 1.38 percent of Mo; 2.13 percent of Al; 0.62 percent of Ti; 0.14 percent of C; 0.02 percent of Sc; 0.08 percent of Y; and preparing alloy by the mass percentage of the balance of Ni, performing induction melting in a vacuum environment, controlling the melting temperature to 1568 ℃ in the melting process, and finally pouring into an alloy ingot. (2): atomizing the alloy ingot obtained in the step (1) by adopting argon to prepare powder, wherein the gas flow is 0.17m3(3) sieving 10-150 μm alloy powder, loading into stainless steel sheath, and pumping at 500 deg.C for 12 hr to pressure of 1 × 10-4Pa, hot isostatic pressing in an argon environment, wherein the pressure is 180 MPa; the temperature is 1175 ℃ and the temperature is kept for 240 min. (4): preheating the hot isostatic pressing material to an extrusion temperature of 1180 ℃, keeping the temperature for 120min, preheating an extrusion cylinder to 380 ℃, then carrying out hot extrusion, wherein the extrusion ratio is 16: 1, the extrusion pressure is 1003Mpa, the extrusion speed is 227mm/s, and air cooling to room temperature after the hot extrusion. (5): and (4) cutting off the sheath of the hot extrusion material obtained in the step (4) by using a wire cut electrical discharge machine to obtain the alloy after hot extrusion. (6): and (4) annealing the hot extruded alloy obtained in the step (5) at 1100 ℃ for 60min to obtain the final target alloy.
Example 3:
a method for preparing a Ni-based superalloy with excellent mechanical properties and complete oxidation resistance comprises the following steps:
(1): according to the proportion of Cr of 19.85 percent; 17.03 percent of W; 11.92 percent of Co; 1.62 percent of Mo; 1.95 percent of Al; 0.69 percent of Ti; 0.13 percent of C; 0.05 percent of Sc; 0.07 percent of Y; and preparing alloy according to the mass percentage of the balance of Ni, performing induction melting in a vacuum environment, controlling the melting temperature to 1535 ℃ in the melting process, and finally pouring into an alloy ingot. (2): atomizing the alloy ingot obtained in the step (1) by adopting argon to prepare powder, wherein the gas flow is 0.21m3(3) sieving 10-150 μm alloy powder, placing into stainless steel sheath, and evacuating at 500 deg.C for 12 hr to 7 × 10-5Pa, hot isostatic pressing in an argon environment, wherein the pressure is 170 MPa; keeping the temperature at 1180 ℃ for 240 min. (4): preheating hot isostatic pressing material to extrusion temperatureKeeping the temperature at 1180 ℃ for 120min, preheating an extrusion cylinder to 400 ℃, performing hot extrusion at the extrusion ratio of 16: 1 and the extrusion pressure of 1012Mpa at the extrusion speed of 241mm/s, and performing air cooling to room temperature after the hot extrusion. (5): and (4) cutting off the sheath of the hot extrusion material obtained in the step (4) by using a wire cut electrical discharge machine to obtain the alloy after hot extrusion. (6): and (4) annealing the hot extruded alloy obtained in the step (5) at 1140 ℃ for 60min to obtain the final target alloy.
Example 4:
a method for preparing a Ni-based superalloy with excellent mechanical properties and complete oxidation resistance comprises the following steps:
(1): according to the proportion of Cr of 22.46 percent; 16.51 percent of W; 11.18 percent of Co; 1.88 percent of Mo; 1.94 percent of Al; 0.52 percent of Ti; 0.11 percent of C; 0.03 percent of Sc; 0.08 percent of Y; and preparing alloy according to the mass percentage of the balance of Ni, performing induction melting in a vacuum environment, controlling the melting temperature to be 1543 ℃ in the melting process, and finally pouring into an alloy ingot. (2): atomizing the alloy ingot obtained in the step (1) by adopting argon to prepare powder, wherein the gas flow is 0.20m3(3) sieving 10-150 μm alloy powder, loading into stainless steel sheath, and pumping at 500 deg.C for 12 hr to 9 × 10-5Pa, hot isostatic pressing in an argon environment, wherein the pressure is 180 MPa; keeping the temperature at 1190 ℃ for 240 min. (4): preheating the hot isostatic pressing material to an extrusion temperature of 1150 ℃ and preserving heat for 120min, preheating an extrusion cylinder to 400 ℃ and then carrying out hot extrusion, wherein the extrusion ratio is 16: 1, the extrusion pressure is 983Mpa, the extrusion speed is 231mm/s, and air cooling is carried out to the room temperature after the hot extrusion. (5): and (4) cutting off the sheath of the hot extrusion material obtained in the step (4) by using a wire cut electrical discharge machine to obtain the alloy after hot extrusion. (6): and (4) annealing the hot extruded alloy obtained in the step (5) for 90min at 1150 ℃ to obtain the final target alloy.
Example 5:
a method for preparing a Ni-based superalloy with excellent mechanical properties and complete oxidation resistance comprises the following steps:
(1): according to the proportion of 21.42 percent of Cr; 18.03 percent of W; 11.37 percent of Co; 1.52 percent of Mo; 2.06 percent of Al; 0.57 percent of Ti; 0.12 percent of C; 0.02 percent of Sc; 0.07 percent of Y; ni balancePreparing alloy according to the mass percentage, performing induction melting in a vacuum environment, controlling the melting temperature to 1557 ℃ in the melting process, and finally pouring into an alloy ingot. (2): atomizing the alloy ingot obtained in the step (1) by adopting argon to prepare powder, wherein the gas flow is 0.19m3(3) sieving 10-150 μm alloy powder, loading into stainless steel sheath, and pumping at 500 deg.C for 12 hr to 7 × 10-5Pa, hot isostatic pressing in an argon environment, wherein the pressure is 180 MPa; keeping the temperature at 1190 ℃ for 240 min. (4): preheating the hot isostatic pressing material to an extrusion temperature of 1180 ℃, keeping the temperature for 120min, preheating an extrusion cylinder to 400 ℃, carrying out hot extrusion at an extrusion ratio of 16: 1 and an extrusion pressure of 1013Mpa at an extrusion rate of 236mm/s, and carrying out air cooling to room temperature after the hot extrusion. (5): and (4) cutting off the sheath of the hot extrusion material obtained in the step (4) by using a wire cut electrical discharge machine to obtain the alloy after hot extrusion. (6): and (4) annealing the hot extruded alloy obtained in the step (5) at 1150 ℃ for 60min to obtain the final target alloy.
Example 6:
a method for preparing a Ni-based superalloy with excellent mechanical properties and complete oxidation resistance comprises the following steps:
(1): according to the proportion of 23.02 percent of Cr; 18.17 percent of W; 11.35 percent of Co; 1.53 percent of Mo; 2.03 percent of Al; 0.52 percent of Ti; 0.11 percent of C; 0.04 percent of Sc; 0.12 percent of Y; and preparing alloy by the mass percentage of the balance of Ni, performing induction melting in a vacuum environment, controlling the melting temperature to 1559 ℃ in the melting process, and finally pouring into an alloy ingot. (2): atomizing the alloy ingot obtained in the step (1) by adopting argon to prepare powder, wherein the gas flow is 0.18m3(3) sieving 10-150 μm alloy powder, loading into stainless steel sheath, and pumping at 500 deg.C for 12 hr to 8 × 10-5Pa, hot isostatic pressing in an argon environment, wherein the pressure is 180 MPa; keeping the temperature at 1180 ℃ for 240 min. (4): preheating the hot isostatic pressing material to an extrusion temperature of 1150 ℃, preserving heat for 120min, preheating an extrusion cylinder to 400 ℃, then carrying out hot extrusion, wherein the extrusion ratio is 16: 1, the extrusion pressure is 1006Mpa, the extrusion speed is 239mm/s, and air cooling to room temperature after hot extrusion. (5): using a spark wire cutting machine to cutAnd (4) cutting off the sheath of the hot extrusion material obtained in the step (4) to obtain the alloy after hot extrusion. (6): and (4) annealing the hot extruded alloy obtained in the step (5) at 1180 ℃ for 60min to obtain the final target alloy.
Example 7:
a method for preparing a Ni-based superalloy with excellent mechanical properties and complete oxidation resistance comprises the following steps:
(1): according to the proportion of 20.27 percent of Cr; 18.48 percent of W; 12.17 percent of Co; 1.47 percent of Mo; 2.03 percent of Al; 0.57 percent of Ti; 0.12 percent of C; 0.02 percent of Sc; 0.08 percent of Y; and preparing alloy according to the mass percentage of the balance of Ni, performing induction melting in a vacuum environment, controlling the melting temperature to 1561 ℃ in the melting process, and finally pouring into an alloy ingot. (2): atomizing the alloy ingot obtained in the step (1) by adopting argon to prepare powder, wherein the gas flow is 0.19m3(3) sieving 10-150 μm alloy powder, loading into stainless steel sheath, and pumping at 500 deg.C for 12 hr to 8 × 10-5Pa, hot isostatic pressing in an argon environment, wherein the pressure is 180 MPa; keeping the temperature at 1180 ℃ for 240 min. (4): preheating the hot isostatic pressing material to an extrusion temperature of 1180 ℃, keeping the temperature for 120min, preheating an extrusion cylinder to 400 ℃, then carrying out hot extrusion, wherein the extrusion ratio is 16: 1, the extrusion pressure is 1008Mpa, the extrusion speed is 232mm/s, and air cooling is carried out to the room temperature after the hot extrusion. (5): and (4) cutting the sheath of the hot extrusion material obtained in the step (4) by using a wire cut electrical discharge machine to obtain the alloy after hot extrusion. (6): and (4) annealing the hot extruded alloy obtained in the step (5) at 1150 ℃ for 60min to obtain the final target alloy.
Example 8:
a method for preparing a Ni-based superalloy with excellent mechanical properties and complete oxidation resistance comprises the following steps:
(1): according to the proportion of Cr of 22.53 percent; 18.32 percent of W; 12.04 percent of Co; 1.58 percent of Mo; 2.27 percent of Al; 0.53 percent of Ti; 0.13 percent of C; 0.03 percent of Sc; 0.09 percent of Y; and preparing alloy according to the mass percentage of the balance of Ni, performing induction melting in a vacuum environment, controlling the melting temperature to be 1548 ℃ in the melting process, and finally pouring into an alloy ingot. (2): atomizing the alloy ingot obtained in the step (1) by adopting argon to prepare powderGas flow of 0.22m3(3) sieving 10-150 μm alloy powder, loading into stainless steel sheath, and pumping at 500 deg.C for 12 hr to 7 × 10-5Pa, hot isostatic pressing in an argon environment, wherein the pressure is 180 MPa; keeping the temperature at 1180 ℃ for 240 min. (4): preheating the hot isostatic pressing material to an extrusion temperature of 1180 ℃, keeping the temperature for 120min, preheating an extrusion barrel to 400 ℃, carrying out hot extrusion at an extrusion ratio of 16: 1 and an extrusion pressure of 983Mpa at an extrusion rate of 244mm/s, and carrying out air cooling to room temperature after the hot extrusion. (5): and (4) cutting the sheath of the hot extrusion material obtained in the step (4) by using a wire cut electrical discharge machine to obtain the alloy after hot extrusion. (6): and (4) annealing the hot extruded alloy obtained in the step (5) at 1180 ℃ for 30min to obtain the final target alloy.
Comparative example 1:
a method for preparing a fully oxidation resistant Ni-based superalloy, comprising the steps of:
(1): according to the proportion of Cr of 22.46 percent; 18.52 percent of W; 12.31 percent of Co; 1.47 percent of Mo; 2.05 percent of Al; 0.62 percent of Ti; 0.15 percent of C; 0.11 percent of Y; and preparing alloy according to the mass percentage of the balance of Ni, performing induction melting in a vacuum environment, controlling the melting temperature to be 1548 ℃ in the melting process, and finally pouring into an alloy ingot. (2): atomizing the alloy ingot obtained in the step (1) by adopting argon to prepare powder, wherein the gas flow is 0.22m3(3) sieving 10-150 μm alloy powder, loading into stainless steel sheath, and pumping at 500 deg.C for 12 hr to 7 × 10-5Pa, hot isostatic pressing in an argon environment, wherein the pressure is 180 MPa; keeping the temperature at 1180 ℃ for 240 min. (4): preheating the hot isostatic pressing material to an extrusion temperature of 1180 ℃, keeping the temperature for 120min, preheating an extrusion cylinder to 400 ℃, carrying out hot extrusion at an extrusion ratio of 16: 1 and an extrusion pressure of 994Mpa at an extrusion speed of 216mm/s, and carrying out air cooling to room temperature after the hot extrusion. (5): and (4) cutting the sheath of the hot extrusion material obtained in the step (4) by using a wire cut electrical discharge machine to obtain the alloy after hot extrusion. (6): and (4) annealing the hot extruded alloy obtained in the step (5) at 1180 ℃ for 30min to obtain the final target alloy.
Comparative example 2:
a method for preparing a fully oxidation resistant Ni-based superalloy, comprising the steps of:
(1): according to the proportion of Cr of 22.73 percent; 18.62 percent of W; 1.49 percent of Mo; 1.94 percent of Al; 0.63 percent of Ti; 0.12 percent of C; 0.04 percent of Sc; 0.10 percent of Y; and preparing alloy according to the mass percentage of the balance of Ni, performing induction melting in a vacuum environment, controlling the melting temperature to 1561 ℃ in the melting process, and finally pouring into an alloy ingot. (2): atomizing the alloy ingot obtained in the step (1) by adopting argon to prepare powder, wherein the gas flow is 0.18m3(3) sieving 10-150 μm alloy powder, loading into stainless steel sheath, and pumping at 500 deg.C for 12 hr to 7 × 10-5Pa, hot isostatic pressing in an argon environment, wherein the pressure is 180 MPa; keeping the temperature at 1180 ℃ for 240 min. (4): preheating the hot isostatic pressing material to an extrusion temperature of 1180 ℃, keeping the temperature for 120min, preheating an extrusion cylinder to 400 ℃, then carrying out hot extrusion, wherein the extrusion ratio is 16: 1, the extrusion pressure is 994Mpa, the extrusion speed is 215mm/s, and air cooling to room temperature after hot extrusion. (5): and (4) cutting the sheath of the hot extrusion material obtained in the step (4) by using a wire cut electrical discharge machine to obtain the alloy after hot extrusion. (6): and (4) annealing the hot extruded alloy obtained in the step (5) at 1180 ℃ for 30min to obtain the final target alloy.
Comparative example 3:
a method for preparing a fully oxidation resistant Ni-based superalloy, comprising the steps of:
(1): according to the proportion of 23.03 percent of Cr; 18.53 percent of W; 1.54 percent of Mo; 2.16 percent of Al; 0.52 percent of Ti; 0.12 percent of C; 0.10 percent of Y; and preparing alloy according to the mass percentage of the balance of Ni, performing induction melting in a vacuum environment, controlling the melting temperature to 1561 ℃ in the melting process, and finally pouring into an alloy ingot. (2): atomizing the alloy ingot obtained in the step (1) by adopting argon to prepare powder, wherein the gas flow is 0.18m3(3) sieving 10-150 μm alloy powder, loading into stainless steel sheath, and pumping at 500 deg.C for 12 hr to 8 × 10-5Pa, hot isostatic pressing in an argon environment, wherein the pressure is 180 MPa; keeping the temperature at 1180 ℃ for 240 min. (4): preheating hot isostatic pressing material to extrusion temperatureKeeping the temperature at 1180 ℃ for 120min, preheating an extrusion cylinder to 400 ℃, performing hot extrusion at the extrusion ratio of 16: 1 and the extrusion pressure of 1004Mpa at the extrusion speed of 204mm/s, and performing air cooling to room temperature after the hot extrusion. (5): and (4) cutting the sheath of the hot extrusion material obtained in the step (4) by using a wire cut electrical discharge machine to obtain the alloy after hot extrusion. (6): and (4) annealing the hot extruded alloy obtained in the step (5) at 1180 ℃ for 30min to obtain the final target alloy.
The chemical composition (wt.%) of the above examples 1-8 and comparative examples 1-3 are shown in table 1.
Table 1 examples and comparative examples chemical composition (wt.%)
Alloy (I) Cr W Co Mo Al Ti C Sc Y Ni
Example 1 19.40 17.54 12.01 1.50 2.07 0.55 0.11 0.03 0.03 Balance of
Example 2 20.14 17.21 11.84 1.38 2.13 0.62 0.14 0.02 0.08 Balance of
Example 3 19.85 17.03 11.92 1.62 1.95 0.69 0.13 0.05 0.07 Balance of
Example 4 22.46 16.51 11.18 1.88 1.94 0.52 0.11 0.03 0.08 Balance of
Example 5 21.42 18.03 11.37 1.52 2.06 0.57 0.12 0.02 0.07 Balance of
Example 6 23.02 18.17 11.35 1.53 2.03 0.52 0.11 0.04 0.12 Balance of
Example 7 20.27 18.48 12.17 1.47 2.03 0.57 0.12 0.02 0.08 Balance of
Example 8 22.53 18.32 12.04 1.58 2.27 0.53 0.13 0.03 0.09 Balance of
Comparative example 1 22.46 18.52 12.31 1.47 2.05 0.62 0.15 - 0.11 Balance of
Comparative example 2 22.73 18.62 - 1.49 1.94 0.63 0.12 0.04 0.10 Balance of
Comparative example 3 23.03 18.53 - 1.54 2.16 0.52 0.12 - 0.10 Balance of
Performance testing
Comparative experiments were conducted on the alloys described in examples 1 to 8 and the alloys described in comparative examples 1 to 3, respectively, for the room-temperature tensile strength elongation after fracture (GB/T228.1-2010: Metal Material Room temperature tensile test method), the 900 ℃ tensile strength and elongation after fracture (GB/T4338-2006: Metal Material high temperature tensile test method), and the oxidation rate at 1000 ℃ under constant temperature oxidation for 100 hours (HB 5258-2000: Steel and superalloy Oxidation resistance measurement test method), and the results are shown in Table 2.
TABLE 2 mechanical and antioxidant Properties of the examples and comparative examples
Figure BDA0002491815860000091
It is seen from table 2 that examples 1-8 and comparative examples 1-3 all achieved complete oxidation resistance, wherein the absence of Sc in comparative example 1 shows a significant decrease in tensile strength at room temperature and at high temperatures of 900 ℃, but no significant decrease in elongation after fracture; comparative example 2 the elongation after fracture of Co, which lacks the alloying element, at room temperature and 900 ℃ is obviously reduced while the tensile strength of the alloy is slightly reduced; comparative example 3 lack of both alloying element Co and alloying element Sc shows that the tensile strength and post-fracture elongation of the alloy are significantly reduced compared to examples 1-8, both at room temperature and 900 ℃. The invention proposes that the tensile strength and the elongation after fracture of the Ni-based high-temperature alloy at room temperature and high temperature can be improved by simultaneously adding the alloy element Co and the alloy element Sc, and the oxidation resistance of the Ni-based high-temperature alloy is not obviously influenced. This provides a good material for the hot end parts of the next generation of aeroengines.
The foregoing is considered as illustrative of the preferred embodiments of the invention and is not to be construed as limiting the invention in any way. Other preparation methods are for example: preparing the high-temperature alloy with the components through a casting process; preparing a high-temperature alloy with the components by a hot isostatic pressing process; preparing the high-temperature alloy with the components by a hot extrusion process; preparing the high-temperature alloy with the components by a forging process; the high-temperature alloy with the composition is prepared by combining two or more processes. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical spirit of the present invention should fall within the protection scope of the technical scheme of the present invention, unless the technical spirit of the present invention departs from the content of the technical scheme of the present invention.

Claims (10)

1. The powder nickel-based superalloy is characterized by comprising the following elements in percentage by mass: 15.0 to 25.0 percent of Cr; 15.0 to 25.0 percent of W; 9.0 to 15.0 percent of Co; 0.5 to 3.0 percent of Mo; 0.5 to 4.0 percent of Al; 0.5 to 1.5 percent of Ti; 0.001 to 0.20 percent of C; sc is 0.001 to 0.20 percent; 0.001 to 0.50 percent of Y; the balance being Ni.
2. The powder nickel-base superalloy according to claim 1, wherein the content of Mo and W is as follows: 1.3 to 1.9 percent of Mo; 16.0 to 19.0 percent of W.
3. The powder nickel-base superalloy as claimed in claim 1, wherein the content of Al and Ti is: 1.9 to 2.3 percent of Al; 0.5 to 0.7 percent of Ti.
4. The powder nickel-base-superalloy as in claim 1 or 3, wherein the amount of Cr, Y is: 19.0 to 24.0 percent of Cr; 0.03 to 0.12 percent of Y.
5. The powder nickel-base superalloy as claimed in claim 1, wherein the contents of Sc and C are: sc is 0.02 to 0.05 percent; 0.11 to 0.14 percent of C.
6. The powder nickel-base superalloy according to claim 1 or 5, wherein the content of Co is 11.0% to 13.0%.
7. A method for preparing the powder nickel-base superalloy as set forth in any of claims 1 to 6, comprising the steps of: (1) smelting an alloy ingot with a target component by an induction heating method; (2) preparing alloy powder from the alloy ingot by an atomization method; (3) putting the alloy powder into a sheath, and performing hot isostatic pressing treatment to obtain a hot isostatic pressing material; (4) carrying out hot extrusion on the hot isostatic pressing material to obtain an extruded bar; (5) removing the sheath of the extruded bar to obtain a nickel-based superalloy bar; (6) and annealing the nickel-based high-temperature alloy bar to obtain the powder nickel-based high-temperature alloy.
8. The method for preparing powder nickel-base superalloy according to claim 7, wherein in the step (2), the alloy is atomized by using nitrogen or inert gas, and the gas flow rate is 0.02-0.24m3The gas pressure is 0.5-0.9MPa, and the temperature of the atomized melt is 1400-1500 ℃; the granularity of the alloy powder in the step (2) is 10-150 mu m.
9. According to claimThe method for preparing the powder nickel-base superalloy as set forth in claim 7, wherein the hot isostatic pressing treatment in the step (3) comprises the following specific operation steps: firstly, alloy powder is put into a package sleeve and pumped at the temperature of 550 ℃ under the temperature of 450--4Compacting the powder under Pa; and then carrying out hot isostatic pressing treatment in an inert gas protective environment, wherein the hot isostatic pressing pressure is 150MPa-180MPa, the temperature is 1100-1200 ℃, and the heat preservation time is 120-300 min.
10. The method for preparing powder nickel-base superalloy according to claim 7, wherein the step (4) of hot pressing comprises the following specific steps: firstly, preheating a hot isostatic pressing material to an extrusion temperature, preheating an extrusion cylinder to the temperature of 300-; then carrying out extrusion treatment, wherein the extrusion temperature is 1130-1200 ℃, and the extrusion ratio is 13-16: 1, the extrusion pressure is 950-1100MPa, and the extrusion speed is 170-260 mm/s; the temperature of the annealing treatment in the step (6) is 1100-1200 ℃, and the time is 30-120 min.
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