METHOD FOR MANUFACTURING MACHINE COMPONENTS BY ADDITIVE MANUFACTURING

Abstract

A method for manufacturing a machine component made of metal-based material is described. The method comprises the steps of: providing a powder blend comprising at least one metal-containing powder material and at least one strengthening dispersor in powder form, wherein the strengthening dispersor in powder form has an average grain size less than an average grain size of the metal-containing powder material; and forming the machine component by an additive manufacturing process using the powder blend.

Claims

1. A method for manufacturing a machine component made of a metal-based material, the method comprising: providing a powder blend comprising at least one metal-containing powder material and at least one strengthening dispersor in powder form, wherein the strengthening dispersor in powder form has an average grain size equal to or less than about 5 micrometers and less than an average grain size of the metal-containing powder material; and forming the component by an additive manufacturing process using the powder blend.

2. The method of claim 1, wherein the additive manufacturing process is selected from the group consisting of: electron beam melting (EBM), selective laser melting (SLM), selective laser sintering (SLS), laser metal forming (LMF), direct metal laser sintering (DMLS), and direct metal laser melting (DMLM).

3. The method of claim 1, wherein the at least one strengthening dispersor in powder form has an average grain size equal to or less than about 0.1 micrometers.

4. The method of claim 1, wherein the strengthening dispersor in powder form has an average grain size equal to or greater than about 5nm.

5. The method of claim 1, wherein the at least one strengthening dispersor in powder form has a nanometric average grain size.

6. The method of claim 1, wherein the at least one metal-containing powder material has an average grain size between about 10 micrometers and about 100 micrometers.

7. The method of claim 1, wherein the powder blend comprises between about 0.01% and about 48% by weight the at least one strengthening dispersor in powder form.

8. The method of claim 1, wherein the powder blend comprises between about 0.2% and about 20% by weight of the at least one strengthening dispersor in powder form.

9. The method of claim 1, wherein the strengthening dispersor in powder form is an atomized powder.

10. The method of claim 1, wherein the metal-containing powder material is an atomized powder.

11. The method of claim 1, wherein the at least one strengthening dispersor in powder form is a ceramic material.

12. The method of claim 1, wherein the at least one strengthening dispersor in powder form is an oxide.

13. The method of claim 1, wherein the at least one strengthening dispersor in powder form is selected from the group consisting of: Y.sub.2O.sub.3, Al.sub.2O.sub.3, Th.sub.2O.sub.4, Zr.sub.2O.sub.3, La.sub.2O.sub.3, Yb.sub.2O.sub.3, Dy.sub.2O.sub.3, Si.sub.3N.sub.4, AlN, SiC, TaC, WC, and combinations thereof.

14. The method of claim 1, wherein the at least one metal-containing powder material is a high-temperature superalloy.

15. The method of claim 14, wherein the high-temperature superalloy is selected from the group consisting of: Ni-based superalloys, Co-based superalloys, Fe-based superalloys, Mo-based superalloys, W-based superalloys, Ta-based superalloys; Nb-based superalloys, and combinations thereof.

16. The method of claim 1, wherein the metal-containing powder material is one of a silicide, an alluminide, or a refractory-metal containing compound.

17. The method of claim 16, wherein the metal-containing powder material is selected from the group consisting of: Nb.sub.3Si, MoSi.sub.2, TaSi, MoSiNb, NiAl, and FeAl.

18. The method of claim 1, wherein of providing a powder blend comprises: producing the metal-containing powder material with a first average grain size; producing the strengthening dispersor in powder form with a second average grain size, wherein the second average grain size is lower than the first average grain size; and mixing together the metal-containing powder material and the strengthening dispersor in powder form to obtain the powder blend.

19. The method of claim 1, further comprising at least one heat-treatment step performed on the formed component.

20. The method of claim 19, wherein the at least one heat-treatment step comprises a hot isostatic pressing step.

21. The method of claim 1, wherein the machine component is a turbomachine component.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0016] A more complete appreciation of the disclosed embodiments of the invention and many of the attendant advantages thereof will be readily obtained as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings, wherein:

[0017] FIG. 1 illustrates a schematic of an additive manufacturing device using electron beam melting technology, for manufacturing a machine component;

[0018] FIG. 2 illustrates a schematic of direct metal laser melting device for additive manufacturing;

[0019] FIG. 3 illustrates a flow diagram of methods according to the present disclosure.

DETAILED DESCRIPTION

[0020] Reference throughout the specification to one embodiment or an embodiment or some embodiments means that the particular feature, structure or characteristic described in connection with an embodiment is included in at least one embodiment of the subject matter disclosed. Thus, the appearance of the phrase in one embodiment or in an embodiment or in some embodiments in various places throughout the specification is not necessarily referring to the same embodiment(s). Further, the particular features, structures or characteristics may be combined in any suitable manner in one or more embodiments.

[0021] The modifier about used in connection with a quantity is inclusive of the stated value and has the meaning dictated by the context (e.g., includes the tolerance ranges associated with measurement of the particular quantity).

[0022] In the following description reference will be made to manufacturing of turbomachine components. It shall however be understood that the methods disclosed herein can be applied also to the manufacturing of other machine components, in particular machine components, which are subject to high temperature operating conditions and to fatigue cycles, e.g. components of reciprocating internal combustion engines.

[0023] FIG. 1 is a schematic of an exemplary additive manufacturing machine or device, which can be used for manufacturing a turbomachine component, such as a turbine blade B, a turbine nozzle, a turbine shroud or other turbine components, according to methods of the present disclosure.

[0024] As known to those skilled in the art, additive manufacturing is a process wherein an article having a complex shape is manufactured layer-by-layer starting from a powder material, which is locally melted using an energy source. In the embodiment of FIG. 1, the energy source is an electron beam gun. In other embodiments, the energy source can be a laser.

[0025] The additive manufacturing machine of FIG. 1 is designated 100 as a whole. The structure and operation of additive manufacturing machines are known per se and will not be described in great detail herein. In short, the additive manufacturing machine 100 of FIG. 1 includes an energy source, which in the exemplary embodiment disclosed herein includes an electron-beam gun 101 comprising an electron emitter 103, which generates an electron beam EB. The electron beam EB is directed towards a target surface TS, arranged under the electron-beam gun 101. Along the electron-beam path a focusing coil 105 and a deflection coil 107 can be arranged. The focusing coil 105 focuses the electron beam on the target surface TS and the deflection coil 107 controls the movement of the electron beam EB along a pattern, according to which a powder material has to be melted and solidified. A computer device 109 controls the deflection coil 107 and the movement of the electron beam EB. The movement of the electron beam EB is controlled by the computer device 109 based on data from a file representing the three-dimensional product to be manufactured.

[0026] Under the energy source 101 a confinement structure 111 can be arranged. The confinement structure 111 can be combined with a temperature control means, for example comprising a heater shown schematically at 113, e.g. an electrical heater. A movable table 115 can be arranged in the confinement structure 111. The movable table 115 can be controlled to move vertically according to double arrow f115. The vertical movement of the movable table 115 can be controlled by the computer device 109. A powder material container 117 can be arranged above the target surface TS and is controlled to move horizontally according to double arrow f117, for example under the control of the computer device 109.

[0027] The additive manufacturing process performed by the additive manufacturing machine 100 can be summarized as follows. A first layer of powder material from the powder material container 117 is distributed on the movable table 115 by moving the powder material container 117 according to arrow f117 one or more times along the movable table 115, which is placed at the height of the target surface TS. Once the first layer of powder material has been distributed, the electron-beam gun 101 is activated and the electron beam EB is controlled by the deflection coil 107 such as to locally melt the powder material in a restricted portion of the layer, corresponding to a cross-section of the product to be manufactured. After melting, the melted powder material is allowed to cool and solidify. Powder material outside the boundaries of the cross-section of the product to be manufactured remains in powder form.

[0028] Once the first layer has been processed as described above, the movable table 115 is lowered and a subsequent layer of powder material is distributed on top of the first, solidified layer. The second layer of powder material is in turn selectively melted and subsequently allowed to cool and solidify. Melting and solidifying are performed such that each layer portion will adhere to the previously formed layer portion. The process is repeated stepwise, until the entire product is formed, by subsequently adding one powder material layer after the other and selectively melting and solidifying layer portions corresponding to subsequent cross sections of the product.

[0029] Once the product has been completed, the powder material which has not been melted and solidified can be removed and recycled.

[0030] The above described process can be carried out under controlled temperature conditions by means of the heater 113. The temperature within the confinement structure 111 is controlled such that the entire process is performed at high temperature and virtually no residual stresses remain in the product at the completion of the manufacturing cycle. After the construction process has been completed, the product can be allowed to cool down from a processing temperature to an environment temperature following a cooling curve, which prevents residual stresses in the final product.

[0031] In an embodiment, the interior of the confinement structure 111 is maintained under hard vacuum conditions, such that oxygen absorption by the powder material and the melted material is prevented.

[0032] FIG. 2 illustrates a schematic of a DMLM (Direct Metal Laser Melting) device 201. The device includes a laser source 203, e.g. a carbon dioxide laser. The laser beam LB generated by the laser source 203 is focused by optics 204 and can be deflected by mirrors 205. The mirrors 205 are controlled by a programmable control unit, not shown, to follow a pattern which corresponds to the cross-section of each layer of the article to be manufactured, e.g. a turbine blade. A first vertically movable table 207 supports the workpiece or article B during manufacturing. A second vertically movable table 209 forms the bottom of a powder material container. A horizontally movable wiper blade 211 distributes powder material from the powder material container on top of the workpiece B being manufactured. The table 207 and the table 209 can be housed in a vacuumized container, or in a container filled with inert gas, e.g. argon.

[0033] The additive manufacturing process performed by device 201 is known per se and can be summarized as follows. The table 207 is moved in the upper position and a first layer of powder material is uniformly distributed on the table 207 by the wiper blade 211. The laser source 203 is activated and the laser beam LB is controlled so as to locally and selectively melt the powder material of the layer on table 207. The table 207 is then lowered (arrow 207) by a stroke corresponding to the thickness of the subsequent layer. The first layer of melted material is allowed to solidify. The table 209 is lifted (arrow f209) to make additional powder material available for the wiper blade 211. This latter performs a further reciprocating movement (arrow f211) to distribute the next powder material layer on top of the previous one on table 207 and the laser beam LB is activated and moved by mirrors 205 to selectively melt the powder material of the second layer.

[0034] The process is repeated until the final article is obtained.

[0035] In the schematic of FIG. 2 deflecting mirrors 205 are used. In other exemplary embodiments a fiber laser can be used, wherein the laser energy is conveyed by means of a fiber, the terminal end whereof is moved according to numerically controlled axes, e.g. X and Y axes, parallel to table 207.

[0036] According to embodiments disclosed herein, the powder material used in the additive manufacturing process is a powder blend comprised of at least two powder materials, namely a metal-containing powder and a strengthening dispersor in powder form. As mentioned above, the metal-containing powder can be an intermetallic or a metal powder, e.g. a superalloy, suitable for high temperature conditions of operation of the machine component formed thereby. The dispersor can be a ceramic material, such as, but not limited to, an oxide powder.

[0037] According to some exemplary embodiments, the metal-containing powder is a superalloy powder, such as a high temperature superalloy powder. The superalloy powder can be one of a Ni-based superalloy, Co-based superalloy, Fe-based superalloy, Mo-based superalloy, W-based superalloy; Ta-based superalloy; Nb-based superalloy. In other embodiments, the metal-containing powder material can be selected from the group consisting of Nb.sub.3Si, MoSi.sub.2, TaSi, MoSiNb or other silicides. In yet further embodiments, the metal-containing powder material can be an alluminide, such as NiAl or FeAl.

[0038] The metal-containing powder material can be obtained starting from an ingot or bar of a master superalloy, which is subsequently molten and atomized. According to some exemplary embodiments, the master superalloy ingot can be manufactured by vacuum induction melting.

[0039] According to some embodiments, atomization is achieved by vacuum inert gas atomization, which ensures the production of superalloy powder having a low oxygen content and spherical shape of the grains. The master superalloy ingot is melted and fed through a nozzle into an atomization chamber, wherein a pressurized jet of inert gas is directed against the melted metal flow, which is thus separated into a plurality of small metal particles.

[0040] The grain size of the powder obtained can be controlled by adjusting the gas/metal flow ratio in the atomization chamber.

[0041] According to other embodiments, the atomization of the starting ingot can be obtained by a process selected from the group consisting of Vacuum Induction Gas Atomization (VIGA), Plasma Rotating Electrode Process (PREP), Plasma Atomization (PA), Rotating Disc Atomization (RDA).

[0042] In an embodiment, a required granulometric distribution, i.e. grain dimension of the final atomized metal-containing powder material can be achieved e.g. by means of a cyclone classifier. In some embodiments, the granulometric distribution is selected such that the average grain size of the metal-containing powder material is comprised between about 10 micrometers and about 100 micrometers. In some exemplary embodiments, the average grain size is comprised between about 10 micrometers and about 60 micrometers.

[0043] As mentioned above, the powder blend further comprises at least one dispersor, e.g. a ceramic material, in powder form. In some embodiments, a single ceramic material in powder form can be used. In other embodiments a mixture of two or more different ceramic materials in powder form, having different chemical compositions, can be used. In some embodiments, the ceramic powder material is an oxide powder.

[0044] According to exemplary embodiments of the method disclosed herein, the at least one strengthening dispersor in powder form can a metal oxide. In some embodiments the strengthening oxide is selected from the group consisting of: Y.sub.2O.sub.3, Al.sub.2O.sub.3, Th.sub.2O.sub.4, Zr.sub.2O.sub.3, La.sub.2O.sub.3, Yb.sub.2O.sub.3, Dy.sub.2O.sub.3, and combinations thereof. Other ceramic, non-oxide materials can be selected from the group consisting of: Si.sub.3N.sub.4, AlN, SiC, TaC, WC, and combinations thereof.

[0045] The strengthening dispersor in powder form can have an average grain size lower than the average grain size of the metal-containing powder material. In some embodiments the strengthening dispersor in powder form has an average grain size equal to or less than about 5 micrometers. In some embodiments, the strengthening dispersor in powder form can have an average grain size of about 1 micrometer or less, more particularly about 0.5 micrometers or less. In some embodiments the strengthening dispersor in powder form has a nanometric average grain size, for instance an average grain size equal to or less than about 60 nm, or else equal to or less than about 50 nm. In some embodiments the average grain size is not less than about 5 nm.

[0046] Nanometric dimensional strengthening dispersor can be obtained by known methods. Suitable methods are disclosed e.g. in A. Lorke et al. (eds.): Nanoparticles from the Gas Phase, NanoScience and Technology, Springer-Verlag Berlin Heidelberg 2012, Chapter 2; Christina Raab et al.: Production of Nanopartiles and Nanomaterials, in NanoTrust Dossiers, n. 6, Feb. 2011; Takuya Tsuzuki: Commercial Scale Produton of Inorganic Nanoparticles, in Int. J. Nanotechnol., vol. 6, nos 5/6 2009; Francois Bozon-Verduraz et al: Nanoparticles of Metal and metal Oxides: Some Peculiar Synthesis Methods, Size and Shape Control, Application to Catalysts Preparation, in Brazilian Journal of Physics, vol. 39, n. 1A, April 2009.

[0047] Combining coarser metal-containing material in powder form and finer strengthening dispersor in powder form, enhanced mechanical properties of the final component produced by additive manufacturing can be achieved. The small dispersor powder grains give raise to a fine distribution of the dispersor in the metallic matrix, reducing or preventing the risk of increasing the fragility of the final material.

[0048] The amount of strengthening dispersor in powder form in the final blend can range e.g. between about 0.01% and about 48% by weight. In some embodiments, strengthening dispersor powder is present in an amount ranging between about 0.1% and about 30% by weight, for instance between about 0.1% and about 2% by weight.

[0049] The following Table 1 provides a list of exemplary compositions of suitable powder blends. The superalloy metal component of the blend is a Ni-based superalloy. The composition is given in % by weight.

TABLE-US-00001 TABLE 1 Y.sub.2O.sub.3 Y.sub.2O.sub.3 Ni Co W Cr Al Ti Ta Re Ru Mo Hf C B Zr <5 m <20 nm Bal. 9.10 9.40 8.01 5.54 0.69 3.16 0.49 1.38 0.07 0.01 0.01 1.10 Bal. 9.10 9.40 8.01 5.54 0.69 3.16 0.49 1.38 0.07 0.01 0.01 1.10 Bal. 9.15 9.45 8.06 5.57 0.70 3.18 0.50 1.39 0.07 0.01 0.01 0.55 Bal. 9.15 9.45 8.06 5.57 0.70 3.18 0.50 1.39 0.07 0.01 0.01 0.55 Bal. 5.54 4.95 4.55 5.54 5.54 6.33 4.95 2.37 0.10 1.10 Bal. 5.54 4.95 4.55 5.54 5.54 6.33 4.95 2.37 0.10 1.10 Bal. 5.57 4.97 4.57 5.57 5.57 6.36 4.97 2.39 0.10 0.55 Bal. 5.57 4.97 4.57 5.57 5.57 6.36 4.97 2.39 0.10 0.55

[0050] The following Table 2 lists additional exemplary embodiments of compositions, which can be used with the method disclosed herein. These compositions are comprised of Mo-based, Ni-based, W-based, Ta-based and Nb-based alloys.

TABLE-US-00002 TABLE 2 Ceramic (e.g. Si.sub.3N.sub.4) and/or Oxide Ni Co Cr Mo W Ta Re Ru Nb Ti Al Fe C Hf B Zr Si (e.g. Y.sub.2O.sub.3.) 10 Bal. 29 7 1 0.07 0.01 1 Bal. 8.5 16 1.75 2.6 1.75 0.9 3.4 3.4 0.05 0.1 1 Bal. 9.5 14 1.55 3.8 2.7 0.15 4.9 3 0.3 0.05 0.014 0.04 0.25 1 Bal. 9.5 8.4 0.5 9.5 3 0.75 5.5 0.2 0.05 1.5 0.015 0.013 0.06 1 Bal. 10 8.9 2 7 3.8 0.05 0.1 2.5 4.8 0.2 0.06 1.55 0.015 0.03 0.1 1 Bal. 7.5 9.8 1.5 6 4.8 0.1 1 3.5 4.25 0.2 0.06 0.15 0.004 0.01 0.2 1 Bal. 5 8 0.6 8 6 1 5.6 25 Bal. 5 10 4 12 1.5 5 1 Bal. 1 7.2 0.9 9 8.8 1.4 1 5 0.07 0.25 0.02 1 Bal. 7.5 7 1.5 5 6 1.5 0 0.05 6.2 0 0.05 0.15 0.004 0.01 0.2 1 Bal. 7.5 7 1.5 5 6 3 0.1 0.05 6.2 0.2 0.05 0.15 0.004 0.01 0.2 1 Bal. 9.6 6.4 0.6 6 6.6 2.9 1.03 5.64 0.1 1 Bal. 7.8 4.9 1.9 9 6 2.4 0.5 5.3 0.1 1 Bal. 10 5 1.9 5.9 8.7 3 5.6 0.1 8 Bal. 12.5 4.2 1.4 6 7.2 5.4 5.75 0.05 0.15 0.004 1 Bal. 3 2 0.4 5 8 6 1 0.2 5.7 0.03 1 Bal. 12 3 2 6 6 5 6 0.1 10 Bal. 5.8 3.2 2.8 5.9 5.6 5 2 5.9 0.1 1 Bal. 5.8 3.2 2.8 5.6 5.6 5.8 3.6 5.7 0.1 1 Bal. 16.5 2 2 6 8.25 5.95 3 5.55 0.03 0.15 4 Bal. 5.3 4.4 2.3 4.8 5.3 6.1 4.8 5.7 0.1 1 Bal. 6.5 4.6 1.1 4 7.6 6.4 5 5.9 0.1 3 Bal. 9.5 8.4 0.5 9.5 3 0.75 5.5 0.2 0.05 1.5 0.015 0.013 0.06 1 Bal. 11.75 6.8 1.5 4.9 6.35 2.8 0.1 0.02 6.15 0.2 0.07 1.5 0.015 0.03 0.06 1 Bal. 9.5 8.4 0.5 9.5 3 0.75 5.5 0.2 0.05 1.5 0.015 0.013 0.06 0.5 Bal 0.5 0.1 0.5 Bal 0.5 0.1 48 Bal 1 36 0.5 Bal 1 36 48 2 Bal 25 2 8 16 1 10 Bal 2.5 1 Bal 0.5 0.1 1 10 Bal 1 Bal 1 Bal 5 0.5 1 Bal 24 0.5 1

[0051] The turbomachine component manufactured by additive manufacturing as disclosed so far can be subjected to one or more additional process steps. According to some embodiments, a final hot isostatic pressing (HIP) step can be performed for removing or reducing the porosity inside the melted and solidified material. The hot isostatic pressing step or treatment can be performed e.g. in an atmosphere of inert gas under pressures between about 80 and about 200 MPa.

[0052] According to some embodiments the turbomachine component is subjected to subsequent heat treatments under vacuum aimed at achieving desired material properties, e.g. at homogenizing the microstructure and subsequent aging the material to obtain precipitation hardening strengthening for the precipitation hardening superalloys (i.e. gamma prime former). Localized (in specific component areas) homogenization and heat treatment can be applied to locally increase the grain size to maximize coarse grain size properties in specific areas (typically the airfoil areas of gas turbine buckets).

[0053] FIG. 2 illustrates a summarizing flow chart of exemplary embodiments of the method as disclosed above.

[0054] While the disclosed embodiments of the subject matter described herein have been shown in the drawings and fully described above with particularity and detail in connection with several exemplary embodiments, it will be apparent to those of ordinary skill in the art that many modifications, changes, and omissions are possible without materially departing from the novel teachings, the principles and concepts set forth herein, and advantages of the subject matter recited in the appended claims. Hence, the proper scope of the disclosed innovations should be determined only by the broadest interpretation of the appended claims so as to encompass all such modifications, changes, and omissions. In addition, the order or sequence of any process or method steps may be varied or re-sequenced according to alternative embodiments.