JP7207067B2 - Manufacturing method of metal member - Google Patents

Description

The present disclosure relates to a method of making a metal member.

2. Description of the Related Art Conventionally, various three-dimensional modeling methods have been employed as methods for producing metal members used as parts of various industrial devices. Patent Literature 1 discloses a three-dimensional additive manufacturing method capable of manufacturing a metal member using metal powder that can be solidified by irradiation with a high-energy beam. However, there are cases where cracks and voids are generated in metal members that are shaped by such a three-dimensional layered manufacturing method. Therefore, there is a method of removing cracks and voids by, for example, performing hot isostatic pressing (HIP) processing on a metal member formed by a three-dimensional layered manufacturing method.

However, although HIP treatment is effective in removing cracks and voids generated inside the metal member, it is difficult to remove cracks that partially reach the surface of the metal member, for example. difficult. Therefore, Patent Literature 2 discloses a processing method in which shot peening or the like for plastically deforming the surface of a part is performed before HIP processing.

Japanese Patent Application Publication No. 2009-544501 Japanese translation of PCT publication No. 2015-516299

However, the processing method disclosed in Patent Literature 2 requires a processing device for performing surface processing such as shot peening in addition to the HIP device for performing HIP processing. In other words, the process until completion of manufacturing the metal member is complicated, and the equipment for manufacturing the metal member is also large-scale.

Accordingly, an object of the present disclosure is to provide a method of manufacturing a metal member that is advantageous in making cracks and voids less likely to remain.

One aspect of the present disclosure is a method for manufacturing a metal member formed from metal powder, comprising: a first shaping step of processing the metal powder by three-dimensional metal additive manufacturing to shape an outer shell structure; A second molding step of forming an internal structure independent of the outer shell structure by interposing an intermediate layer composed of metal powder between the body and processing the metal powder by three-dimensional metal additive manufacturing; and a treatment step of subjecting the outer shell structure, the intermediate layer, and the inner structure to hot isostatic pressing after the first shaping step and the second shaping step.

In the method for producing the metal member described above, before the first shaping process and the second shaping process, the same powder layers that will be the outer shell structure, the intermediate layer, and the inner structure are formed by three-dimensional metal additive manufacturing. A preheating step of heating the metal powder at a temperature below the melting point of the metal powder may also be included. The second shaping process is performed before and after the first shaping process for each same powder layer, and the manufacturing method includes an intermediate layer forming process for forming an intermediate layer between the first shaping process and the second shaping process. may contain. The number of powder layers forming the outer shell structure positioned below or above the internal structure in the stacking direction may be less than the number of powder layers forming the internal structure. The number of powder layers forming the intermediate layer positioned below or above the internal structure in the stacking direction may be less than the number of powder layers forming the internal structure. The modeling conditions for the three-dimensional metal additive manufacturing in the second modeling process may be different from the modeling conditions for the three-dimensional metal additive manufacturing in the first modeling process. In the second forming step, a communicating structure may be formed in the intermediate layer to allow a portion of the outer shell structure and a portion of the internal structure to communicate with each other. The metal member includes a first part and a second part, the first part being shaped by a third shaping step in which metal powder is processed and shaped by three-dimensional metal additive manufacturing, and the second part being the first It may be shaped by a shaping process and a second shaping process, and the treatment process may be applied to the first part and the second part after the first shaping process, the second shaping process, and the third shaping process. The modeling conditions for the three-dimensional metal additive manufacturing in the third modeling process may be different from at least one of the modeling conditions for the three-dimensional metal additive manufacturing in the first modeling process or the second modeling process. Alternatively, the metal member may be a turbine blade, the first portion may be a blade portion of the turbine blade, and the second portion may be a blade root portion of the turbine blade.

Advantageous Effects of Invention According to the present disclosure, it is possible to provide a method for manufacturing a metal member that is advantageous in making cracks and voids less likely to remain.

1 is a diagram showing a metal member to be manufactured in the first embodiment of the present disclosure; FIG. It is a figure which shows the structure of a three-dimensional metal additive manufacturing apparatus. It is a figure which shows the flow of the three-dimensional metal additive manufacturing process in 1st Embodiment. FIG. 2 is a diagram showing the configuration of a hot isostatic pressurizing device containing metal members. It is a figure which shows the other shape of an intermediate member. FIG. 5 is a diagram showing a turbine blade to be manufactured in the second embodiment of the present disclosure; It is a figure which shows the flow of the three-dimensional metal additive manufacturing process in 2nd Embodiment. FIG. 2 is a diagram showing the configuration of a hot isostatic pressurization device that accommodates turbine blades; It is a figure which shows the metal member produced by the conventional production method.

Hereinafter, each embodiment of the present disclosure will be described in detail with reference to the drawings. Here, the dimensions, materials, and other specific numerical values shown in each embodiment are merely examples, and do not limit the present disclosure unless otherwise specified. Elements having substantially the same function and configuration are denoted by the same reference numerals to omit redundant description, and elements that are not directly related to the present disclosure are omitted from the drawings.

(First embodiment)
First, a method for manufacturing a metal member according to the first embodiment of the present disclosure will be described. FIG. 1 is a perspective view showing a block 10 as a metal member to be manufactured by the manufacturing method according to this embodiment. FIG. 1(a) is a diagram showing a block to be modeled using the three-dimensional modeling apparatus 1. FIG. The block shown in FIG. 1( a ) is in the process of making block 10 . Therefore, hereinafter, the block in the state of FIG. 1(a) is referred to as "intermediate member 10A" in order to distinguish it from the block 10 which is the final product. FIG. 1(b) is a diagram showing a block 10 as a final product produced by subjecting the intermediate member 10A to HIP processing using a HIP device 40. FIG. In each drawing according to this embodiment, the Z-axis is taken in the vertical direction, and the X-axis and the Y-axis perpendicular to the X-axis are taken in the horizontal plane perpendicular to the Z-axis. In addition, in FIG. 1, the block 10 and the intermediate member 10A are partially drawn in a cross section cut along the YZ plane in order to clarify the internal state.

The fabrication method of the present disclosure is applicable to fabrication of metal members that are widely used as parts of various industrial devices. Therefore, the material and shape of the metal member are various. In the present embodiment, the block 10, which is an example of the metal member, will be described as a cube having a side length of L3.

In the method of manufacturing a metal member according to the present embodiment, first, an intermediate member 10A as shown in FIG. 1A is formed by three-dimensional metal additive manufacturing. Hereinafter, three-dimensional metal additive manufacturing is abbreviated as three-dimensional manufacturing.

The intermediate member 10</b>A has an outer shell structure 12 , an inner structure 14 and an intermediate layer 16 . The outer shell structure 12 is a box-shaped body forming the outer shell of the intermediate member 10A. The outer shell structure 12 has a cubic shape with a side length of L1. The thickness of the outer shell structure 12 is T1 in all XYZ directions. The internal structure 14 is a cube enclosed in the outer shell structure 12 with the intermediate layer 16 interposed therearound. The length of one side of the internal structure 14 is L2. The intermediate layer 16 is a layer that contacts the outer shell structure 12 on the outside and contacts the internal structure 14 on the inside. The thickness of the intermediate layer 16 is T2 in all XYZ directions. In this embodiment, the thickness T1 of the outer shell structure 12 and the thickness T2 of the intermediate layer 16 are the same value for convenience. The outer shell structure 12 and the inner structure 14 are formed by processing the metal powder P (see FIG. 2, etc.) as follows. On the other hand, the intermediate layer 16 is composed of the metal powder P itself.

FIG. 2 is a schematic cross-sectional view showing an example of the configuration of the three-dimensional modeling apparatus 1 used in the manufacturing method according to this embodiment. The three-dimensional modeling apparatus 1 irradiates the metal powder P with an electron beam E to melt and solidify the metal powder P, and stacks the solidified metal powder P to form a three-dimensional object. This device uses a bed system. The metal powder P in this embodiment is, for example, CM247LC, which is a Ni-based heat-resistant alloy. The metal powder P is composed of many powder bodies. Also, as the metal powder P, if it can be melted and solidified by the irradiation of the electron beam E, granules having a particle diameter larger than that of the powder may be used.

It should be noted that the metal powder P may be preheated by further irradiating the metal powder P with the electron beam E before each molding process of the powder layer in which the metal powder P is melted and solidified. Preheating, also called preheating, is a process of heating the metal powder P at a temperature below the melting point of the metal powder P. By this preheating, the metal powder P is heated and pre-sintered, the accumulation of negative charges in the metal powder P due to the irradiation of the electron beam E is suppressed, and the metal powder P scatters when the electron beam E is irradiated. It is possible to suppress the rising smoke phenomenon.

A three-dimensional modeling apparatus 1 includes a beam emitting unit 2 , a modeling unit 3 and a control unit 4 .

The beam emitting unit 2 is a unit that emits an electron beam E to the metal powder P in the shaping unit 3 to melt the metal powder P. As shown in FIG. The electron beam E is a charged particle beam formed by linear motion of electrons, which are charged particles. The beam emission section 2 includes an electron gun section 21 , an aberration coil 22 , a focus coil 23 , a deflection coil 24 and a column 25 .

The electron gun section 21 emits an electron beam E toward the shaping section 3 . The electron gun section 21 is electrically connected to the control section 4 and operates upon receiving a control signal from the control section 4 .

The aberration coil 22 is installed around the electron beam E emitted from the electron gun section 21 and corrects the aberration of the electron beam E. As shown in FIG. The aberration coil 22 is electrically connected to the controller 4 and operates upon receiving a control signal from the controller 4 . Depending on the type of the 3D modeling apparatus 1, the installation of the aberration coil 22 may be omitted.

The focus coil 23 is installed around the electron beam E emitted from the electron gun part 21, converges the electron beam E, and adjusts the focus state at the irradiation position of the electron beam E. As shown in FIG. The focus coil 23 is electrically connected to the controller 4 and operates upon receiving a control signal from the controller 4 .

The deflection coil 24 is installed around the electron beam E emitted from the electron gun section 21, and adjusts the irradiation position of the electron beam E according to a control signal. Since the deflection coil 24 electromagnetically deflects the beam, the scanning speed during irradiation of the electron beam E can be increased compared to the case of mechanically deflecting the beam. Also, the deflection coil 24 is electrically connected to the control section 4 and operates upon receiving a control signal from the control section 4 .

The column 25 is, for example, a cylindrical housing. Column 25 accommodates electron gun section 21 , aberration coil 22 , focus coil 23 and deflection coil 24 .

The shaping section 3 is a unit that shapes a metal member into a desired shape. The modeling section 3 includes a chamber 30 , a stage 31 , an elevator 32 , a modeling tank 33 , a recoater 34 and a hopper 35 .

The chamber 30 is, for example, a box-shaped housing. Chamber 30 houses stage 31 , elevator 32 , recoater 34 and hopper 35 . The chamber 30 is connected with the column 25 of the beam emitting section 2 . The internal space of the chamber 30 communicates with the internal space of the column 25 in which the electron gun section 21 is arranged. Also, the internal space of the chamber 30 is maintained in a vacuum or nearly vacuum state.

The stage 31 supports the intermediate member 10A. The stage 31 is positioned on an extension line in the direction of emission of the electron beam E, and is, for example, a disc-shaped member whose main plane is a horizontal plane. Also, the stage 31 is arranged in the modeling tank 33 and is movable in the Z direction. A bottom plate 36 is installed on the surface of the stage 31 . Metal powder P is supplied directly onto the bottom plate 36 .

The elevator 32 is a mechanism for raising and lowering the stage 31 . The elevator 32 is electrically connected to the controller 4 and operates upon receiving a control signal from the controller 4 . For example, the elevator 32 moves the stage 31 upward at the initial stage of molding the metal member, and lowers the stage 31 each time the metal powder P is melted and solidified on the stage 31 and stacked. Any mechanism may be used as the elevator 32 as long as it is a mechanism capable of lifting the stage 31 .

The modeling tank 33 is a cylindrical container having an inner wall that matches the outer shape of the stage 31 . In the example of this embodiment, the shape of the stage 31 is disc-shaped, so the shape of the modeling tank 33 is a cylinder having an inner wall whose cross-sectional shape is concentric with respect to the axis along the movement direction of the stage 31. is. As a result, the metal powder P supplied to the modeling tank 33 is prevented from leaking downward from the stage 31 . In order to further suppress leakage of the metal powder P, a sealing material may be provided on the outer edge of the stage 31 . Further, the shape of the modeling tank 33 is not limited to a cylindrical shape, and may be a rectangular tube shape with a rectangular cross section.

The recoater 34 is a powder coating mechanism that supplies the metal powder P above the stage 31 and smoothes the surface of the metal powder P. As shown in FIG. The recoater 34 is, for example, a rod-shaped or plate-shaped member. The recoater 34 supplies the metal powder P to the irradiation area of the electron beam E by moving horizontally as indicated by the arrow in FIG. 2, and smoothes the surface of the metal powder P. Further, the movement of the recoater 34 is controlled by an actuator (not shown) or the like. As a mechanism for leveling the metal powder P, a mechanism other than the recoater 34 may be used.

The hopper 35 is a container that accommodates the metal powder P before application. The hopper 35 has a discharge port 35a for discharging the metal powder P at its lower portion. The metal powder P discharged from the discharge port 35 a flows directly onto the stage 31 or is supplied onto the stage 31 by the recoater 34 . As a mechanism for supplying the metal powder P in layers onto the stage 31, a mechanism other than the recoater 34 and the hopper 35 may be used.

The control unit 4 is a unit that controls the overall operation of the three-dimensional modeling apparatus 1 . The control unit 4 includes, for example, a computer having a CPU, ROM, or RAM. The control unit 4 performs elevating control of the stage 31, operation control of the recoater 34, emission control of the electron beam E, operation control of the deflection coil 24, and the like, for example.

The control unit 4 causes modeling to be performed using, for example, three-dimensional CAD (Computer-Aided Design) data of the intermediate member 10A. The three-dimensional CAD data is shape data of the intermediate member 10A that is input to the control unit 4 in advance. The control unit 4 generates two-dimensional slice data based on the three-dimensional CAD data. The slice data is, for example, horizontal cross-sectional data of the intermediate member 10A, and is a collection of a large number of data corresponding to each position in the stacking direction. Based on the slice data, the control unit 4 determines the area of the metal powder P to be irradiated with the electron beam E, and outputs a control signal to the deflection coil 24 according to the area. As a result, the electron beam E is applied to a region corresponding to the shape of the intermediate member 10A. Also when preheating the metal powder P, the control unit 4 outputs a control signal to the deflection coil 24 of the beam emission unit 2, and scans and irradiates the electron beam E onto the heating region on the stage 31. Let

Next, a three-dimensional modeling process using the three-dimensional modeling apparatus 1 will be described.

FIG. 3 is a schematic cross-sectional view showing the flow of the three-dimensional modeling process for modeling the intermediate member 10A by the three-dimensional modeling apparatus 1 in chronological order. In the three-dimensional molding process, the metal powder P on the bottom plate 36 is irradiated with the electron beam E to repeat the molding of a part of the intermediate member 10A, thereby molding the intermediate member 10A in a layered manner.

First, referring to FIG. 3A, the molding of the intermediate member 10A in the first layer La1, which is the bottom layer of the powder layer La, will be described. The three-dimensional modeling apparatus 1 performs powder supply processing on the first layer La1. The powder supply process is a process of supplying the metal powder P onto the bottom plate 36 and smoothing the surface of the supplied metal powder P. As shown in FIG. Specifically, the control unit 4 outputs a control signal to the elevator 32 to adjust the vertical position of the stage 31 and outputs a control signal to an actuator or mechanism (not shown) to operate the recoater 34 . As a result, the recoater 34 moves horizontally, the metal powder P is supplied onto the stage 31, and the surface of the metal powder P is leveled. In FIG. 3A, for convenience of explanation, the thickness of each powder layer La below the first layer La1 is the same as the thickness T1 of the outer shell structure 12 and the thickness T2 of the intermediate layer 16. I assume there is. In other words, in FIG. 3A, the outer shell structure 12 or the intermediate layer 16 positioned below and above the inner structure 14 in the stacking direction is each formed of one powder layer La. I am assuming. However, the present disclosure is not limited to such a form. That is, either or all of the outer shell structure 12 and the intermediate layer 16 positioned below and above the inner structure 14 in the stacking direction may be formed of two or more powder layers La.

Next, the three-dimensional modeling apparatus 1 performs modeling processing on the first layer La1. The shaping process is a process of actually shaping the intermediate member 10A. Specifically, the control unit 4 generates two-dimensional slice data based on the three-dimensional CAD data of the intermediate member 10A. Based on this slice data, the control unit 4 determines the area of the metal powder P to be irradiated with the electron beam E, and causes the beam emission unit 2 to irradiate the electron beam E according to the area. Since the thickness of one layer La corresponds to the thickness T1 of the outer shell structure 12, in the shaping process here, the bottom of the outer shell structure 12 is shaped as part of the intermediate member 10A. Become.

Here, in the present embodiment, the first layer La<b>1 may be preheated before the beam irradiation for shaping the bottom portion of the outer shell structure 12 . In this case, the control unit 4 preliminarily sinteres the metal powder P in the entire first layer La1 by performing beam irradiation as a preliminary heating process, and then performs a shaping process for finally forming the outer shell structure 12. Beam irradiation is performed as

After the bottom portion of the outer shell structure 12 is formed with respect to the first layer La1, in the second layer La2, by repeating the series of processes from the powder supply process to the molding process as described above, one part of the intermediate member 10A is further processed. part is molded. Since the thickness of one powder layer La corresponds to the thickness T2 of the intermediate layer 16, a part of the side wall of the outer shell structure 12 is shaped as part of the intermediate member 10A in the molding process here. , and the bottom of the intermediate layer 16 is formed.

Here, also in the second layer La2, preheating may be performed before the beam irradiation for shaping the part of the side wall of the outer shell structure 12 and the bottom of the intermediate layer 16. FIG. In this case, the control unit 4 first performs preliminary sintering of the metal powder P on the entire second layer La2 by performing beam irradiation as a preliminary heat treatment. Therefore, at the stage where the preheating process is finished, both the part of the side wall of the outer shell structure 12 and the bottom of the intermediate layer 16 are presintered. After that, the control unit 4 causes beam irradiation as a shaping process for finally forming a part of the side wall of the outer shell structure 12 . Therefore, when the shaping process for the second layer La2 is completed, part of the side wall of the outer shell structure 12 is solidified metal powder P, while the bottom of the intermediate layer 16 is a presintered body. remains.

In addition, in the three-dimensional modeling process, there may be a case where the preheating process is not performed. In this case, the intermediate layer 16 becomes a region not irradiated with the electron beam E, that is, becomes a layer in which the metal powder P remains as it is.

Subsequently, as shown in FIG. 3B, the three-dimensional modeling apparatus 1 repeats the series of processes from the powder supply process to the modeling process for each of the layers above the third layer La3. , the intermediate member 10A is gradually formed in layers. In addition, in FIG.3(b), even modeling of 10 A of intermediate members in 7th layer La7 is drawn. In particular, in each layer from the third layer La3 to the fifteenth layer La15 (see FIG. 3(c)), in addition to part of each side wall of the outer shell structure 12 and the intermediate layer 16, part of the inner structure 14 The part is gradually formed.

For example, the third layer La3 is a region where part of the sidewall of the outer shell structure 12, part of the sidewall of the intermediate layer 16, and the bottom of the inner structure 14 are formed. Preheating may be performed before beam irradiation for shaping this region. In this case, the control unit 4 first performs preliminary sintering of the metal powder P on the entire third layer La3 by performing beam irradiation as a preliminary heat treatment. Therefore, at the stage where the preliminary heat treatment is finished, the entire region becomes a pre-sintered body. After that, the control unit 4 performs beam irradiation as a shaping process for finally forming a part of the side wall of the outer shell structure 12, and continuously performs a shaping process as a shaping process for finally forming the bottom of the inner structure 14. Beam irradiation is performed. Therefore, at the stage when the shaping process for the third layer La3 is completed, a part of the side wall of the outer shell structure 12 and the bottom of the inner structure 14 are solidified metal powder P, while the intermediate layer 16 A part of the side wall portion of is left as the temporary sintered body.

Then, as shown in FIG. 3C, the three-dimensional modeling apparatus 1 performs modeling of the upper portion of the intermediate layer 16 on the 16th layer La16 and modeling of the upper portion of the outer shell structure 12 on the 17th layer La17. , the intermediate member 10A is finally shaped into a desired shape.

The three-dimensional modeling process described above is divided into two molding processes, a first molding process for molding the outer shell structure 12 and a second molding process for molding the internal structure 14, when classified according to the part of the intermediate member 10A. include. That is, in the present embodiment, in the three-dimensional modeling process by the three-dimensional modeling apparatus 1, it can be considered that the first modeling process and the second modeling process are performed in parallel. Here, when the preheating process is performed, the method for manufacturing a metal member according to the present embodiment includes the preheating process before the first shaping process and the second shaping process in which the final shaping process is performed. can be considered. On the other hand, when the preheating treatment is not performed, the intermediate layer forming step of forming the intermediate layer 16 is included between the first shaping step and the second shaping step in the metal member manufacturing method according to the present embodiment. can be considered included.

Here, as shown in FIG. 1(a), a plurality of cracks 50, 51 and holes 52 are formed inside the intermediate member 10A formed by the three-dimensional forming process as described above, particularly in the internal structure 14. may occur. In particular, crack 50 indicates a crack that does not reach the interior of internal structure 14 , ie, a portion of which does not reach the surface of internal structure 14 . On the other hand, a crack 51 indicates a crack partially reaching the surface of the internal structure 14 . It is undesirable for the cracks 50 and 51 and the voids 52 to remain in the block 10 as the final product. Therefore, in the method for manufacturing a metal member according to the present embodiment, hot isostatic pressing (HIP) processing is performed on the intermediate member 10A that has been formed by the three-dimensional forming process, so that the cracks 50 and 51 and the holes 52 to remove

FIG. 4 is a schematic diagram showing the configuration of a hot isostatic pressing device (HIP device 40) used in the manufacturing method according to this embodiment, and the intermediate member 10A housed in the HIP device 40. FIG. The HIP device 40 is a device that performs HIP processing on an object housed therein. The HIP device 40 includes a pressure vessel 41 , a support base 42 and a heater 43 .

The pressure vessel 41 has an internal space S1 capable of accommodating the intermediate member 10A, which is an object to be processed. The internal space S1 can be sealed. The pressure vessel 41 is connected to a gas supply device (not shown). The pressure vessel 41 can be adjusted to a predetermined pressure by making the internal space S1 into an inert gas atmosphere with an inert gas such as argon gas supplied from the gas supply device. The support base 42 supports the accommodated intermediate member 10A in the internal space S1. The heater 43 heats the internal space S1 to a predetermined temperature.

Next, a treatment process using the HIP device 40 will be described.

After completing the three-dimensional modeling process, the intermediate member 10A taken out from the three-dimensional modeling apparatus 1 is placed on the support table 42 and housed in the pressure vessel 41, as shown in FIG. Next, the HIP device 40 starts HIP processing under a predetermined temperature and pressure. At this time, as processing conditions, for example, the temperature is set within the range of 1000 to 1300° C. and the pressure is set to 100 MPa or higher.

By subjecting the intermediate member 10A to the HIP treatment, first, the cracks 50 and 51 and the holes 52 generated in the internal structure 14 are removed. Here, for comparison, a conventional method for manufacturing a metal member will be described.

FIG. 9 is a perspective view showing a block 100 as a metal member to be manufactured by a conventional manufacturing method. FIG. 9A is a diagram showing an intermediate member 100A to be modeled using the three-dimensional modeling apparatus 1. FIG. FIG. 9(b) is a diagram showing a block 100 as a final product produced by subjecting the intermediate member 100A to HIP processing using the HIP device 40. FIG.

The intermediate member 100A is shaped as a simple cube in the example of FIG. As shown in FIG. 9(a), such an intermediate member 100A also has cracks 150, 151 or voids 50, 51 or voids 52 that may occur in the internal structure 14 of the present embodiment. Pores 152 may occur. The cracks 150 and 151 are caused, for example, by thermal stress resulting from temperature changes during the three-dimensional fabrication process. The voids 152 are caused, for example, by the properties of the metal powder P, or by thermal stress caused by temperature changes during the three-dimensional fabrication process, similar to the cracks 150 and 151 . In particular, the larger the size of the intermediate member 100A, the greater the restraint around the heating portion, so that this thermal stress tends to occur in the vicinity of the heating portion.

When the intermediate member 100A having the cracks 150, 151 and the holes 152 is subjected to the HIP process, the cracks 150 and the holes 152 are removed by the high-temperature, high-pressure inert gas. However, as shown in FIG. 9(b), the crack 151 partially reaching the surface of the intermediate member 100A is not removed due to the action of the HIP process, and remains in the block 100 as the final product. .

In contrast, in the present embodiment, the internal structure 14 is included in the outer shell structure 12 with the intermediate layer 16 interposed therebetween. That is, even if a crack 51 partially reaching the surface of the internal structure 14 occurs in the internal structure 14 , the crack 51 stops at the boundary with the intermediate layer 16 and the outer shell structure 12 is broken. It does not reach the surface, that is, the surface of the intermediate member 10A. Therefore, when the intermediate member 10A having the cracks 50, 51 and the holes 52 is subjected to the HIP process, the cracks 50 and the holes 52 are first removed as in the conventional case. Furthermore, the crack 51, which partially reaches the surface of the internal structure 14, does not reach the surface of the intermediate member 10A as a whole and can be regarded as a crack occurring inside. As shown in FIG. 1(b), it is removed by the action of the HIP treatment. As a result, the cracks 50 and 51 and the holes 52 are less likely to remain in the block 10 as the final product.

In particular, when the intermediate layer 16 is a preliminary sintered body formed by preheating, the metal powders P forming the intermediate layer 16 are partially bonded to each other at their respective surfaces due to a diffusion phenomenon. It is in. Here, "partially bonded" means that the metal powders P are bonded to each other while making point contact or surface contact. In other words, a large number of small voids are dispersedly present in the intermediate layer 16, which is a pre-sintered body. Therefore, even if the crack 51 occurs in the internal structure 14 , it is considered that the crack 51 stops growing when it reaches one of the gaps in the intermediate layer 16 . Further, the bonding force that bonds the metal powders P together changes by appropriately adjusting the beam conditions and the like during the preliminary heat treatment. On the other hand, the particle sizes of the metal powders P are usually different from each other, or can be changed by intentionally mixing metal powders P with different particle sizes and shapes. Therefore, these conditions may be adapted in advance to conditions that facilitate the stoppage of cracks 51 in the internal structure 14 .

Secondly, the metal powder P is sintered in the intermediate layer 16 by subjecting the intermediate member 10A to the HIP treatment. The metal powder P forming the intermediate layer 16 is the same as the metal powder P forming the outer shell structure 12 and the inner structure 14 . Therefore, by sintering the metal powder P of the intermediate layer 16, the intermediate layer 16 is transformed into a high-density bonding portion, and as shown in FIG. Integrate with 14.

By subjecting the intermediate member 10A to the HIP treatment in this manner, the block 10 in which the cracks 50 and 51 and the holes 52 are unlikely to remain is finally manufactured.

Next, various conditions for making it more difficult for cracks 50 and 51 and holes 52 to remain in block 10 will be described.

First, when the intermediate member 10A is subjected to the HIP treatment, the block 10 may shrink because the density changes. Therefore, if the dimension of one side of the block 10 as the final product is the length L3, the final amount of deformation is taken into consideration in advance, and the length L1, which is the dimension of one side of the intermediate member 10A, is longer than the length L3. Slice data or the like may be generated to increase the size.

Further, it is assumed that, in the intermediate member 10A for which the three-dimensional modeling process has been completed, all parts corresponding to the internal structures 14 are made of metal powder P, for example. In this case, compared to the intermediate member 10A in which the internal structural body 14 exists in the present embodiment, the average density of the portion corresponding to the internal structural body 14 is smaller. becomes larger. In other words, the internal structure 14 in this embodiment is a component that increases the average density of the block 10 as a whole in order to reduce the amount of deformation of the block 10 after HIP processing. Therefore, the size of the internal structure 14 may be set so as to occupy most of the size of the intermediate member 10A.

Also, in a certain integrated intermediate member, as described above, the larger the size of the intermediate member, the more likely the thermal stress, which can cause cracks and voids, occurs. Therefore, the thickness T1 of the outer shell structure 12, which is a member independent of the inner structure 14, may be sufficiently thinner than the length L2 of the inner structure 14 in this embodiment. As a result, even if the intermediate member 10A is subjected to the HIP treatment, the outer shell structure 12 is less prone to cracks and voids. For example, the thickness T1 of the outer shell structure 12 depends on the size and shape of the block 10, but may be about 1 mm. Alternatively, regarding the number of powder layers La during layered manufacturing by the three-dimensional modeling apparatus 1, the number of powder layers La forming the outer shell structure 12 positioned below or above the internal structure 14 in the stacking direction is It may be less than the number of powder layers La forming the structure 14 .

In addition, the intermediate layer 16 prevents the outer shell structure 12 from being affected by the thermal stress generated in the second shaping process for shaping the inner structure 14, and also prevents cracks 51 generated in the inner structure 14 from occurring. Avoid reaching the surface of the intermediate member 10A. That is, the thickness T2 of the intermediate layer 16 may be sufficiently thin compared to the length L2 of the internal structure 14 as long as these avoidance effects are achieved. For example, although the thickness T2 of the intermediate layer 16 depends on the size and shape of the block 10, it may be about 1 mm. Alternatively, regarding the number of powder layers La during layered manufacturing by the three-dimensional modeling apparatus 1, the number of powder layers La forming the intermediate layer 16 positioned below or above the internal structure 14 in the stacking direction is equal to the number of the internal structure 14 may be less than the number of powder layers La.

Next, the effects of this embodiment will be described.

First, the manufacturing method of the metal member formed from the metal powder P according to the present embodiment includes a first shaping step of processing the metal powder P by three-dimensional metal additive manufacturing to shape the outer shell structure 12 . In addition, in the method of manufacturing the metal member, the intermediate layer 16 is interposed between the outer shell structure 12 and the metal powder P is processed by three-dimensional metal additive manufacturing to shape the inner structure 14 in the second shaping step. including. Furthermore, the method for manufacturing the metal member includes a treatment step of subjecting the outer shell structure 12, the intermediate layer 16 and the inner structure 14 to hot isostatic pressure treatment after the first shaping step and the second shaping step. . Here, the metal member is block 10, for example.

According to the manufacturing method according to the present embodiment, even if a crack that partially reaches the surface of the internal structure 14 occurs in the internal structure 14 at the stage of the second molding process, the metal member is the metal member before the treatment process. It does not reach the surface of the intermediate member 10A. In other words, before the treatment process, cracks that have partially reached the surface of the metal member, which are generally considered difficult to remove, can be eliminated from the intermediate member 10A in advance. In addition, since cracks and voids generated in the intermediate member 10A can be removed by the treatment process, as a result, it is possible to provide a method of manufacturing a metal member that is advantageous in making it difficult for cracks and voids to remain. can be done.

In addition, in the intermediate member 10A, since the internal structure 14 exists inside the outer shell structure 12, compared to the case where the inside of the outer shell structure 12 is entirely made of the metal powder P, the entire intermediate member 10A can increase the average density of Therefore, the amount of deformation after the intermediate member 10A is subjected to the treatment process can be further reduced, so that the dimensional accuracy of the metal member as the final product can be improved.

Further, in the manufacturing method according to the present embodiment, each of the same powder layers La serving as the outer shell structure 12, the intermediate layer 16, and the inner structure 14 is preheated before the first shaping process and the second shaping process. A step may be included. The preheating step is a step of heating the metal powder P at a temperature below the melting point of the metal powder P by three-dimensional metal additive manufacturing.

In this case, the metal powder P forming the intermediate layer 16 is the same as the metal powder P forming the outer shell structure 12 and the inner structure 14 . Therefore, according to such a manufacturing method, the intermediate layer 16 is transformed into a high-density bonding portion by the treatment step of hot isostatic pressing treatment, ie, HIP treatment, and the outer shell structure 12 and the inner structure are formed. Integrate with 14. That is, in the metal member as the final product, the internal structure is not clearly separated for each part like the block 10 shown in FIG. 1(b). Therefore, the metal member produced by the production method according to the present embodiment can be handled in the same manner as, for example, general machined products, forged products, or cast products formed from a single raw material or material.

Moreover, according to such a manufacturing method, not only the outer shell structure 12 and the inner structure 14 but also the intermediate layer 16 can obtain the effect of the preliminary heat treatment as described above. In particular, when the intermediate layer 16 is a pre-sintered body formed by preheating, the gaps between the metal powders P are smaller than when the intermediate layer 16 is composed of the original metal powder P as it is. becomes smaller and the filling factor improves. When the filling rate of the intermediate layer 16 is high in this way, the amount of deformation from the intermediate member 10A before the HIP treatment to the block 10 as the final product after the HIP treatment is small. Therefore, there is also the advantage that the dimensional accuracy of the block 10 can be easily improved.

Further, in the manufacturing method according to the present embodiment, the first shaping step and the second shaping step are continuous for each same powder layer La, and between the first shaping step and the second shaping step, the intermediate layer 16 may include an intermediate layer forming step of forming

When a part of the outer shell structure 12 and a part of the inner structure 14 are successively modeled for each of the same powder layers La by three-dimensional metal additive manufacturing, the three-dimensional shaping apparatus 1 is, for example, an intermediate It is possible not to irradiate the electron beam E to the position where the layer 16 is provided. In this case, the intermediate layer 16 may be composed of the metal powder P. Alternatively, intermediate layer 16 may be void.

According to such a manufacturing method, it is possible to make the control of the three-dimensional modeling apparatus 1 during lamination modeling simpler.

In the above example, the intermediate layer 16 made of metal powder P and having a thickness T2 of about 1 mm is formed as the intermediate layer forming step. However, the present disclosure is not limited to this. That is, it may be a minute gap. According to such a manufacturing method, since the outer shell structure 12 and the inner structure 14 are directly integrated by the HIP treatment, the intermediate layer 16 is finally made of the metal powder P. The same effect as when configured is achieved.

In addition, in the manufacturing method according to the present embodiment, the number of powder layers La forming the outer shell structure 12 positioned below or above the internal structure 14 in the stacking direction is equal to the number of powder layers La forming the internal structure 14. It may be less than the number of La.

According to such a manufacturing method, the thickness T1 of the outer shell structure 12 is thinner than the length L2 of the inner structure 14. Therefore, even if the intermediate member 10A is subjected to the HIP treatment, the thickness of the outer shell is reduced. Cracks and voids are less likely to occur in the structure 12 .

In addition, in the manufacturing method according to the present embodiment, the number of powder layers La forming the intermediate layer 16 located below or above the internal structure 14 in the stacking direction is the number of powder layers La forming the internal structure 14. It can be less than the number.

According to such a manufacturing method, the thickness T2 of the intermediate layer 16 is thinner than the length L2 of the internal structure 14, so the length L2 of the internal structure 14 in the intermediate member 10A is sufficiently large. be able to.

In addition, in the metal member manufacturing method according to the present embodiment, the modeling conditions for the three-dimensional metal additive manufacturing in the second modeling process may be different from the modeling conditions for the three-dimensional metal additive manufacturing in the first modeling process. .

For example, the internal structure 14 formed in the second forming step is a portion located inside the metal member, and even if the internal structure 14 has cracks 50, 51 and holes 52 at the stage of the intermediate member 10A, , is removed by subsequent HIP processing. Therefore, the conditions for shaping the internal structure 14 do not necessarily have to be the same as the conditions for shaping the outer shell structure 12 , and may be less strict than the conditions for shaping the outer shell structure 12 . Therefore, by making the forming conditions in the second forming process and the forming conditions in the first forming process different in this way, and making one forming condition looser than the other forming condition, for example, manufacturing Time can be shortened.

Here, modeling conditions for three-dimensional metal additive manufacturing include the following. First, the heat source of the three-dimensional modeling apparatus 1 includes output, spot diameter, scanning speed, and scanning interval. Here, the output of the heat source means current/voltage when the three-dimensional modeling apparatus 1 is of the electron beam system, and laser output when the three-dimensional modeling apparatus 1 is of the laser system. In addition, the material supply amount, preheating temperature, or atmosphere in the three-dimensional modeling apparatus 1 may be changed. Here, the material supply amount refers to the layer thickness when the three-dimensional modeling apparatus 1 is of the powder bed type, and refers to the welding amount when the three-dimensional modeling apparatus 1 is of the powder feed type, which will be described later.

FIG. 5 is a schematic cross-sectional view showing another shape of the intermediate member 10A corresponding to FIG. 3(c). In addition, in FIG. 5, the same code|symbol is attached|subjected to the same structure as 10 A of intermediate members shown in FIG.

In the first modeling step in the first layer La1 of the three-dimensional modeling step, the intermediate member 10A is formed with the communicating structure 12a that connects a part of the bottom plate 36 and a part of the outer shell structure 12. may be As a result, the intermediate member 10A can be stably formed with respect to the bottom plate 36 in the subsequent three-dimensional forming process.

Moreover, particularly in this embodiment, the inner structure 14 is formed inside the outer shell structure 12 with the intermediate layer 16 interposed therebetween. Therefore, in the second modeling process in the third layer La3 of the three-dimensional modeling process, the intermediate member 10A is provided with a communicating structure 14a that allows a part of the outer shell structure 12 and a part of the internal structure 14 to communicate with each other. It may be molded. Thereby, the internal structure 14 can be stably formed with respect to the outer shell structure 12 in the subsequent three-dimensional forming process.

(Second embodiment)
Next, a method for manufacturing a metal member according to the second embodiment of the present disclosure will be described. In the first embodiment, the block 10 as the metal member has a simple shape, and the entire block 10 is subjected to the first shaping process and the second shaping process. On the other hand, in the present embodiment, the metal member is the turbine blade 60 having a more complicated shape, and a part of the turbine blade 60 is subjected to the first shaping process and the second shaping process. Illustrate.

FIG. 6 is a perspective view showing a turbine blade 60 to be manufactured by the manufacturing method according to this embodiment. The turbine blades 60 are one component of turbine components used in aircraft jet engines, industrial gas turbines, and the like, and are installed in plurality on the outer circumference of a turbine rotor (not shown). The turbine blade 60 includes, for example, a blade portion 62 as a first portion and a dovetail portion 64 as a second portion. Note that the dovetail portion is also called a blade root portion. The wing portion 62 is a portion that guides gas under high pressure or high temperature. The dovetail portion 64 is a portion that is fitted into a groove portion previously formed in the turbine rotor in order to fix the turbine blade 60 to the turbine rotor. The material of the turbine blades 60 may be, for example, CM247LC as in the first embodiment. In each figure according to the present embodiment, the Z-axis is taken in the extending direction of the turbine blade 60, and the X-axis and the Y-axis perpendicular to the X-axis are taken in the horizontal plane perpendicular to the Z-axis. .

Here, looking at each portion of the turbine blade 60, the blade portion 62 has a generally thin shape. On the other hand, the dovetail portion 64 has a generally thick shape. Therefore, in the present embodiment, the turbine blade 60 is manufactured by using the manufacturing method described below, with different molding steps for different parts having different schematic shapes.

First, as a three-dimensional modeling process, the intermediate member 60A of the turbine blade 60 is modeled using the three-dimensional modeling apparatus 1 employed in the first embodiment. In the three-dimensional modeling process in this embodiment, the modeling process is changed for each of the wing portion 62 as the first portion and the dovetail portion 64 as the second portion.

FIG. 7 is a schematic cross-sectional view showing the flow of the three-dimensional modeling process for modeling the intermediate member 60A by the three-dimensional modeling apparatus 1 in chronological order. Note that FIG. 7 corresponds to FIG. 3 used in the description of the first embodiment. In addition, in FIG. 7 and FIG. 8 below, the shape of the intermediate member 60A is simplified and drawn. In the three-dimensional forming process, the intermediate member 60A is formed from the portion corresponding to the dovetail portion 64 of the turbine blade 60 toward the portion corresponding to the blade portion 62 of the turbine blade 60 . That is, as shown in FIG. 6, if the extending direction of the turbine blade 60 is the Z-axis, the stacking direction in the three-dimensional fabrication process is the Z-direction.

First, in the three-dimensional modeling process, a portion corresponding to the dovetail portion 64 of the intermediate member 60A is modeled. The dovetail portion 64 has a thicker shape than the wing portion 62 . Here, as described in the first embodiment, the larger the size of the intermediate member, the more likely thermal stress that can cause cracks and voids in the three-dimensional fabrication process occurs. In other words, if the metal member is the turbine blade 60 , cracks may eventually remain, particularly in the dovetail portion 64 . Therefore, in the present embodiment, the portion corresponding to the dovetail portion 64 is shaped by a modeling process that combines the first shaping process and the second shaping process, as in the first embodiment. Specifically, a portion corresponding to the dovetail portion 64 includes an outer shell structure 65 , an intermediate layer 66 and an inner structure 67 . These correspond to the outer shell structure 12, the intermediate layer 16, and the inner structure 14 in the first embodiment, respectively. A portion corresponding to the dovetail portion 64 is formed based on the same forming process as in the first embodiment, as shown in FIGS. 7(a) and 7(b).

Subsequently, a portion of the intermediate member 60A corresponding to the wing portion 62 is formed. The wings 62 have a thin shape compared to the dovetails 64 . That is, in the wing portion 62, thermal stress that can cause cracks and voids is less likely to occur in the three-dimensional fabrication process. Therefore, in the present embodiment, unlike the first embodiment, the portion corresponding to the wing portion 62 is formed in the third forming step, which is a single forming step.

As shown in FIG. 7(c), in the third forming step, the portion corresponding to the dovetail portion 64 formed up to the eighth layer La8 is followed by the turbine in the ninth layer La9 and the tenth layer La10. A portion corresponding to the flange portion 68 of the blade 60 is shaped. Thereafter, from the eleventh layer La11 to the uppermost twenty-sixth layer La26, a portion corresponding to the main body 69 of the wing portion 62 is formed, and finally the intermediate member 60A is formed into a desired shape.

Next, in the manufacturing method of the turbine blade 60 according to the present embodiment, the intermediate member 60A formed by the three-dimensional forming process is subjected to HIP processing.

FIG. 8 is a schematic diagram showing an intermediate member 60A accommodated in the HIP device 40 employed in the first embodiment. The HIP treatment is performed under the same conditions as in the first embodiment, and finally the turbine blade 60 is produced.

Thus, in the method for manufacturing a metal member according to this embodiment, the metal member includes the first portion and the second portion. The first part is shaped by a third shaping step in which the metal powder P is processed and shaped by three-dimensional metal additive manufacturing. A 2nd site|part is modeled by a 1st modeling process and a 2nd modeling process. Further, the treatment process is applied to the first part and the second part after the first shaping process, the second shaping process and the third shaping process. Here, the metal member is the turbine blade 60, for example. In this case, the first portion is the wing portion 62, for example. Also, the second portion is, for example, the dovetail portion 64 .

According to the manufacturing method according to the present embodiment, of the parts to be modeled in the three-dimensional modeling process, only the parts that are likely to have cracks or voids are manufactured in the same steps as in the first embodiment. That is, since it is not necessary to perform the shaping process including the first shaping process and the second shaping process for the entire metal member, it is possible to shorten the manufacturing time.

Here, as shown in FIG. 6, the shape of the turbine blade 60 is more complicated than the block 10 illustrated in the first embodiment. In this case, the shapes of the outer shell structure 65, the intermediate layer 66, and the inner structure 67 in the dovetail portion 64 to which the first shaping process and the second shaping process are applied are actually complicated, and the length and length are uniform. It is difficult to define dimensions such as thickness. Therefore, the volume of the outer shell structure 65 and the inner structure 67 may be defined as a ratio to the overall volume of the dovetail portion 64 . For example, the internal structure 67 may be formed in the dovetail portion 64 so that the volume of the internal structure 67 is about 80% of the volume of the dovetail portion 64 .

In addition, in the metal member manufacturing method according to the present embodiment, the modeling conditions for the three-dimensional metal additive manufacturing in the third modeling process are the same as the modeling conditions for the three-dimensional metal additive manufacturing in the first modeling process or the second modeling process. It may be different from at least one. Accordingly, as in the case of the first embodiment, it is possible to shorten the manufacturing time by appropriately changing the modeling conditions of the three-dimensional metal additive manufacturing for each modeling process. The modeling conditions for the three-dimensional metal additive manufacturing referred to here are the same as the modeling conditions exemplified above.

Note that the statement that the metal member includes the first portion and the second portion does not mean that the metal member includes two portions. If the metal member has at least two or more parts with different shapes, by performing the first shaping step and the second shaping process on any of the three or more parts, the present embodiment can be applied.

Further, the turbine blade 60 is exemplified as a metal member to be produced by the production method. However, the present disclosure is applicable to fabrication of any metal member that has a different shape for each part. For example, it is applicable to manufacture of shafts and impellers of supercharger turbines.

(Other embodiments)
In each of the above-described embodiments, the three-dimensional modeling apparatus 1 is a three-dimensional metal additive manufacturing apparatus that performs modeling using an electron beam as an energy beam among the powder bed methods. However, the three-dimensional modeling apparatus that can be used in the present disclosure is not limited to this, and may be a three-dimensional metal additive manufacturing apparatus that performs modeling using a laser as an energy beam among powder bed methods. Three-dimensional modeling apparatuses that use lasers include, for example, those that employ selective laser melting (SLM) and selective laser sintering (SLS). Note that in a three-dimensional modeling apparatus using a laser, the inside of a chamber in which modeling is performed does not have to be in a vacuum state, and an atmosphere of an inert gas such as an argon gas atmosphere may be used. Moreover, in a three-dimensional modeling apparatus using a laser, preheating may be omitted or may be performed. In each of the above embodiments, preheating is performed by irradiating the electron beam E. FIG. That is, although the heat source for preheating is an energy beam, it is not limited to this. For example, a heater such as a radiant heater may be provided separately from the beam emitting unit 2, and the powder may be preheated by raising the temperature of the powder using the heater. Further, in each of the above-described embodiments, the method of solidifying the metal powder P by melting and solidifying the metal powder P has been described, but the method is not limited to such a method, and the metal powder P is sintered to P may be solidified. Further, the three-dimensional modeling apparatus 1 is not limited to the powder bed method, which is a selective melting method, and may employ, for example, a so-called powder feed method, which is a material addition method.

Moreover, in each of the above-described embodiments, the case where the first modeling process and the second modeling process related to three-dimensional metal additive manufacturing are continuously performed for each of the same powder layers La has been exemplified. However, the present disclosure is not limited to this. For example, firstly, the entire outer shell structure 12 except for the 17th layer La17, which is the uppermost layer, is shaped by the first shaping step. Second, the inner structure 14 is shaped separately from the outer shell structure 12 . At this time, the first modeling process and the second modeling process may be modeled using different three-dimensional modeling apparatuses 1 . Thirdly, the 17th layer La of the outer shell structure 12 is shaped after the inner structure 14 that has been shaped in advance is housed in the outer shell structure 12 with the intermediate layer 16 interposed therebetween. Then, it is also possible to finally form the intermediate member 10A. Thus, in the present disclosure, the first modeling process and the second modeling process may not necessarily be performed consecutively for each same powder layer La.

Although preferred embodiments of the present disclosure have been described above, the present disclosure is not limited to these embodiments, and various modifications and changes are possible within the scope of the gist thereof.

REFERENCE SIGNS LIST 10 block 12 outer shell structure 14 inner structure 16 intermediate layer 60 turbine blade 62 blade portion 64 dovetail portion 65 outer shell structure 66 intermediate layer 67 inner structure La powder layer P metal powder

Claims (10)

A method for producing a metal member formed from metal powder,
a first shaping step of processing the metal powder by three-dimensional metal additive manufacturing to shape an outer shell structure;
An intermediate layer composed of the metal powder is interposed between the outer shell structure and the metal powder is processed by three-dimensional metal additive manufacturing to form an internal structure independent of the outer shell structure. a second molding step;
a processing step of subjecting the outer shell structure, the intermediate layer, and the internal structure to hot isostatic pressing after the first shaping step and the second shaping step;
A method of making a metal member, comprising: Before the first shaping step and the second shaping step, each of the same powder layers that will be the outer shell structure, the intermediate layer, and the inner structure is subjected to three-dimensional metal additive manufacturing so that the metal powder has a melting point lower than the melting point. 2. The method for producing a metal member according to claim 1, comprising a preheating step of heating the metal powder at a temperature of . The second shaping step is performed before and after the first shaping step for each same powder layer,
2. The method of manufacturing a metal member according to claim 1, comprising an intermediate layer forming step of forming the intermediate layer between the first shaping step and the second shaping step. 4. The method according to claim 2 or 3 , wherein the number of powder layers forming the outer shell structure positioned below or above the internal structure in the stacking direction is smaller than the number of powder layers forming the internal structure. A method of making the described metal member. Any one of claims 2 to 4 , wherein the number of powder layers forming the intermediate layer positioned below or above the internal structure in the stacking direction is smaller than the number of powder layers forming the internal structure. 2. A method for producing a metal member according to item 1. The metal member according to any one of claims 1 to 5 , wherein the modeling conditions for the three-dimensional metal additive manufacturing in the second modeling process are different from the modeling conditions for the three-dimensional metal additive manufacturing in the first modeling process. method of making. 7. The method according to any one of claims 1 to 6 , wherein in the second forming step, a communicating structure that connects a portion of the outer shell structure and a portion of the internal structure is formed in the intermediate layer. A method for producing the metal member according to . The metal member includes a first portion and a second portion,
The first part is shaped by a third shaping step in which the metal powder is processed and shaped by three-dimensional metal additive manufacturing,
The second part is shaped by the first shaping step and the second shaping step,
The treatment step is performed on the first portion and the second portion after the first shaping step, the second shaping step, and the third shaping step.
A method for producing a metal member according to any one of claims 1 to 7 . 9. The method according to claim 8 , wherein the manufacturing conditions for three-dimensional metal additive manufacturing in the third manufacturing process are different from at least one of the manufacturing conditions for three-dimensional metal additive manufacturing in the first manufacturing process or the second manufacturing process. A method for producing a metal member. the metal member is a turbine blade,
the first portion is a blade portion of the turbine blade,
The second portion is a root portion of the turbine blade,
A method for producing a metal member according to claim 8 or 9 .

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