KR102545931B1 - Manufacturing method for Mar-M247 alloy multilayer shaped structure with excellent tensile properties and Mar-M247 alloy multilayer shaped structure thereof - Google Patents

Abstract

The present invention relates to a method for manufacturing a Mar-M247 alloy laminate having excellent tensile properties due to control of heat treatment process conditions. It relates to a method for manufacturing a Mar-M247 alloy sculpture.
The method for manufacturing a Mar-M247 alloy laminated body having excellent tensile properties due to the control of heat treatment process conditions according to the present invention is an additive manufacturing method using a laser powder bed fusion (L-PBF) method, a gas spraying method. A first step of providing a Mar-M247 alloy powder made of; A second step of setting process parameters for laser powder bed fusion (L-PBF); A third step of supplying the Mar-M247 alloy powder; A fourth step of selectively irradiating a molding light source to melt the Mar-M247 alloy powder; A fifth step of forming one layer of Mar-M247 material while cooling and solidifying the molten Mar-M247 alloy powder; and a sixth step of repeating and stacking the third to fifth steps until the three-dimensional sculpture of the Mar-M247 material is completed. It is made to include, characterized in that the process variable of the second step is set to a laser power of 170 to 190 (W).

Description

Manufacturing method for Mar-M247 alloy multilayer shaped structure with excellent tensile properties and Mar-M247 alloy multilayer shaped structure using the same structure thereof}

The present invention relates to a method for manufacturing a Mar-M247 alloy laminate having excellent tensile properties due to control of heat treatment process conditions. It relates to a method for manufacturing a Mar-M247 alloy sculpture.

A nickel-based heat-resistant superalloy containing nickel as a base and adding various alloying elements is a material used as a high-temperature heat-resistant material such as a turbine engine. Among nickel-based heat-resistant superalloys, Mar-M247 is the optimal cast type superalloy, and has excellent high-temperature characteristics due to the precipitation of ordered γ' phase (Ni ₃ Al) in the γ-base. It is important to obtain better high-temperature characteristics by controlling the microstructure of these nickel-based superheat-resistant alloys.

In general, if Mar-M247 is manufactured through welding or machining, the quality is excellent, but the processing cost is high and it is difficult to manufacture parts with complex shapes. Therefore, it is necessary to control additive manufacturing process conditions in order to use additive manufacturing, which is advantageous for manufacturing complex shapes, and to obtain the optimal tensile properties of Mar-M247. In addition, it is necessary to control the heat treatment conditions to control the fraction and shape of the γ' phase and to secure excellent tensile properties.

In the conventional case, an alloy is manufactured through casting rather than additive manufacturing or grain boundary shapes are controlled through heat treatment, but the shape and fraction of the γ 'precipitated phase, which is the core of controlling the physical properties of superheat-resistant alloys, cannot be controlled. In addition, there was a problem of low tensile strength.

Korean Patent Registration No. 10-1507898

The present invention has been made to solve the above problems, and an object of the present invention is to provide a superheat-resistant alloy Mar-M247 laminated body having excellent physical properties capable of producing complex shaped parts.

In addition, an object of the present invention is to provide a superheat resistant alloy Mar-M247 laminated body that can control the size and shape of the γ 'phase precipitate by controlling the heat treatment process.

In addition, an object of the present invention is to provide a Mar-M247 laminated structure, which is a super alloy having excellent tensile strength by controlling the heat treatment process.

The technical problems to be solved by the invention are not limited to the above-mentioned technical problems, and other technical problems not mentioned will be clearly understood by those skilled in the art from the description below. You will be able to.

The method for manufacturing a Mar-M247 alloy laminated sculpture having excellent tensile properties due to the control of heat treatment process conditions according to the present invention,

In the additive manufacturing method using Laser Powder Bed Fusion (L-PBF),

A first step of providing Mar-M247 alloy powder produced by a gas injection method;

A second step of setting process parameters for laser powder bed fusion (L-PBF);

A third step of supplying the Mar-M247 alloy powder;

A fourth step of selectively irradiating a molding light source to melt the Mar-M247 alloy powder;

A fifth step of forming one layer of Mar-M247 material while cooling and solidifying the molten Mar-M247 alloy powder; and

A sixth step of repeating and stacking the third to fifth steps until the three-dimensional sculpture of the Mar-M247 material is completed; is made including,

The process variable in the second step is characterized in that the laser power is set to 170 to 190 (W).

By means of solving the above problems, the present invention can manufacture a Mar-M247 laminated body, which is a heat-resistant superalloy having excellent physical properties capable of manufacturing complex-shaped parts.

In addition, the present invention can control the size and shape of the γ 'phase precipitate phase of the superheat-resistant alloy Mar-M247 laminated body by controlling the heat treatment process.

In addition, the present invention can manufacture a Mar-M247 laminated structure, which is a super-heat-resistant alloy having very excellent tensile strength, by controlling the heat treatment process.

1 is a flow chart showing a method for manufacturing a Mar-M247 alloy laminated body having excellent tensile properties due to the control of heat treatment process conditions of the present invention.
2 is a schematic diagram of an apparatus for manufacturing a Mar-M247 alloy laminated sculpture having excellent tensile properties due to heat treatment process condition control according to an embodiment of the present invention.
Figure 3 is a picture of the microstructure of the Mar-M247 alloy laminated body manufactured by an embodiment of the present invention according to an embodiment of the present invention.

The terms used in this specification will be briefly described, and the present invention will be described in detail.

The terms used in the present invention have been selected from general terms that are currently widely used as much as possible while considering the functions in the present invention, but these may vary depending on the intention of a person skilled in the art or precedent, the emergence of new technologies, and the like. Therefore, the term used in the present invention should be defined based on the meaning of the term and the overall content of the present invention, not simply the name of the term.

In the entire specification, when a part is said to "include" a certain component, it means that it may further include other components, not excluding other components unless otherwise stated.

Hereinafter, with reference to the accompanying drawings, embodiments of the present invention will be described in detail so that those skilled in the art can easily carry out the present invention. However, the present invention may be embodied in many different forms and is not limited to the embodiments described herein.

The specific details, including the problem to be solved, the means for solving the problem, and the effect of the invention with respect to the present invention are included in the embodiments and drawings to be described below. Advantages and features of the present invention, and methods for achieving them, will become clear with reference to the embodiments described below in detail in conjunction with the accompanying drawings.

Hereinafter, the present invention will be described in more detail with reference to the accompanying drawings.

In the present invention, the microstructure has a microstructure including a coherent L12-rule FCC γ′ phase from a disordered γ phase matrix and plays an important role in enhancing the strength of the alloy. In the present invention, nickel-based superalloys have a great effect on microstructure (grain size, crystal orientation, and precipitate phase transformation) and mechanical strength (hardness, yield, tensile and fatigue resistance) according to temperature and time changes, so aging conditions and work hardening A related study was conducted. Accordingly, the present invention is a heat treatment process technology for improving the characteristics of the Mar-M247 alloy. It was intended to provide optimal heat treatment process conditions by analyzing the microstructure of the alloy material according to the technology and analyzing the mechanical properties thereof to consider the linkage. .

As shown in Figure 1, the manufacturing method of the Mar-M247 alloy laminated body having excellent tensile properties due to the control of heat treatment process conditions is performed by the following steps.

First, in the first step (S10), Mar-M247 alloy powder is provided. The present invention is performed according to additive manufacturing using a laser powder bed fusion (L-PBF), and provides Mar-M247 alloy powder produced by a gas spraying method in step 1 (S10).

The Mar-M247 alloy is prepared using Carpenter's CM247LC. In addition, the Mar-M247 alloy contains tungsten (W): 9.5 wt%, cobalt (Co): 9.2 wt%, chromium (Cr) 8.1 wt%, aluminum (Al) 5.6 wt%, tantalum (Ta): 3.2 wt% %, hafnium (Hf): 1.4 wt%, titanium (Ti): 0.7 wt%, molybdenum (Mo): 0.5 wt%, carbon (C): 0.075 wt%, zirconium (Zr): 0.015 wt%, boron (B): 0.015% by weight and the remainder Ni.

In addition, the Mar-M247 alloy powder preferably has a particle size of 15 to 45 μm.

Next, in the second step (S20), process parameters are set. The second step (S20) sets process parameters for Laser Powder Bed Fusion (L-PBF). As shown in FIG. 2, the process variable is controlled by setting the power and scan speed of the laser.

The laser power is preferably set to 170 to 190 (W). When the laser power is less than 170 (W), the energy is too low, so the stacking time is too long, and stacking defects such as unmelted powder are generated, so that the tensile strength of the stacked object is too low and sufficient energy density cannot be irradiated. This causes a problem of deterioration in tensile properties, and when the laser power exceeds 190 (W), powder vaporization occurs and there is a possibility that the laminated object may be physically deformed.

In addition, the scan speed is preferably set to 900 to 1,100 (mm/s). The scan speed is set to the maximum scan speed within a range that can be molded, and when the scan speed is less than 900 (mm/s), the scan speed is too low, causing a problem in that the laminate production time takes too long, and the scan speed is too low. If it exceeds 1,100 (mm/s), the amount of energy applied to the powder is reduced, and stacking faults occur along the scan direction, so that the resulting laminated object may be physically deformed. Therefore, it is preferable to perform under the above conditions. .

When the laser power is high and the scan speed is slow, the powder is vaporized as excessive energy is irradiated, and there is a risk of deteriorating surface roughness and physical properties. On the other hand, when the laser power is low and the scan speed is high, energy is not irradiated and unmelted powder is formed, resulting in stacking defects. Therefore, in order to manufacture a molded body with high productivity, it is necessary to set optimal process conditions with high laser power and high scan speed.

The hatching space is an interval between laser scan paths along which the laser moves, and is preferably 130 to 170 μm. When the hatching space is less than 130 μm, productivity is reduced, and when the hatching space exceeds 170 μm, the overlapping area is reduced and porosity is increased. It is desirable to do

The layer thickness (layer thickness) is preferably 30 to 40 ㎛. If the layer thickness is less than 30 μm, there is a risk of vaporization of the powder due to excessive heat input, and if the layer thickness exceeds 40 μm, heat transfer is not performed properly and unmelted powder increases. Since the probability is high, it is preferable to perform under the above conditions.

Higher productivity requires higher energy densities using higher laser powers and scan speeds. Since the 1980s, laser power and scan speed have generally been limited to less than 200 (W) and 1200 (mm/s), respectively, due to operational stability and limited specifications of equipment. As shown in FIG. 2, efforts have been made to obtain appropriate mechanical properties by controlling various process variables under the laser power and scan speed conditions of the present invention.

Build rate (VB), which is a representative indicator of the productivity of the laser powder bed fusion (L-PBF) process, is determined by the following equation (1).

VB = VS X Δy X Δz (1)

(Where VS is the scan speed, Δy is the increase in hatching space, and Δz is the increase in layer height)

The productivity of laser powder bed fusion (L-PBF) parts is affected by volume according to the control of process parameters, and the scan speed is the most important parameter for improving productivity.

Next, in the third step (S30), the Mar-M247 alloy powder is supplied. In the third step (S30), the Mar-M247 alloy powder is supplied.

Next, in the fourth step (S40), the Mar-M247 alloy powder is melted. In the fourth step (S40), the alloy powder is melted by selectively irradiating a shape light source in an Ar gas atmosphere. In the fourth step (S40), the irradiation of the modeling light source is carried out in an inert gas atmosphere (Ar Gas) and an oxygen concentration of 100 ppm or less. When carried out at an oxygen concentration higher than 100 PPM, a problem occurs in that the molten powder reacts with oxygen to form an oxide, so it is preferable to carry out the above conditions.

Next, in the fifth step (S50), one layer of Mar-M247 material is formed.

Next, the sixth step (S60) is laminated by repeating the third step (S30) to the fifth step (S50). In the sixth step (S60), the third step (S30) to the fifth step (S50) are repeatedly laminated until the three-dimensional sculpture made of the Mar-M247 material is completed.

Next, the seventh step (S70) is a solution heat treatment. The seventh step (S70) is a solution heat treatment at 1,200 to 1,300 ° C. for 1.5 to 2.5 hours. When the solution heat treatment is performed at less than 1,200 ° C, a problem occurs that the precipitated phase is not properly dissolved in the base and thus a single phase is not formed, and when the solution heat treatment is performed at a temperature exceeding 1,300 ° C, a problem occurs that the alloy melts, so it is performed under the above conditions It is desirable to do In addition, when the solution heat treatment is performed for less than 1.5 hours, a problem occurs that the precipitation phase is not dissolved in the base and cannot be made into a single phase, just as the temperature is low, and if it is 2.5 hours, it is sufficiently dissolved to form a single phase. is an unnecessary process.

Next, in the eighth step (S80), a primary aging process is performed. The eighth step (S80) may be subjected to primary aging treatment in the following two methods.

The first step is the 8-1st step (S81) of primary aging at 850 to 900 °C. The 8-1 step (S81) is performed at 850 to 900 ° C. for 23 to 25 hours.

The second is the 8-2 step (S82) of primary aging treatment at 950 to 1,100 ° C. The 8-2 step (S82) is performed at 950 to 1,100 ° C. for 4 to 6 hours.

As stated above, the primary purpose of the aging is to control the uniformity of the precipitated phase (γ′) on the matrix (γ). At this time, if the temperature of the primary aging is too low, precipitates (γ') are formed in unstable places such as grain boundaries or inclusions, and as a result, precipitated phases (γ') are formed non-uniformly as a whole. If the temperature is too high, there is a problem in that the solid solution limit is increased by that much, and the precipitated phase (γ') is dissolved again as a matrix, and the fraction of the precipitated phase (γ') is lowered. Therefore, in the present invention, primary aging is performed by setting an appropriate temperature (a temperature enough to form a uniform precipitated phase) and time as described above, and the difference in tensile strength can be confirmed. The time is about 5 hours so that the precipitated phase (γ') can be precipitated sufficiently uniformly, and if more than that, there is a problem that the crystal grains and the precipitated phase (γ') can be coarsened.

Next, in the ninth step (S90), secondary aging is performed. In the ninth step (S90), when the 8-2 step (S82) is performed, secondary aging is performed at 750 to 800 °C. The ninth step (S90) is performed at 750 to 800 ° C. for 23 to 25 hours.

The purpose of the secondary aging is to control the size of the precipitated phase (γ'). If the temperature is set too low, there is a risk of forming coarse precipitates, and if the temperature is too high, there is a problem that the precipitates may be dissolved again in the matrix and the fraction of the precipitated phase (γ′) may be lowered. It is important to form precipitates (γ') through an appropriate time (24 h in this experiment) because there is a problem in that the precipitate coarsens and the precipitate phase becomes coarse when the time is prolonged.

The Mar-M247 alloy laminated body of the present invention is characterized in that it is manufactured by the Mar-M247 alloy laminated body manufacturing method having excellent tensile properties due to the heat treatment process condition control described above.

The Mar-M247 alloy laminated sculpture is laminated by providing Mar-M247 alloy powder using a laser powder bed fusion (L-PBF), and the Mar-M247 alloy powder is manufactured using Carpenter's CM247LC do. In addition, the CM247LC alloy powder contains tungsten (W): 9.5 wt%, cobalt (Co): 9.2 wt%, chromium (Cr) 8.1 wt%, aluminum (Al) 5.6 wt%, tantalum (Ta): 3.2 wt% , Hafnium (Hf): 1.4% by weight, Titanium (Ti): 0.7% by weight, Molybdenum (Mo): 0.5% by weight, Carbon (C): 0.075% by weight, Zirconium (Zr): 0.015% by weight, Boron ( B): 0.015% by weight and the balance Ni.

The Mar-M247 alloy laminate is characterized in that it is manufactured by controlling the laser power to 150 to 170 (W) during additive manufacturing. When the laser power is less than 170 (W), the energy is too low, so the stacking time is too long, and stacking defects such as unmelted powder are generated, so that the tensile strength of the stacked object is too low and sufficient energy density cannot be irradiated. This causes a problem of deterioration in tensile properties, and when the laser power exceeds 190 (W), powder vaporization occurs and there is a possibility that the laminated object may be physically deformed.

In addition, the Mar-M247 alloy laminated body is characterized in that the scan speed is set to 900 to 1,100 (mm / s) during additive manufacturing. The scan speed is set to the maximum scan speed within a range that can be molded, and when the scan speed is less than 900 (mm/s), the scan speed is too low, causing a problem in that the laminate production time takes too long, and the scan speed is too low. If it exceeds 1,100 (mm/s), the amount of energy applied to the powder decreases, and stacking faults occur along the scan direction, so that the resulting laminated object may be physically deformed. Therefore, it is preferable to perform under the above conditions. .

When the laser power is high and the scan speed is slow, the powder is vaporized as excessive energy is irradiated, and there is a risk of deteriorating surface roughness and physical properties. On the other hand, when the laser power is low and the scan speed is high, energy is not irradiated and unmelted powder is formed, resulting in stacking defects. Therefore, in order to manufacture a molded body with high productivity, it is necessary to set optimal process conditions with high laser power and high scan speed.

Higher productivity requires higher energy densities using higher laser powers and scan speeds. Since the 1980s, laser power and scan speed have generally been limited to less than 200 (W) and 1200 (mm/s), respectively, due to operational stability and limited specifications of equipment. As shown in FIG. 2, efforts have been made to obtain appropriate mechanical properties by controlling various process variables under the laser power and scan speed conditions of the present invention.

Build rate (VB), which is a representative indicator of the productivity of the laser powder bed fusion (L-PBF) process, is determined by the following equation (1).

VB = VS*?*Δy*?*Δz (1)

(Where VS is the scan speed, Δy is the increase in hatching space, and Δz is the increase in layer height)

The productivity of laser powder bed fusion (L-PBF) parts is affected by volume according to the control of process parameters, and the scan speed is the most important parameter for improving productivity.

The Mar-M247 alloy laminated body is characterized in that it is manufactured by sequentially performing solution heat treatment and aging treatment after lamination using Laser Powder Bed Fusion (L-PBF).

The aging treatment is characterized in that the first aging treatment at 850 to 900 ° C., or the second aging treatment at 750 to 800 ° C. after the first aging treatment at 950 to 1,100 ° C.

It is characterized in that the γ' phase of 1 μm or less is uniformly distributed through the primary aging treatment.

The secondary aging treatment is characterized by precipitating a γ′ phase of 1 μm or less.

The Mar-M247 alloy laminated body having excellent tensile properties according to the present invention is characterized by having a tensile strength of 1,300 MPa.

In addition, it is characterized in that the yield strength (yield strength) is 1,280 MPa.

In addition, it is characterized in that the elongation (elongation) is 8% or more.

Tensile strength, yield strength and elongation were measured using the Mar-M247 alloy laminated body manufactured by the method described below. Hereinafter, examples will be described in detail to aid understanding of the present invention. However, the following examples are merely illustrative of the contents of the present invention, but the scope of the present invention is not limited to the following examples. The embodiments of the present invention are provided to more completely explain the present invention to those skilled in the art.

Example

The Mar-M247 alloy powder prepared through the gas injection method was laminated and manufactured using a laser powder bed fusion (L-PBF) method. Specimens were prepared with a laser power of 160 (W) and a scanning speed of 800 (mm/s) among process parameters.

Then, each specimen was prepared under the following conditions. Each specimen was subjected to the same solution heat treatment for 2 hours at a temperature of 1,250 °C for all specimens to form a single phase. In addition, in order to obtain a precipitation strengthening effect, a one-step aging treatment and a two-step aging treatment were performed as shown in Table 1 below.

sample solution heat treatment
(solution heat treatment) 1st aging
(One-step aging treatment) 2nd aging
(Two-step aging treatment) S8 1,250 °C (2h) 870 °C (24h) - T9-7 1,250 °C (2h) 980 °C (5h) 770°C (24h) T9-8 1,250 °C (2h) 980 °C (5h) 870 °C (24h) T9-9 1,250 °C (2h) 980 °C (5h) 970°C (24h) T10-8 1,250 °C (2h) 1080 °C (5h) 870 °C (24h) T10-9 1,250 °C (2h) 1080 °C (5h) 970°C (24h)

comparative example

The Mar-M247 alloy powder prepared through the gas injection method was laminated and manufactured using a laser powder bed fusion (L-PBF) method. However, as shown in the process conditions in Table 2 below, the solution heat treatment is performed differently from the conditions of the present invention for one-step aging treatment and two-step aging treatment. did

sample hot rolled
(heated rolling) solution heat treatment
(solution heat treatment) heat treatment Comparative Example 1 1,150°C (3 times) 1,175 °C (15 minutes) - Comparative Example 2 1,150°C (3 times) 1,175 °C (15 minutes) 1,000 ℃ (1 hour)

Experimental example

(1) Tensile strength

In order to evaluate the tensile properties of the specimens in Examples and Comparative Examples, a tensile test was performed at room temperature at a strain rate of 10 ^-3 /s. Tensile specimens were manufactured according to ASTM E8/E8M with a gauge length of 6.4 mm and a gauge diameter of 2.5 mm.

(2) yield strength

After conducting the tensile test, the yield strength was measured by using a straight line in the elastic region with a 0.2% offset at the point where the strain is zero.

(3) Elongation

When the break point of the stress-strain curve and a straight line with the same slope as the slope of the elastic region intersect, the value of the x-intercept (y=0) of the straight line is the elongation.

Table 3 shows the tensile strength, yield strength and elongation results obtained with the specimens prepared in Examples and Comparative Examples.

sample Yield Strength (MPa) Tensile Strength (MPa) Elongation (%) Testing temp.(℃) S8 971 1280 8 25 T9-7 956 1260 8 25 T9-8 902 1194 10 25 T9-9 916 1268 12 25 T10-8 849 1089 8 25 T10-9 1024 1023 9 25 Comparative Example 1 352 825 75 25 Comparative Example 2 352 843 59 25

In the comparative example experiment, the superalloy was not manufactured by the additive manufacturing method, and the heat treatment method was also different. In an embodiment of the present invention, the precipitated phase is controlled by controlling the first/second aging time and temperature.

In the experiment of Comparative Example 1, after casting, 50% hot rolling was performed three times at 1,050 to 1,150 °C, and solution treatment was performed at 1,175 °C, followed by rapid water cooling to prepare a superheat resistant alloy. Comparative Example 2 The alloy prepared in Comparative Example 1 was further subjected to heat treatment at 1,000 °C for 1 hour.

This is a comparative example to show that even the same superalloy has high tensile strength and yield strength at room temperature by controlling the first/secondary aging time and temperature.

The uniform precipitated phase of the γ 'phase was controlled through six different heat treatment processes (S8 to T10-9) of the Mar-M247 alloy laminated composition prepared by laminating through the examples. To form a single phase, solution heat treatment was performed at 1250 °C (2h) in the same way for all specimens, and one step/two step aging was performed to obtain a precipitation strengthening effect.

Since one step aging (870 °C to 1080 °C) proceeds at a high temperature, as shown in FIG. 4, it was confirmed that a uniform γ' precipitate phase of 1 μm or less was distributed. This improved the morphology of carbides and their distribution at grain boundaries.

In addition, in the two-step aging (780 °C ~ 970 °C), a γ' phase of about 1 μm in size was precipitated and generally contributed to the tensile strength. That is, the higher the temperature of the two step aging, the finer γ' phase was precipitated.

It can be seen that Mar-M 247 having a tensile property of about 1,300 MP is manufactured as shown in FIG. 4 by forming a small and uniform cubic γ' precipitated phase through one step/two step aging.

In the conventional case, excellent physical properties were obtained through casting for the manufacture of Mar-M247 alloy, but there is a disadvantage in that parts of complex shapes cannot be manufactured. Therefore, the present invention suggests laser power and scan speed, which are the optimal processes for obtaining a super heat-resistant alloy, Mar-M247 laminated body, and provides heat treatment conditions capable of controlling the γ' precipitated phase.

According to the present invention, the tensile strength obtained through the heat treatment process is 1,300 MPa, and it is possible to manufacture a superheat-resistant alloy having a tensile strength of 450 to 540 MPa compared to the prior art.

By means of solving the above problems, the present invention can manufacture a Mar-M247 laminated body, which is a heat-resistant superalloy having excellent physical properties capable of manufacturing complex-shaped parts.

In addition, the present invention can control the size and shape of the γ 'phase precipitate phase of the superheat-resistant alloy Mar-M247 laminated body by controlling the heat treatment process.

In addition, the present invention can manufacture a Mar-M247 laminated structure, which is a super-heat-resistant alloy having very excellent tensile strength, by controlling the heat treatment process.

As such, it will be understood that the technical configuration of the present invention described above can be implemented in other specific forms without changing the technical spirit or essential features of the present invention by those skilled in the art to which the present invention pertains.

Therefore, the embodiments described above should be understood as illustrative and not restrictive in all respects, and the scope of the present invention is indicated by the claims to be described later rather than the detailed description, and the meaning and scope of the claims and their All changes or modified forms derived from equivalent concepts should be construed as being included in the scope of the present invention.

S10. The first step to provide Mar-M247 alloy powder
S20. 2nd step to set process parameters
S30. The third step of supplying the Mar-M247 alloy powder
S40. The fourth step of melting the Mar-M247 alloy powder
S50. The 5th step of forming one layer of Mar-M247 material
S60. 6th step of laminating by repeating the 3rd to 5th steps
S70. 7th step of solution heat treatment
S80. 8th step of primary aging treatment
S81. Step 8-1 of primary aging treatment at 850 to 900 ° C.
S82. Step 8-2 of primary aging treatment at 950 to 1,100 ° C.
S90. 9th step of secondary aging

Claims (14)

In the additive manufacturing method using Laser Powder Bed Fusion (L-PBF),
A first step of providing Mar-M247 alloy powder produced by a gas injection method;
A second step of setting process parameters for laser powder bed fusion (L-PBF);
A third step of supplying the Mar-M247 alloy powder;
A fourth step of selectively irradiating a molding light source to melt the Mar-M247 alloy powder;
A fifth step of forming one layer of Mar-M247 material using the molten Mar-M247 alloy powder;
A sixth step of repeating and stacking the third to fifth steps until the three-dimensional sculpture of the Mar-M247 material is completed;
A seventh step of solution heat treatment at 1,200 to 1,300 ° C. for 2 hours;
An 8-1 step of primary aging treatment at 850 to 900 ° C. for 23 to 25 hours;
An 8-2 step of primary aging treatment at 950 to 1,100 ° C. for 4 to 6 hours; and
A ninth step of secondary aging treatment at 750 to 800 ° C. for 23 to 25 hours;
In the first step, the Mar-M247 alloy powder is prepared with a particle size of 15 to 45 μm,
The process variable in the second step is set to a laser power of 170 to 190 (W),
The process variable in the second step is set to a scan speed of 900 to 1,100 mm/s,
The hatching space, which is the interval between the laser scan paths through which the laser moves, is 130 to 170 μm,
Set the layer thickness to 30 to 40 μm,
The modeling light source in the fourth step is carried out in an argon (Ar) gas, which is an inert gas atmosphere, while maintaining an oxygen concentration of 100 ppm or less,
The Mar-M247 alloy powder contains tungsten (W): 9.5 wt%, cobalt (Co): 9.2 wt%, chromium (Cr) 8.1 wt%, aluminum (Al) 5.6 wt%, tantalum (Ta): 3.2 wt% , Hafnium (Hf): 1.4% by weight, Titanium (Ti): 0.7% by weight, Molybdenum (Mo): 0.5% by weight, Carbon (C): 0.075% by weight, Zirconium (Zr): 0.015% by weight, Boron ( B): A method for manufacturing a Mar-M247 alloy laminated molding having excellent tensile properties, characterized in that it is composed of 0.015% by weight and the balance Ni.
delete delete delete delete delete delete After lamination using the laser powder bed fusion (L-PBF) method according to claim 1,
It is prepared by sequentially performing solution heat treatment and aging treatment,
The aging treatment,
Primary aging treatment at 850 to 900 ° C., or
After primary aging treatment at 950 to 1,100 ° C., secondary aging treatment at 750 to 800 ° C.,
In the first aging treatment, the γ' phase of 1 μm or less is uniformly distributed,
The secondary aging treatment precipitates a γ' phase of 1 μm or less,
Tensile strength is 1,300 MPa,
The yield strength is 1,280 MPa,
Manufactured with an elongation of 8% or more,
In the lamination using the laser powder bed fusion (L-PBF)
The hatching space, which is the interval between the laser scan paths through which the laser moves, is 130 to 170 μm,
Set the layer thickness to 30 to 40 μm ,
Mar-M247 alloy powder contains tungsten (W): 9.5 wt%, cobalt (Co): 9.2 wt%, chromium (Cr) 8.1 wt%, aluminum (Al) 5.6 wt%, tantalum (Ta): 3.2 wt%, Hafnium (Hf): 1.4 wt%, Titanium (Ti): 0.7 wt%, Molybdenum (Mo): 0.5 wt%, Carbon (C): 0.075 wt%, Zirconium (Zr): 0.015 wt%, Boron (B ): Mar-M247 alloy laminated body with excellent tensile properties, characterized in that it consists of 0.015% by weight and the balance Ni.
delete delete delete delete delete delete

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