A new high-strength alloy material resistant to 1100 °c and additive manufacturing method, shaped piece and application thereof
By combining multi-component high-temperature alloy materials with additive manufacturing technology, the forming problem of complex high-temperature components in the 900-1200℃ temperature range has been solved, realizing the preparation of high-strength and high-plasticity aero-engine hot-end component materials at high temperatures, filling the gap in the application temperature range of traditional alloys.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- AVIC BEIJING AERONAUTICAL MFG TECH RES INST
- Filing Date
- 2026-05-15
- Publication Date
- 2026-07-21
AI Technical Summary
Existing technologies do not yet produce additive manufacturing alloys that can operate for extended periods in the 900-1200℃ temperature range. This makes it difficult to ensure high-temperature mechanical properties while forming complex high-temperature components, becoming a key bottleneck in the development of next-generation aero-engines.
A novel high-strength alloy material with a temperature resistance of 1100℃ and its additive manufacturing method were developed. A stable face-centered cubic matrix was constructed using Ni, Co, and Cr as the main components, combined with multiple strengthening elements, and laser selective melting process. The powder particle size and protective atmosphere were controlled, and the material was spread and solidified layer by layer to ensure the internal density and high-temperature performance of the formed part.
The resulting molded parts have a tensile strength of over 100 MPa at 1100℃, exhibiting excellent high-temperature plasticity and oxidation resistance. This meets the requirements of high temperature resistance, lightweight design, and long service life for hot-end components of next-generation aero-engines, and addresses the gap in the use of traditional alloys in high-temperature regions.
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Abstract
Description
Technical Field
[0001] This invention relates to the field of additive manufacturing materials technology, and in particular to a novel high-strength alloy material resistant to 1100℃, its additive manufacturing method, formed parts, and applications. Background Technology
[0002] As the thrust-to-weight ratio of aero engines continues to increase, hot-end components such as combustion chambers are subject to higher requirements for structural materials, including lightweighting, high-temperature resistance, and excellent durability. Traditional high-temperature alloys typically cannot operate at temperatures exceeding 1000℃ over long periods, and the increasingly complex structures of components pose a severe challenge to traditional manufacturing technologies.
[0003] Multi-principal element alloys, as a new type of high-temperature alloy material, possess excellent high-temperature specific strength, enabling them to serve for extended periods at temperatures above 1000℃. Combined with additive manufacturing technology, they can provide an innovative approach for the development of hot-end components for next-generation aero-engines and aircraft that can withstand even higher temperatures.
[0004] However, the structural designs of new-generation aircraft and aero-engines are becoming increasingly complex, and complex geometric structures such as internal flow channels and irregular curved surfaces urgently require non-traditional forming technologies such as additive manufacturing. However, there are currently no additive manufacturing alloys that can operate for extended periods in the 900-1200℃ temperature range. How to ensure high-temperature mechanical properties while forming complex high-temperature components has become one of the key bottlenecks restricting the development of new-generation aero-engines.
[0005] To fill the material gap in the operating temperature range between traditional high-temperature alloys and refractory alloys, and to meet the design requirements of next-generation aero-engines and aircraft, it is of great significance to develop a new type of high-temperature alloy and its supporting forming technology that is compatible with additive manufacturing processes. Summary of the Invention
[0006] The purpose of this invention is to provide a novel high-strength alloy material with a temperature resistance of 1100℃, its additive manufacturing method, formed parts, and applications. The alloy material has both excellent high-temperature resistance and good additive manufacturing formability. Its stable operating temperature can reach 1100℃, and its tensile strength at this temperature exceeds 100MPa.
[0007] To achieve the above objectives, this invention provides a novel high-strength alloy material resistant to 1100℃. The chemical composition of the alloy material, by mass percentage, includes: Ni: 27.0~32.0 wt.%, Co: 31.0~36.0 wt.%, Cr: 27.0~32.0 wt.%, W: 1.0~5.0 wt.%, Ta: 1.0~5.0 wt.%, Ti: 0.1~1.0 wt.%, Al: 0.1~1.0 wt.%, Re: 1.0~3.0 wt.%, Nb: 0.1~2.0 wt.%, and C: 0.05~0.1 wt.%.
[0008] Preferably, the particle size distribution of the alloy material powder is 15~53μm.
[0009] This invention also provides an additive manufacturing method for a novel high-strength alloy material resistant to 1100℃, comprising the following steps: S1. Place the alloy material in the powder supply cylinder of the forming chamber for later use; S2. Install the molded substrate into the sealed molding chamber, fill the chamber with inert gas to form a protective atmosphere, and control the oxygen content to be lower than the safety threshold. S3. Preheat the molded substrate installed in S2; S4. Using laser technology, the alloy material of S1 is laid layer by layer on the preheated forming substrate of S3 according to the preset scanning path, and then melted and solidified layer by layer until the part is completely formed. S5. After forming is completed, the part is cooled with the furnace, and the forming chamber is opened to take out the formed part.
[0010] Preferably, in S2, the inert gas is high-purity argon or high-purity helium, and the purity of the inert gas is greater than or equal to 99.99%.
[0011] Preferably, in S3, the preheating temperature is 50~300℃.
[0012] Preferably, in S4, the laser process parameters are: laser power 200~230W, scanning speed 700~1200mm / s, melt channel spacing 60~100μm, powder layer thickness 20~40μm, and scanning is performed with an interlayer rotation angle of 67° during the laser selective melting process.
[0013] Preferably, in S5, the part is cooled to below 50°C in the furnace.
[0014] The present invention also provides a molded part made of a novel high-strength alloy material resistant to 1100℃, which is prepared by the above-mentioned additive manufacturing method.
[0015] This invention also provides the application of the above-mentioned novel high-strength alloy material resistant to 1100℃ in the manufacture of hot-end components for aero-engines.
[0016] The beneficial effects of this invention are: (1) This invention addresses the process characteristics of laser selective melting (SLM) with rapid solidification, non-equilibrium structure, high temperature gradient and high cooling rate. It uses multi-component high alloy materials to accurately match the forming law of additive manufacturing, and solves the problems of cracks, compositional segregation, uneven structure and low density that traditional high temperature alloys are prone to in additive manufacturing from the source.
[0017] (2) The molded parts obtained by the present invention can be used at a stable temperature of up to 1100℃. At this temperature, the tensile strength exceeds 100MPa, while maintaining good plasticity. They can be used stably for a long time in high temperature and stress coupling environment, effectively filling the gap in the operating temperature range between traditional nickel-based high temperature alloys (usually <1000℃) and refractory alloys (poor machinability, high cost, high density).
[0018] (3) The molded parts obtained by the present invention have better tensile strength, structural stability and antioxidant properties in the 1100℃ temperature range, which can meet the core requirements of high temperature resistance, lightweight and long service life of the hot end components of the new generation of aero engines and aircraft, and provide a new material solution for key components such as combustion chamber, turbine and internal flow channel of high thrust-to-weight ratio engine.
[0019] The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Attached Figure Description
[0020] Figure 1 This is a schematic diagram of the engineering stress-strain curve of the molded part obtained in Embodiment 1 of the present invention at room temperature; Figure 2 This is a schematic diagram of the engineering stress-strain curve of the molded part obtained in Embodiment 1 of the present invention at 1100℃; Figure 3 This is a schematic diagram of the metallographic structure of the molded part obtained in Embodiment 2 of the present invention. Detailed Implementation
[0021] The present invention will be further described below with reference to the accompanying drawings and embodiments. Unless otherwise defined, the technical or scientific terms used in this invention should be understood in their ordinary sense by those skilled in the art. The features mentioned above or in the specific examples mentioned in this invention can be combined arbitrarily, and these specific embodiments are only used to illustrate the invention and are not intended to limit the scope of the invention.
[0022] This invention provides a novel high-strength alloy material resistant to 1100℃. The chemical composition of the alloy material, by mass percentage, includes: Ni: 27.0~32.0 wt.%, Co: 31.0~36.0 wt.%, Cr: 27.0~32.0 wt.%, W: 1.0~5.0 wt.%, Ta: 1.0~5.0 wt.%, Ti: 0.1~1.0 wt.%, Al: 0.1~1.0 wt.%, Re: 1.0~3.0 wt.%, Nb: 0.1~2.0 wt.%, and C: 0.05~0.1 wt.%.
[0023] This invention constructs a stable face-centered cubic matrix with Ni, Co, and Cr as the main elements, and combines them with multi-element strengthening elements such as W, Ta, Re, Nb, Al, and Ti to achieve significant solid solution strengthening. The synergistic effect of Al and Cr elements enhances the alloy's high-temperature oxidation and hot corrosion resistance, extending its high-temperature service life. High-melting-point elements such as W and Re reduce the atomic diffusion rate, suppressing high-temperature creep and microstructure instability. The precipitation of intermetallic compound strengthening phases such as γ′ by Al, Ti, Ta, and Nb at high temperatures significantly improves high-temperature strength and microstructure stability. Trace amounts of C are added for grain boundary strengthening and regulation, improving high-temperature grain boundary strength and crack resistance.
[0024] The alloy material system of this invention can achieve crack-free and high-density forming throughout the additive manufacturing process, with low internal defect rate and uniform structure of the formed parts. At the same time, it takes into account excellent high-temperature mechanical properties and process adaptability, breaking through the technical bottleneck that traditional high-temperature alloys cannot simultaneously meet the requirements of additive manufacturing and high-temperature service above 1100°C.
[0025] Preferably, the powder particle size distribution of the alloy material is 15~53μm. By controlling the powder particle size within the above range, this invention can effectively suppress common defects in the SLM process such as spheroidization, porosity, and cracks.
[0026] In some specific embodiments of the present invention, the alloy material is prepared using the gas atomization powder preparation method in the prior art.
[0027] This invention also provides an additive manufacturing method for a novel high-strength alloy material resistant to 1100℃, comprising the following steps: S1. Place the alloy material in the powder supply cylinder of the forming chamber for later use; S2. The forming substrate is installed in a sealed forming chamber, and an inert gas is filled into the chamber to form a protective atmosphere, controlling the oxygen content to be lower than the safety threshold. The sealed chamber and low oxygen atmosphere can prevent the alloy material and the molten pool from oxidizing, absorbing gas, and burning at high temperatures, avoiding defects such as oxide inclusions, pores, and cracks, and significantly improving the density and high-temperature mechanical properties of the formed parts. S3. Preheat the forming substrate installed in S2; by preheating, the temperature gradient between the forming substrate and the molten pool is reduced, thermal stress and deformation tendency are reduced, cracking, warping and poor interlayer bonding are suppressed in the additive manufacturing process, and the dimensional accuracy and structural integrity of the parts are improved.
[0028] S4. Using laser technology, the alloy material of S1 is laid layer by layer on the preheated forming substrate of S3 according to the preset scanning path, and then melted and solidified layer by layer until the part is completely formed. The high energy density of the laser is used to achieve rapid melting and solidification of powder, resulting in a fine and uniform microstructure. Layer-by-layer stacking can realize the integrated manufacturing of complex structures, ensuring that the internal structure of the part is dense and the performance is uniform. S5. After forming is completed, the part is cooled in the furnace, and the forming chamber is opened to remove the formed part. Slow cooling in the furnace can further release internal stress, avoid cracking or deformation of the part caused by rapid cooling, and ensure the dimensional and structural stability of the formed part; cooling to a low temperature before removing the part can avoid high-temperature contact oxidation and ensure the surface quality of the part.
[0029] Preferably, in S2, the inert gas is high-purity argon or high-purity helium, with a purity of ≥99.99%, which can minimize the impact of harmful gases such as oxygen and nitrogen and ensure the purity of the molten pool.
[0030] Preferably, in S3, the preheating temperature is 50~300℃, which ensures stress release while avoiding overheating that could lead to coarse grains.
[0031] Preferably, in step S4, the laser process parameters are: laser power 200~230W, scanning speed 700~1200mm / s, melt channel spacing 60~100μm, powder layer thickness 20~40μm, and scanning with an interlayer rotation angle of 67° during selective laser melting. Using an interlayer rotation angle of 67° for scanning can eliminate interlayer anisotropy, reduce melt channel overlap defects, and make the microstructure and properties more uniform.
[0032] Preferably, in S5, the parts are cooled to below 50°C in the furnace, which is safe and reliable and can prevent secondary oxidation.
[0033] The present invention also provides a molded part made of a novel high-strength alloy material resistant to 1100℃, which is prepared by the above-mentioned additive manufacturing method.
[0034] This invention also provides the application of the above-mentioned novel high-strength alloy material resistant to 1100℃ in the manufacture of hot-end components for aero-engines.
[0035] Example 1 This invention provides a novel high-strength alloy material resistant to 1100℃, whose chemical composition, by mass percentage, includes: Ni: 29.25 wt.%, Co: 33.3 wt.%, Cr: 29.3 wt.%, W: 3 wt.%, Ta: 2 wt.%, Ti: 0.35 wt.%, Al: 0.5 wt.%, Re: 1.5 wt.%, Nb: 0.75 wt.%, and C: 0.05 wt.%. The elements are proportioned according to the specified ratio, and alloy powder with a particle size distribution of 15~53 μm is obtained using an existing gas atomization powdering method.
[0036] The additive manufacturing method for the above-mentioned novel high-strength alloy material resistant to 1100℃ includes the following steps: S1. Place the alloy material in the powder supply cylinder of the forming chamber for later use.
[0037] S2. Install the molded substrate into the sealed molding chamber, fill the chamber with high-purity argon gas with a purity of ≥99.99% to form a protective atmosphere, and control the oxygen content to be below the safety threshold.
[0038] S3. Preheat the molded substrate installed in S2 to 200°C.
[0039] S4. Set the forming process parameters as follows: laser power 230W, scanning speed 1000mm / s, melt channel spacing 80μm, powder layer thickness 40μm, and use an interlayer rotation angle of 67° for scanning during laser selective melting. Start the laser beam and spread the alloy material of S1 layer by layer onto the forming substrate after S3 preheating according to the preset scanning path, and melt and solidify layer by layer until the part is completely formed.
[0040] S5. After forming is completed, cool the part with the furnace to below 50°C, open the forming chamber and take out the formed part.
[0041] Example 2 This invention provides a novel high-strength alloy material resistant to 1100℃, whose chemical composition, by mass percentage, includes: Ni: 29.55 wt.%, Co: 32.3 wt.%, Cr: 28.3 wt.%, W: 3 wt.%, Ta: 4 wt.%, Ti: 0.25 wt.%, Al: 0.3 wt.%, Re: 1.5 wt.%, Nb: 0.75 wt.%, and C: 0.05 wt.%. The elements are proportioned according to the specified ratio, and alloy powder with a particle size distribution of 15~53 μm is obtained using an existing gas atomization powdering method.
[0042] The additive manufacturing method for the above-mentioned novel high-strength alloy material resistant to 1100℃ includes the following steps: S1. Place the alloy material in the powder supply cylinder of the forming chamber for later use.
[0043] S2. Install the molded substrate into the sealed molding chamber, fill the chamber with high-purity argon gas with a purity of ≥99.99% to form a protective atmosphere, and control the oxygen content to be below the safety threshold.
[0044] S3. Preheat the molded substrate installed in S2 to 200°C.
[0045] S4. Set the forming process parameters as follows: laser power 200W, scanning speed 1200mm / s, melt channel spacing 80μm, powder layer thickness 40μm, and use an interlayer rotation angle of 67° for scanning during laser selective melting. Start the laser beam and spread the alloy material of S1 layer by layer onto the forming substrate after S3 preheating according to the preset scanning path, and melt and solidify layer by layer until the part is completely formed.
[0046] S5. After forming is completed, cool the part with the furnace to below 50°C, open the forming chamber and take out the formed part.
[0047] Performance testing The formed parts obtained in Example 1 were machined into standard room temperature tensile test specimens and high temperature tensile test specimens. Two parallel specimens were prepared for the room temperature tensile test, labeled 3-16(1) and 3-16(2), and their mechanical properties were tested according to GB / T 228.1 "Metallic materials, tensile testing—Part 1: Room temperature test method". Three parallel specimens were prepared for the high temperature tensile test, labeled 3-16(H1), 3-16(H2), and 3-16(H3), and their mechanical properties were tested according to GB / T 228.2 "Metallic materials, tensile testing—Part 2: High temperature test method". The results are as follows: Figures 1-2 As shown, the molded part has a room temperature tensile strength exceeding 1050 MPa and a high temperature tensile strength exceeding 100 MPa at 1100℃, exhibiting good plasticity.
[0048] The molded part obtained in Example 2 was characterized by microstructure using an optical microscope, and the results are as follows: Figure 3 As shown, there are no obvious defects such as cracks, lack of fusion, or inclusions in the field of view, and only a very small number of micropores exist. This indicates that the alloy of the present invention has excellent compatibility with the laser selective melting process and can achieve high-density forming, providing structural guarantee for excellent high-temperature mechanical properties.
[0049] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit them. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can still be made to the technical solutions of the present invention, and these modifications or equivalent substitutions cannot cause the modified technical solutions to deviate from the spirit and scope of the technical solutions of the present invention.
Claims
1. A novel high-strength alloy material resistant to 1100℃, characterized in that: The chemical composition of the alloy material, by mass percentage, includes: Ni: 27.0~32.0 wt.%, Co: 31.0~36.0 wt.%, Cr: 27.0~32.0 wt.%, W: 1.0~5.0 wt.%, Ta: 1.0~5.0 wt.%, Ti: 0.1~1.0 wt.%, Al: 0.1~1.0 wt.%, Re: 1.0~3.0 wt.%, Nb: 0.1~2.0 wt.%, C: 0.05~0.1 wt.%.
2. The novel high-strength alloy material resistant to 1100℃ according to claim 1, characterized in that: The powder particle size distribution of the alloy material is 15~53μm.
3. The additive manufacturing method for a novel high-strength alloy material resistant to 1100℃ as described in any one of claims 1-2, characterized in that: Includes the following steps: S1. Place the alloy material in the powder supply cylinder of the forming chamber for later use; S2. Install the molded substrate into the sealed molding chamber, fill the chamber with inert gas to form a protective atmosphere, and control the oxygen content to be lower than the safety threshold. S3. Preheat the molded substrate installed in S2; S4. Using laser technology, the alloy material of S1 is laid layer by layer on the preheated forming substrate of S3 according to the preset scanning path, and then melted and solidified layer by layer until the part is completely formed. S5. After forming is completed, the part is cooled with the furnace, and the forming chamber is opened to take out the formed part.
4. The additive manufacturing method for a novel high-strength alloy material resistant to 1100℃ according to claim 3, characterized in that: In S2, the inert gas is high-purity argon or high-purity helium, and the purity of the inert gas is greater than or equal to 99.99%.
5. The additive manufacturing method for a novel high-strength alloy material resistant to 1100℃ according to claim 3, characterized in that: In S3, the preheating temperature is 50~300℃.
6. The additive manufacturing method for a novel high-strength alloy material resistant to 1100℃ according to claim 3, characterized in that: In S4, the laser process parameters are: laser power 200~230W, scanning speed 700~1200mm / s, melt channel spacing 60~100μm, powder layer thickness 20~40μm, and scanning is performed with an interlayer rotation angle of 67° during the laser selective melting process.
7. The additive manufacturing method for a novel high-strength alloy material resistant to 1100℃ according to claim 3, characterized in that: In S5, the parts are cooled to below 50°C in the furnace.
8. A formed part made of a novel high-strength alloy material resistant to 1100℃, characterized in that: It is prepared by the additive manufacturing method according to any one of claims 3-7.
9. The application of the formed part of the novel high-strength alloy material resistant to 1100℃ as described in claim 8, characterized in that: It is used in the manufacture of hot-end components for aero-engines.