WO2019191450A1

WO2019191450A1 - Titanium aluminide alloys and titanium aluminide alloy products and methods for making the same

Info

Publication number: WO2019191450A1
Application number: PCT/US2019/024611
Authority: WO
Inventors: Alojz Kajinic; Xuan Nguyen-Dinh
Original assignee: Arconic Inc.
Priority date: 2018-03-29
Filing date: 2019-03-28
Publication date: 2019-10-03

Abstract

The present disclosure relates to titanium aluminide products having 42.5 to 45.75 at. % Al, 1.75 to 4.2 at. % Nb, 0.8 to 1.55 at. % Cr, at least one of (a) 0.10 to 1.25 at. % B and (b) 0.15 to 0.45 at. % Si, up to 4.0 at. % Ta, up to 0.75 at. % W, and up to 0.55 at. % Mo, the balance being titanium, optional incidental elements, and impurities. The new titanium aluminide alloys may realize an improved combination of properties, such as an improved combination of two or more of printability, strength, ductility, castability and oxidation resistance, among others. The titanium aluminide alloy compositions described herein may facilitate the production of crack-free titanium aluminide products for use in high temperature applications, such as, for instance, engine and turbine applications, among others.

Description

TITANIUM ALUMINIDE ALLOYS AND TITANIUM ALUMINIDE ALLOY PRODUCTS AND METHODS FOR MAKING THE SAME

FIELD OF THE INVENTION

[001] The present disclosure relates to titanium aluminide alloys and titanium aluminide alloy products, and methods for making the same.

BACKGROUND

[002] Titanium alloys have low density and high strength, acceptable ductility and are thus industrially applicable in many fields. Titanium aluminide alloys may have even lower density than conventional titanium alloys. However, titanium aluminide alloys are known to have poor ductility as compared to titanium alloys.

SUMMARY OF THE DISCLOSURE

[003] The present disclosure relates to new titanium aluminide alloys and methods of making the same. In one embodiment, and as explained in further detail below, the new titanium aluminide alloys generally comprise (or in some instances, consist essentially of or consist of) 42.5 to 45.75 at. % Al, 1.75 to 4.2 at. % Nb, 0.8 to 1.55 at. % Cr, at least one of (a) 0.10 to 1.25 at. % B and (b) 0.15 to 0.45 at. % Si, up to 4.0 at. % Ta, up to 0.75 at. % W, and up to 0.55 at. % Mo, the balance being titanium, optional incidental elements, and impurities. In one embodiment, the new titanium aluminide alloys realize an improved combination of properties, such as an improved combination of two or more of printability, strength, ductility, castability and oxidation resistance, among others. Improved printability for additive manufacturing may be realized, for instance, via a reduced cracking tendency during solidification. In one embodiment, the titanium aluminide alloy compositions described herein may facilitate the production of crack-free titanium aluminide products for use in high temperature applications, such as, for instance, engine and turbine applications, among others. These and other aspects of the new titanium aluminide alloys, including applicable compositions, processing, properties and product applications, are described in further detail below. i. Composition

[004] As noted above, the new titanium aluminide alloys generally comprise (or in some instances, consist essentially of or consist of) 42.5 to 45.75 at. % Al, 1.75 to 4.2 at. % Nb, 0.8 to 1.55 at. % Cr, at least one of (a) 0.10 to 1.25 at. % B and (b) 0.15 to 0.45 at. % Si, up to 4.0 at. % Ta, up to 0.75 at. % W, and up to 0.55 at. % Mo, the balance being titanium, optional incidental elements, and impurities. In one embodiment, a titanium aluminide alloy comprises 0.15 to 0.45 at. % Si. In another embodiment, a titanium aluminide alloy comprises 0.10 to 1.25 at. % B. In another embodiment, a titanium aluminide alloy comprises both 0.15 to 0.45 at. % Si and 0.10 to 1.25 at. % B. In some embodiments, a titanium aluminide alloy comprises from 0.10 to 1.25 at. % B, wherein the B is from Bmin to Bmax, wherein Bmin and Bmax are calculated as Bmin (in at. %) = (15.4A1 - l7.6Cr - 2l.5Mo - l l. lNb - 6.9Ta - 25W - 527) / 405, and Bmax (in at. %) = (791 - 14.6A1 - 8. lCr - 8.5Mo - 5. lNb - 3.3Ta + 7.3W) / 102.

[005] As noted above, the new titanium aluminide alloys generally may include up to 4.0 at. % Ta, up to 0.75 at. % W, and up to 0.55 at. % Mo. In some embodiments, a titanium aluminide alloy includes at least 0.1 at. % Ta. In some embodiments, a titanium aluminide alloy includes at least 0.1 at. % W. In some embodiments, a titanium aluminide alloy includes at least 0.1 at. % Mo.

[006] As noted above, the titanium aluminide alloys generally include the stated alloying ingredients, the balance being titanium, optional incidental elements, and impurities. As used herein,“incidental elements” means those elements or materials, other than the above listed elements, that may optionally be added to the alloy to assist in the production of the alloy. Incidental elements may be present in minor amounts, or may be present in significant amounts, and may add desirable or other characteristics on their own without departing from the alloys described herein, so long as the alloy retains the desirable characteristics described herein. It is to be understood, however, that the scope of this disclosure should not/cannot be avoided through the mere addition of an element or elements in quantities that would not otherwise impact the combinations of properties desired and attained herein. ii. Processing

[007] The new titanium aluminide products made may be produced via any suitable method, including shape casting, wrought processing, powder metallurgy, and additive manufacturing, among others. In one embodiment, additive manufacturing is used to make a new titanium aluminide product.

a. Additive manufacturing

[008] As used herein,“additive manufacturing” means,“a process of joining materials to make objects from 3D model data, usually layer upon layer, as opposed to subtractive manufacturing methodologies”, as defined in ASTM F2792-l2a entitled “Standard Terminology for Additively Manufacturing Technologies”. The new titanium aluminide products may be manufactured via any appropriate additive manufacturing technique described in this ASTM standard, such as binder jetting, directed energy deposition, material extrusion, material jetting, powder bed fusion, or sheet lamination, among others. Non limiting examples of additive manufacturing processes useful in producing additively manufactured titanium aluminide alloy products include, for instance, DMLS (direct metal laser sintering), SLM (selective laser melting), SLS (selective laser sintering), and EBM (electron beam melting), among others.

[009] Additive manufacturing techniques may facilitate the selective heating of additive manufacturing feedstock(s) above the liquidus temperature of the particular titanium aluminide alloy to be formed, thereby forming a molten pool, followed by rapid solidification of the molten pool. For instance, in one embodiment, a method for producing the new titanium aluminide alloy products includes (a) selectively heating a titanium aluminide alloy (such as any of the titanium aluminide alloys described above in Section i) above its liquidus temperature via an energy source (e.g., at least one of a laser and electron beam), thereby forming a molten pool, and (b) cooling the molten pool, thereby forming a solid material. Steps (a)-(b) may be repeated as necessary until the additively manufactured titanium aluminide alloy product is completed. In one embodiment, cooling the molten pool comprises forming b phase crystals, and then titanium boride particles, and then a phase crystals. In one embodiment, cooling the molten pool comprises cooling at a cooling rate of at least 10³ °C per second. In one embodiment, the cooling rate is at least 10⁴ °C per second. In another embodiment, the cooling rate is at least 10⁵ °C per second. In yet another embodiment, the cooling rate is at least 10⁶ °C per second.

[0010] In one embodiment, an additive manufacturing process includes depositing successive layers of one or more powders and then selectively melting and/or sintering the powders to create, layer-by-layer, an additively manufactured titanium aluminide alloy product. In one embodiment, a method comprises (a) dispersing a powder in a bed, (b) selectively heating a portion of the powder (e.g., via a laser) to a temperature above the liquidus temperature of the particular titanium aluminide alloy product to be formed, (c) forming a molten pool and (d) cooling the molten pool to form a solidified mass. Steps (a)-(d) may be repeated as necessary until the additively manufactured titanium aluminide alloy product is completed.

[0011] In one embodiment, an additive manufacturing process uses an EOSINT M 280 Direct Metal Laser Sintering (DMLS) additive manufacturing system, or comparable system, available from EOS GmbH (Robert-Stirling-Ring 1, 82152 Krailling/Munich, Germany). [0012] In one embodiment, an additive manufacturing process uses an AconityMIDI Direct Metal Laser Sintering (DMLS) additive manufacturing system, or comparable system, available from Aconity3D GmbH (Kaiserstr. 98, 52134 Herzogenrath, Germany).

[0013] In one embodiment, a method comprises (a) dispersing a powder in a bed, (b) selectively binder jetting the powder, and repeating steps (a)-(b), as appropriate, until a green additively manufactured part is completed. The green additively manufactured part may be further processed, such as by sintering and/or hot isostatic pressing (“HIP’ing”).

[0014] In one embodiment, directed energy deposition techniques are utilized. In one embodiment, a method comprises spraying one or more additive manufacturing feedstock powders in a controlled environment, and concomitant to the spraying, a laser is used to melt and/or solidify the sprayed additive manufacturing feedstock powder(s). This spraying and concomitant energy deposition may be repeated as necessary to facilitate production of an additively manufactured titanium aluminide alloy product.

[0015] In one embodiment, electron beam (EB) or plasma arc techniques are utilized. Electron beam techniques may facilitate production of larger parts than readily produced via laser additive manufacturing techniques. For instance, in one embodiment, a method comprises feeding a wire (e.g., < 2.54 mm in diameter) to the wire feeder portion of an electron beam gun. The wire may comprise any of the titanium aluminide alloys described above. The electron beam heats the wire or tube, as the case may be, above the liquidus point of the titanium aluminide alloy to be formed, followed by rapid solidification of the molten pool to form the deposited material.

[0016] To facilitate additive manufacturing of the new titanium aluminide alloys, the new titanium aluminide alloys may be produced as any applicable additive manufacturing feedstock, for instance, such as a powder, a wire, a sheet (e.g., foil) and combinations thereof.

[0017] In one embodiment, a titanium aluminide alloy additive manufacturing feedstock is a powder. As used herein,“powder” means a material comprising a plurality of particles suited to produce a titanium aluminide alloy product via additive manufacturing. In the context of additive manufacturing powder feedstocks,“particle” means a minute fragment of matter having a size suitable for use in the powder of the powder bed (e.g., a size of from 5 microns to 100 microns). Shavings are types of particles. Suitable methods for producing powders include, for instance, atomization (e.g., gas atomization, plasma atomization), and impingement of a molten liquid (e.g., solidification of an impinging molten metal droplet on a cold substrate), among others. [0018] In one embodiment, a titanium aluminide alloy additive manufacturing feedstock is a wire. In some embodiments, the additive manufacturing feedstock is comprised of one or more wires. A ribbon is a type of wire. The wires may be produced, for instance, via melt spinning to produce a ribbon. Powder cored wires may also be used.

[0019] In one embodiment, a titanium aluminide alloy additive manufacturing feedstock is a sheet. Foil is a type of sheet. Sheets may be used in additive manufacturing processes such as sheet lamination, per ASTM F2792-l2a.

[0020] In any of the above-described embodiments, a titanium aluminide additively manufactured product may be thermally treated and/or subjected to thermomechanical processing (“TMP”) to realize a final product. In one embodiment, a method comprises thermally treating a titanium aluminide additively manufactured product (e.g., a crack-free titanium aluminide alloy product). Suitable thermal treatments may include, for instance, one or more of hot isostatic pressing (“HIP”), annealing, and/or heat treating and quenching the titanium aluminide additively manufactured product. A thermal treatment may include, for instance, altering the microstructure of an additively manufactured titanium aluminide product (e.g., to reduce the amount of beta phase). Furthermore, the new titanium aluminide alloy products may be produced by hybrid processing methods, such as methods that couple additive manufacturing with deformation (e.g., hot-die forging, non-isothermal forging, isothermal forging, among others). In one embodiment, the new titanium aluminide alloys may be both additively manufactured and hot worked (e.g., in a manner consistent with the methods described in commonly owned U.S. Patent Publication No. 2015/013144).

[0021] In one embodiment, an additively manufactured titanium aluminide alloy product is a crack-free product. As used herein,“crack-free product” means a product that is sufficiently free of cracks such that it can be used for its intended, end-use purpose. The determination of whether a product is“crack-free” may be made by any suitable method, such as, by visual inspection, dye penetrant inspection, and/or by non-destructive test methods. In some embodiments, the non-destructive test method is an ultrasonic inspection. In some embodiments, the non-destructive test method is a computed topography scan (“CT scan”) inspection (e.g., by measuring density differences within the product). In one embodiment, a titanium aluminide alloy product is determined to be crack-free by visual inspection. In another embodiment, a titanium aluminide alloy product is determined to be crack-free by dye penetrant inspection. In yet another embodiment, a titanium aluminide alloy product is determined to be crack-free by CT scan inspection. In another embodiment, a titanium aluminide alloy product is determined to be crack-free during an additive manufacturing process, wherein in-situ monitoring of the additively manufactured build is employed.

b. Other Methods

[0022] As noted above, aside from additive manufacturing, the new titanium aluminide alloys may be produced via other methods, such as by shape casting the alloy, or wrought processing the alloy, among others. Further, the new titanium aluminide alloys may be cast via any suitable method. In one embodiment, a method comprises heating a titanium aluminide alloy (such as any of the titanium aluminide alloys described above in Section i) above its liquidus temperature, thereby forming a liquid mixture, and then (b) cooling the liquid mixture to below its solidus temperature thereby forming a solid material. In one embodiment, the cooling comprises first forming b phase crystals, and then forming titanium boride particles, and then forming a phase crystals. The solid material may be, for instance, an ingot, a billet, or shape cast product, among others.

[0023] Ingot and/or billets of the new titanium aluminide alloys may be further processed to titanium aluminide alloy products using, for instance, forging, rolling, and extruding, among others. In one embodiment, a method comprises hot working a titanium aluminide alloy, such as by forging, rolling or extruding. In one embodiment, a wrought titanium aluminide alloy product is a rolled product. In one embodiment, a wrought titanium aluminide alloy product is a forged product. In one embodiment, a wrought titanium aluminide alloy is an extruded product. In one embodiment, a wrought titanium aluminide alloy product is a plate. In one embodiment, a titanium aluminide alloy product is a sheet. In any of the above embodiments, the wrought titanium aluminide alloy product may be crack-free.

[0024] The new titanium aluminide alloys may also be produced via shape casting. Shape cast products are those products that achieve their final or near final product form after the casting process. For instance, the new titanium aluminide alloys may be cast into a near-net shape (e.g., via investment casting). In one embodiment, a shape cast titanium aluminide product is crack-free.

[0025] The new titanium aluminide alloys may also be produced via powder metallurgy methods. For instance, a titanium aluminide powder may be compacted via low pressure methods, such as loose powder sintering, slip casting, slurry casting, tape casting, or vibratory compaction. In another aspect, pressure may be used to realize the compaction by methods such as, for instance, die compaction, cold/hot isostatic pressing, and/or sintering. In one embodiment, a powder metallurgy titanium aluminide product is crack-free. [0026] In any of the above-described embodiments, a titanium aluminide product (e.g., a wrought product, a shape cast product, a powder metallurgy product, an additively manufactured product) may be thermally treated. Suitable thermal treatments may include, for instance, one or more of hot isostatic pressing (“HIP”), annealing, and/or heat treating and quenching. A thermal treatment may include, for instance, altering the microstructure of the titanium aluminide product (e.g., to reduce the amount of beta phase). iii. Properties

[0027] As noted above, the new titanium aluminide alloys may realize an improved combination of properties, such as an improved combination of two or more of printability, strength, ductility, castability and oxidation resistance, among others. The new titanium aluminide alloys may also or alternatively realize unique solidification characteristics, which may result in improved hot cracking susceptibility and/or low non-equilibrium freezing ranges. These and other properties of the new titanium aluminide alloys are described in further detail below.

a. Solidification Characteristics

[0028] In one embodiment, the new titanium aluminide alloys described herein may realize unique solidification characteristics, such as a hot cracking susceptibility from 2600 to 5000°C, a non-equilibrium freezing range from 120 to l90°C, and/or a Unique Solidification Pathway, as described in greater detail below. Due to at least the unique solidification characteristics, the new titanium aluminide alloys may realize, for instance, improved printability for additive manufacturing.

[0029] In one embodiment, a new titanium aluminide alloy realizes a hot cracking susceptibility (“HCS”) of from 2600 to 5000°C. The HCS of a titanium aluminide alloy generally describes the absolute maximum steepness of the Scheil solidification curve (i.e., a plot of °C versus Vf_s (square root of the fraction of solid)) toward the end of the solidification process. Titanium aluminide alloys having a HCS of less than 2600°C may have an insufficient amount of alloying elements to realize sufficient oxidation resistance (e.g., at elevated temperatures). For instance, an alloy with an insufficient amount of one or more of Nb, Cr, Ta, W, Mo, and Si may realize poor oxidation resistance. Thus, the invention alloys described herein may realize a HCS of at least 2600°C. Titanium aluminide alloys having a HCS greater than 5000°C may realize a large non-equilibrium freezing range (e.g., greater than l90°C). Such titanium aluminide alloys may be prone to cracking (e.g., during additive manufacturing and/or casting) due to microsegregation and/or insufficient liquid feeding during the final stages of solidification. Thus, the invention alloys described herein may realize a HCS of not greater than 5000°C.

[0030] As noted above, the new titanium aluminide alloys described may realize a non- equilibrium freezing range of from 120 to l90°C. A titanium aluminide alloy having a non equilibrium freezing range from 120 to l90°C may facilitate unique solidification characteristics, such as the Unique Solidification Pathway described in greater detail below. A non-equilibrium freezing range of not greater than l20°C may realize a solidification pathway where the peritectic reaction b + liquid - a occurs. Solidification pathways where peritectic reactions occur may be unfavorable, as peritectic reactions may promote cracking (e.g., due to an insufficient amount of ductile b phase present in the alloy immediately below the solidus temperature). Thus, the new titanium aluminide alloys described herein may realize a non-equilibrium freezing range of at least l20°C. Titanium aluminide alloys having a non-equilibrium freezing range of greater than l90°C may form an excessive amount of b phase during solidification, which may negatively impact the physical properties of the titanium aluminide alloy. For instance, an excessive amount of b phase may deteriorate physical properties such as ductility, formability, fracture toughness, and damage tolerance properties, among others. An excessive amount of b phase may deteriorate the ductility, for instance, as the more ductile disordered bcc phase may transform into the less ductile B2 phase. Thus, the new titanium aluminide alloys described herein may realize a non equilibrium freezing range of not greater than l90°C.

[0031] As used herein,“b phase” or“beta phase” means at least one of the ordered and disordered body-centered cubic titanium phases. As noted in the above definition, all references to“b phase” or“beta phase” include both the ordered phase (sometimes referred to as B2) and disordered phase (sometimes referred to as bcc), unless the context clearly dictates otherwise. The terms,“ordered” and“disordered” refer to the symmetrical packing of atoms in the crystal structure. For instance, the ordered beta phase may be compared to the ionic compound CsCl that has symmetrical packing of cesium and chlorine atoms in the crystal lattice. Conversely, the disordered beta phase does not have the symmetrical packing of atoms (e.g., a random distribution of atoms).

[0032] As used herein,“a” or“alpha phase” means a disordered hexagonal close-packed (hep) titanium phase. The alpha phase includes aluminum in solid solution, i.e., as a substitute atom for titanium. Similar to the beta phase, the terms“disordered” refers to the lack of symmetrical packing of atoms in the crystal structure. [0033] The new titanium aluminide alloys described herein may form via a solidification pathway that may facilitate the formation of equiaxed grains and/or the production of crack- free titanium aluminide products, among other characteristics. The solidification pathway generally occurs in a sequence, where b phase crystals form first from the liquid, then titanium boride particles form, and then a crystals form, and this solidification pathway is sometimes referred to herein as the“Unique Solidification Pathway.” In one embodiment, the Unique Solidification Pathway realizes the formation of b crystals from the liquid prior to the formation of titanium boride particles (e.g., TiB and/or T1B2 particles). Titanium boride particles may be useful in facilitating grain refinement of the titanium aluminide alloys, and grain refinement may restrict and/or prevent cracking during solidification. However, an excessive amount of boron may result in a solidification pathway where titanium boride particles form first from the liquid, and such a solidification pathway may promote the formation of large titanium boride particles and/or titanium boride particles having a lacey morphology. Certain properties of the titanium aluminide products may be negatively impacted by large titanium boride particles and/or titanium boride particles having a lacey morphology. For instance, the tensile properties (e.g., elongation) and fatigue may be negatively impacted. Further, large titanium boride particles may have a reduced efficacy for grain refining titanium aluminide alloys, and/or a reduced efficacy for restricting and/or preventing cracking (e.g., during additive manufacturing and/or casting).

[0034] An appropriate amount of boron may facilitate the realization of the Unique Solidification Pathway. In this regard, the new titanium aluminide alloys may include 0.10 to 1.25 at. % boron. In one embodiment, a new titanium aluminide alloy includes 0.10 to 1.25 at. % boron, where the B is from Bmin to Bmax, where Bmin and Bmax are calculated as:

Bmin (in at. %) = (15.4A1 - l7.6Cr - 2l.5Mo - l l. lNb - 6.9Ta - 25W - 527) / 405; and

Bmax (in at. %) = (791 - 14.6A1 - 8TCr - 8.5Mo - 5. lNb - 3.3Ta + 7.3W) / 102.

[0035] The titanium aluminide alloys may realize at least one of (i) a hot cracking susceptibility from 2600 to 5000°C, (ii) a non-equilibrium freezing range from 120 to l90°C, and (iii) 0.10 to 1.25 at. % B, where the B is from Bmin to Bmax (per above). In one embodiment, a titanium aluminide alloy realizes at least two of (i), (ii), and (iii). In another embodiment, a titanium aluminide alloy realizes all of (i), (ii), and (iii).

[0036] In one embodiment, a titanium aluminide alloy realizes a hot cracking susceptibility of from 2600 to 5000°C, wherein the hot cracking susceptibility (in °C) is calculated as:

-246. lTi + 129.5A1 + 6483Cr + H54Mo + 625Nb + 697Ta - 924W - 225lSi (Equation 1) wherein Ti, Al, Cr, Mo, Nb, Ta, W, and Si are provided in at. %.

[0037] In one embodiment, a titanium aluminide alloy realizes a non-equilibrium freezing range of from 120 to l90°C, wherein the non-equilibrium freezing range (in °C) is calculated as:

4.lTi - 3.7A1 + 39.5Cr + 2l. lMo + l2. lNb + l9.8Ta + 18.4W - 34.4Si (Equation 2) wherein Ti, Al, Cr, Mo, Nb, Ta, W, and Si are provided in at. %.

[0038] As noted above, in one embodiment, a new titanium aluminide alloy includes 0.10 to 1.25 at. % boron, where the B is from Bmin to Bmax, where Bmin and Bmax are calculated as: Bmin (in at. %) = (15.4A1 - l7.6Cr - 2l.5Mo - l l.lNb - 6.9Ta - 25W - 527) / 405 (Equation 3) Bm_ax (in at. %) = (791 - 14.6A1 - 8. lCr - 8.5Mo - 5. lNb - 3.3Ta + 7.3W) / 102 (Equation 4) wherein Al, Cr, Mo, Nb, Ta and W are provided in at. %.

[0039] The mathematical formulae given above for the hot cracking susceptibility (Equation 1), non-equilibrium freezing range (Equation 2), Bmin (Equation 3) and Bmax (Equation 4) were determined via statistical analysis, including modeling a large number of alloy compositions using the calculation of phase diagram (“CALPHAD”) method. In this regard, the hot cracking susceptibility and non-equilibrium freezing range were determined using the Scheil solidification model (complete diffusion in the liquid; no diffusion in the solid; equilibrium at the interface between the solid and liquid). In conjunction with the CALPHAD method, the hot cracking susceptibility of the titanium aluminide alloys was determined using the method described in the following journal article: S. Kou.“A Simple Index for Predicting the Susceptibility to Solidification Cracking,” Welding Journal, v.94, 2015, p. 374-s.

[0040] FIGS. la-7b are non-limiting graphs illustrating the effect of the alloying elements on the non-equilibrium freezing range (Scheil solidification range) and the hot cracking susceptibility. The graphs are plotted versus the alloying element concentrations for each of aluminum (FIGS la-lb), niobium (FIGS. 2a-2b), chromium (FIGS. 3a-3b), silicon (FIGS. 4a-4b), tantalum (FIGS. 5a-5b), tungsten (FIGS. 6a-6b), and molybdenum (FIGS. 7a-7b.) In FIGS. la-7b, the alloys designated as“IN” are within the scope of the inventive alloy compositions described above in Section i. These alloys may realize one or more of (i) a hot cracking susceptibility of from 2600 to 5000°C, (ii) a non-equilibrium freezing range of from 120 to l90°C, and (iii) 0.10 to 1.25 at. % B, where the B is from Bmin to Bmax, as calculated using Equations 1-4. The alloys designated as“OUT” in FIGS. la-7b are outside the scope of the inventive alloy compositions described above in Section i and do not realize at least one of (i) a hot cracking susceptibility from 2600 to 5000°C, (ii) a non-equilibrium freezing range from 120 to l90°C, and (iii) 0.10 to 1.25 at. % B, where the B is from Bmin to Bmax, as calculated using Equations 1-4.

b. Physical Properties

[0041] As noted above, the new titanium aluminide alloys may realize an improved combination of properties, such as an improved combination of two or more of printability, strength, ductility, castability and oxidation resistance, among others. In one embodiment, a new titanium aluminide alloy realizes an improved combination of at least three of printability, strength, ductility, castability and oxidation resistance. In another embodiment, a new titanium aluminide alloy realizes an improved combination of at least four of printability, strength, ductility, castability and oxidation resistance. In another embodiment, a new titanium aluminide alloy realizes an improved combination of all of printability, strength, ductility, castability and oxidation resistance.

[0042] Improved strength and/or ductility may be realized at room temperature and/or at elevated temperature (e.g., at 700°C, or higher). In one embodiment, a new titanium aluminide alloy realizes a tensile yield strength (TYS) at room temperature of at least 600 MPa. In another embodiment, a new titanium aluminide alloy realizes a tensile yield strength at room temperature of at least 625 MPa. In yet another embodiment, a new titanium aluminide alloy realizes a tensile yield strength at room temperature of at least 650 MPa. In another embodiment, a new titanium aluminide alloy realizes a tensile yield strength at room temperature of at least 675 MPa. In yet another embodiment, a new titanium aluminide alloy realizes a tensile yield strength at room temperature of at least 700 MPa. In another embodiment, a new titanium aluminide alloy realizes a tensile yield strength at room temperature of at least 725 MPa, or more.

[0043] In one embodiment, a new titanium aluminide alloy realizes an ultimate tensile strength (UTS) at room temperature of at least 700 MPa. In another embodiment, a new titanium aluminide alloy realizes an ultimate tensile strength at room temperature of at least 725 MPa. In yet another embodiment, a new titanium aluminide alloy realizes an ultimate tensile strength at room temperature of at least 750 MPa. In another embodiment, a new titanium aluminide alloy realizes an ultimate tensile strength at room temperature of at least 775 MPa. In yet another embodiment, a new titanium aluminide alloy realizes an ultimate tensile strength at room temperature of at least 800 MPa. In another embodiment, a new titanium aluminide alloy realizes an ultimate tensile strength at room temperature of at least 825 MPa. In yet another embodiment, a new titanium aluminide alloy realizes an ultimate tensile strength at room temperature of at least 850 MPa. In another embodiment, a new titanium aluminide alloy realizes an ultimate tensile strength at room temperature of at least 875 MPa, or more.

[0044] In one embodiment, a new titanium aluminide alloy realizes an elongation at room temperature of at least 1.0%. In another embodiment, a new titanium aluminide alloy realizes an elongation at room temperature of at least 1.25%. In yet another embodiment, a new titanium aluminide alloy realizes an elongation at room temperature of at least 1.5%, or more.

[0045] In any of the above-described room temperature tensile property embodiments, the titanium aluminide alloy may be, for instance, an additively manufactured product. Furthermore, in some embodiments, the tensile properties may be measured at room temperature in accordance with ASTM E8.

[0046] In one embodiment, a new titanium aluminide alloy realizes a tensile yield strength (TYS) at 700°C of at least 450 MPa. In another embodiment, a new titanium aluminide alloy realizes a tensile yield strength at 700°C of at least 475 MPa. In yet another embodiment, a new titanium aluminide alloy realizes a tensile yield strength at 700°C of at least 500 MPa. In another embodiment, a new titanium aluminide alloy realizes a tensile yield strength at 700°C of at least 525 MPa. In yet another embodiment, a new titanium aluminide alloy realizes a tensile yield strength at 700°C of at least 550 MPa. In another embodiment, a new titanium aluminide alloy realizes a tensile yield strength at 700°C of at least 575 MPa, or more.

[0047] In one embodiment, a new titanium aluminide alloy realizes an ultimate tensile strength (UTS) at 700°C of at least 650 MPa. In another embodiment, a new titanium aluminide alloy realizes an ultimate tensile strength at 700°C of at least 675 MPa. In yet another embodiment, a new titanium aluminide alloy realizes an ultimate tensile strength at 700°C of at least 700 MPa. In another embodiment, a new titanium aluminide alloy realizes an ultimate tensile strength at 700°C of at least 725 MPa. In yet another embodiment, a new titanium aluminide alloy realizes an ultimate tensile strength at 700°C of at least 750 MPa. In another embodiment, a new titanium aluminide alloy realizes an ultimate tensile strength at 700°C of at least 775 MPa. In yet another embodiment, a new titanium aluminide alloy realizes an ultimate tensile strength at 700°C of at least 790 MPa, or more.

[0048] In one embodiment, a new titanium aluminide alloy realizes an elongation at 700°C of at least 1.5%. In another embodiment, a new titanium aluminide alloy realizes an elongation at 700°C of at least 1.75%. In yet another embodiment, a new titanium aluminide alloy realizes an elongation at 700°C of at least 2.0%. In another embodiment, a new titanium aluminide alloy realizes an elongation at 700°C of at least 2.25%. In yet another embodiment, a new titanium aluminide alloy realizes an elongation at 700°C of at least 2.5%. In another embodiment, a new titanium aluminide alloy realizes an elongation at 700°C of at least 2.75%. In yet another embodiment, a new titanium aluminide alloy realizes an elongation at 700°C of at least 3.0%. In another embodiment, a new titanium aluminide alloy realizes an elongation at 700°C of at least 3.25%. In yet another embodiment, a new titanium aluminide alloy realizes an elongation at 700°C of at least 3.5%. In another embodiment, a new titanium aluminide alloy realizes an elongation at 700°C of at least 3.75%. In yet another embodiment, a new titanium aluminide alloy realizes an elongation at 700°C of at least 4.0%. In another embodiment, a new titanium aluminide alloy realizes an elongation at 700°C of at least 4.25%. In yet another embodiment, a new titanium aluminide alloy realizes an elongation at 700°C of at least 4.5%, or more.

[0049] In any of the above-described elevated temperature tensile property embodiments, the titanium aluminide alloy may be, for instance, an additively manufactured product. Furthermore, in some embodiments, the tensile properties may be measured at elevated temperature in accordance with ASTM E21.

[0050] The new titanium aluminide alloys may have improved ductility, which may help facilitate the realization of industrially applicable titanium aluminide products. Industrially applicable titanium aluminide alloys may be suitable for routine handling and/or installation at room temperature. In some embodiments, the new titanium aluminide alloys realize a room temperature ductility sufficient for industrial applicability. iv. Product Applications

[0051] The new titanium aluminide alloys may find use in various applications, such as use in high temperature applications employed in the automotive and aerospace industries, to name a few. For instance, the new titanium aluminide alloys may find applicability as turbine components in high temperature applications. Furthermore, aerospace applications may also include the production of aerospace components, such as turbine blades, heat exchangers, noise attenuation structures (e.g., for helicopter engine exhaust systems), truss core sheet, sheet for thermal protection systems, and other aerospace engine components. In this regard, aerospace engine components may include static or rotating aerospace engine components, including nozzles, cones, blisks, and discs, among others. Automotive applications may include the production of automotive engine components, such as turbocharger wheels and exhaust valves, among others. v. Miscellaneous

[0052] The figures constitute a part of this specification and include illustrative embodiments of the present disclosure and illustrate various objects and features thereof. In addition, any measurements, specifications and the like shown in the figures are intended to be illustrative, and not restrictive. Therefore, specific structural and functional details disclosed herein are not to be interpreted as limiting, but merely as a representative basis for teaching one skilled in the art to variously employ the present invention.

[0053] Among those benefits and improvements that have been disclosed, other objects and advantages of this invention will become apparent from the following description taken in conjunction with the accompanying figures. Detailed embodiments of the present invention are disclosed herein; however, it is to be understood that the disclosed embodiments are merely illustrative of the invention that may be embodied in various forms. In addition, each of the examples given in connection with the various embodiments of the invention is intended to be illustrative, and not restrictive.

[0054] Throughout the specification and claims, the following terms take the meanings explicitly associated herein, unless the context clearly dictates otherwise. The phrases“in one embodiment” and“in some embodiments” as used herein do not necessarily refer to the same embodiment(s), though it may. Furthermore, the phrases“in another embodiment” and “in some other embodiments” as used herein do not necessarily refer to a different embodiment, although it may. Thus, as described herein, various embodiments of the invention may be readily combined, without departing from the scope or spirit of the invention.

[0055] In addition, as used herein, the term "or" is an inclusive "or" operator, and is equivalent to the term "and/or," unless the context clearly dictates otherwise. The term "based on" is not exclusive and allows for being based on additional factors not described, unless the context clearly dictates otherwise. In addition, throughout the specification, the meaning of "a," "an," and "the" include plural references, unless the context clearly dictates otherwise. The meaning of "in" includes "in" and "on", unless the context clearly dictates otherwise.

BRIEF DESCRIPTION OF THE DRAWINGS

[0056] FIG. la is a non-limiting graphical illustration of the effect of aluminum on the non equilibrium freezing range. [0057] FIG. lb is a non-limiting graphical illustration of the effect of aluminum on the hot cracking susceptibility.

[0058] FIG. 2a is a non-limiting graphical illustration of the effect of niobium on the non equilibrium freezing range.

[0059] FIG. 2b is a non-limiting graphical illustration of the effect of niobium on the hot cracking susceptibility.

[0060] FIG. 3 a is a non-limiting graphical illustration of the effect of chromium on the non equilibrium freezing range.

[0061] FIG. 3b is a non-limiting graphical illustration of the effect of chromium on the hot cracking susceptibility.

[0062] FIG. 4a is a non-limiting graphical illustration of the effect of silicon on the non equilibrium freezing range.

[0063] FIG. 4b is a non-limiting graphical illustration of the effect of silicon on the hot cracking susceptibility.

[0064] FIG. 5a is a non-limiting graphical illustration of the effect of tantalum on the non equilibrium freezing range.

[0065] FIG. 5b is a non-limiting graphical illustration of the effect of tantalum on the hot cracking susceptibility.

[0066] FIG. 6a is a non-limiting graphical illustration of the effect of tungsten on the non equilibrium freezing range.

[0067] FIG. 6b is a non-limiting graphical illustration of the effect of tungsten on the hot cracking susceptibility.

[0068] FIG. 7a is a non-limiting graphical illustration of the effect of molybdenum on the non-equilibrium freezing range.

[0069] FIG. 7b is a non-limiting graphical illustration of the effect of molybdenum on the hot cracking susceptibility.

DETAILED DESCRIPTION

Example 1

[0070] Four experimental alloy compositions were evaluated for their oxidation resistance, hot cracking susceptibility, and minimum energy density to realize no cracking. The four experimental alloys included three inventive titanium aluminide alloys (Alloys 1-3) and one non-inventive titanium aluminide alloy (Alloy 4). The experimental alloys were cast as 1 inch x 1 inch x 1.5 inches blocks using a plasma arc furnace under argon atmosphere. After their casting, each block was cut by wire electro-discharge machining into 1 inch x 1 inch x 0.25 inch coupons for further evaluation. The chemical compositions of the alloys were analyzed using inductively coupled plasma atomic emission spectroscopy, and are given below in Table 1 in atomic percentages.

Table 1: Composition of Experimental Alloys (in at. %)

[0071] The oxidation resistances of the experimental alloys were evaluated by exposing samples of the experimental alloys to air at 800°C for 1000 hours in a furnace. The mass gained per unit of surface area was measured every 24 hours by removing the samples from the furnace, allowing them to cool to room temperature, and weighing on a scale. Results from the oxidation resistance tests after 1,000 hours are given in Table 2, below. In this regard, the inventive alloys realized superior oxidation resistance, when compared to the non- inventive alloy.

Table 2: Oxidation Resistance Test Results

[0072] Samples having the compositions of Alloys 1-4 were solidified by a method that realizes a solidification rate on the order of 10⁶ °C/s, and using a varied amount of energy density (units of J/mm³). Following solidification, metallographic analysis was performed on the as-solidified samples to determine the linear crack density (number of cracks/cm). In this regard, the energy density at which no cracks were observed was determined to be the required minimum energy density (Emin), and the values of which are given in Table 3, below. The minimum energy density required to achieve no cracking in the as-solidified condition may be an important additive manufacturing parameter for titanium aluminide alloys because the minimum energy density is generally related to the amount of aluminum evaporation. For instance, as the energy density employed increases, the amount of aluminum evaporation may increase. Thus, titanium aluminide alloys having a lower minimum energy density to realize no cracks, such as the inventive alloys, may be more suitable for use in additive manufacturing than conventional titanium aluminide alloys.

Table 3: Minimum Energy Density (in J/mm³) for the Experimental Alloys

[0073] The hot cracking susceptibilities of the experimental alloys were modeled using the calculation of phase diagram (“CALPHAD”) method, and using the method outlined in the following journal article: S. Kou.“A Simple Index for Predicting the Susceptibility to Solidification Cracking,” Welding Journal, v.94, 2015, p. 374-s. The hot cracking susceptibility modeling results (in °C) are given in Table 4, below. The inventive alloys realize hot cracking susceptibility values from 2600 to 5000 °C. Conversely, the non- inventive alloy realizes a hot cracking susceptibility of approximately 10,600 °C. The non- inventive alloy also realized a higher minimum energy density to achieve no cracking when compared to the inventive alloys, indicating that the non-inventive alloy is more likely to realize (i) larger amounts of aluminum evaporation during additive manufacturing and/or (ii) cracking during additive manufacturing when energy densities less than the minimum required value are employed.

Table 4: Modeled Hot Cracking Susceptibility Values for

the Experimental Alloys

Example 2 [0074] An additional experimental alloy (Alloy 5) was cast as an ingot. After casting, the ingot was atomized into powder. The composition of the powder was measured using inductively coupled plasma atomic emission spectroscopy, the results of which are given in atomic percentages in Table 5, below.

Table 5: Composition of Alloy 5 Powder (in at. %)

[0075] Additively manufactured specimens were produced from the atomized powder of Alloy 5 using a selective laser melting (“SLM”) additive manufacturing apparatus. Additively manufactured layers were built, layer-upon-layer, in the vertical direction (i.e., the Z-direction). After their production, all of the specimens were subjected to a hot isostatic pressing treatment and then heat-treated. The heat-treated specimens were then machined into tensile testing specimens for room temperature and elevated temperature tensile testing. Room temperature (25°C) tensile testing was conducted on some of the tensile testing specimens and in accordance with ASTM E8. Elevated temperature (700°C) tensile testing was conducted on the remaining tensile testing specimens and in accordance with ASTM E21. Tensile testing was conducted in the XY-plane of the samples (i.e., a direction orthogonal to the build (Z) direction). The room temperature and elevated temperature tensile testing results are given in Table 6, below.

Table 6: Tensile Properties of Alloy 5

[0076] Aspects of the invention will now be described with reference to the following numbered clauses:

Clause 1. A titanium aluminide alloy comprising:

42.5 to 45.75 at. % Al;

1.75 to 4.2 at. % Nb;

0.8 to 1.55 at. % Cr; at least one of:

(a) 0.10 to 1.25 at. % B; and

(b) 0.15 to 0.45 at. % Si;

up to 4.0 at. % Ta;

up to 0.75 at. % W; and

up to 0.55 at. % Mo;

the balance being titanium, optional incidental elements, and impurities.

Clause 2. The titanium aluminide alloy of clause 1, wherein the titanium aluminide alloy includes at least 0.1 at. % Ta.

Clause 3. The titanium aluminide alloy of any of the preceding clauses, wherein the titanium aluminide alloy includes at least 0.1 at. % W.

Clause 4. The titanium aluminide alloy of any of the preceding clauses, wherein the titanium aluminide alloy includes at least 0.1 at. % Mo.

Clause 5. The titanium aluminide alloy of any of the preceding clauses, wherein the titanium aluminide alloy comprises (i) 0.10 to 1.25 at. % B, or (ii) 0.15 to 0.45 at. % Si;, or (iii) both 0.10 to 1.25 at. % B and 0.15 to 0.45 at. % Si.

Clause 6. The titanium aluminide alloy of clause 1, wherein the titanium aluminide alloy comprises from 0.10 to 1.25 at. % B, wherein the B is from Bminto Bmax, wherein Bmin and Bmax are calculated as:

Bmin (in at. %) = (15.4A1 - l7.6Cr - 2l.5Mo - l l. lNb - 6.9Ta - 25W - 527) / 405;

Bmax (in at. %) = (791 - 14.6A1 - 8 Cr - 8.5Mo - 5. lNb - 3.3Ta + 7.3W) / 102. Clause 7. The titanium aluminide alloy of any of the preceding clauses, wherein the titanium aluminide alloy realizes a non-equilibrium freezing range of from 120 to l90°C, wherein the non-equilibrium freezing range (in °C) is calculated as 4. lTi - 3.7A1 + 39.5Cr + 21.1Mo + l2. lNb + 19.8Ta + 18.4W - 34.4SL

Clause 8. The titanium aluminide alloy of any of the preceding clauses, wherein the titanium aluminide alloy realizes a hot cracking susceptibility of from 2600 to 5000°C, wherein the hot cracking susceptibility (in °C) is calculated as -246. lTi + 129.5A1 + 6483Cr + 1154Mo + 625Nb + 697Ta - 924W - 2251 Si.

Clause 9. A shape cast product made from the titanium aluminide alloy of any of clauses 1-8. Clause 10. The titanium aluminide alloy of any of clauses 1-8, wherein the titanium aluminide alloy is in the form of an aerospace component.

Clause 11. The aerospace component of clause 10, wherein the aerospace component is a turbine blade. Clause 12. An additive manufacturing feedstock comprising the titanium aluminide alloy of any of clauses 1-8.

Clause 13. The additive manufacturing feedstock of clause 12, wherein the additive manufacturing feedstock is a powder, a wire, a sheet and combinations thereof.

Clause 14. An additively manufactured product, wherein the additively manufactured product is produced from the powder of clause 13.

Clause 15. An additively manufactured product made from the titanium aluminide alloy of any of clauses 1-8.

Clause 16. The additively manufactured product of any of clauses 14-15, wherein the additively manufactured product realizes a tensile yield strength (TYS) at room temperature of at least 600 MPa, or at least 625 MPa, or at least 650 MPa, or at least 675 MPa, or at least 700 MPa, or at least 725 MPa.

Clause 17. The additively manufactured product of any of clauses 14-16, wherein the additively manufactured product realizes an ultimate tensile strength (UTS) at room temperature of at least 700 MPa, or at least 725 MPa, or at least 750 MPa, or at least 775 MPa, or at least 800 MPa, or at least 825 MPa, or at least 850 MPa, or at least 875 MPa. Clause 18. The additively manufactured product of any of clauses 14-17, wherein the additively manufactured product realizes an elongation at room temperature of at least 1.0%, or at least 1.25%, or at least 1.5%.

Clause 19. The additively manufactured product of any of clauses 14-18, wherein the additively manufactured product realizes a tensile yield strength (TYS) at 700°C of at least 450 MPa, or at least 475 MPa, or at least 500 MPa, or at least 525 MPa, or at least 550 MPa, or at least 575 MPa.

Clause 20. The additively manufactured product of any of clauses 14-19, wherein the additively manufactured product realizes an ultimate tensile strength (UTS) at 700°C of at least 650 MPa, or at least 675 MPa, or at least 700 MPa, or at least 725 MPa, or at least 750 MPa, or at least 775 MPa, or at least 790 MPa.

Clause 21. The additively manufactured product of any of clauses 14-20, wherein the additively manufactured product realizes an elongation at 700°C of at least 1.5%, or at least 1.75%, or at least 2.0%, or at least 2.25%, or at least 2.5%, or at least 2.75%, or at least 3.0%, or at least 3.25%, or at least 3.5%, or at least 3.75%, or at least 4.0%, or at least 4.25%, or at least 4.5%.

Clause 22. The additively manufactured product of any of clauses 14-21, wherein the additively manufactured product is in a thermally treated condition. Clause 23. A method comprising:

(a) heating the titanium aluminide alloy of any of clauses 1-8 above its liquidus temperature, thereby forming a liquid mixture;

(b) cooling the liquid mixture to below its solidus temperature thereby forming a solid material, wherein the cooling comprises first forming b phase crystals, and then forming titanium boride particles, and then forming a phase crystals.

Clause 24. The method of clause 23, wherein the heating step (a) comprises selectively heating a portion of a powder comprising the titanium aluminide alloy via at least one of a laser and an electron beam, thereby forming a molten pool;

wherein the molten pool comprises the liquid mixture; and

wherein the cooling step (b) comprises cooling the molten pool at a cooling rate of at least 10³ °C per second, or at least 10⁴ °C per second, or at least 10⁵ °C per second, or at least 10⁶ °C per second.

Clause 25. The method of clause 24, wherein the solid material is an additively manufactured product.

Clause 26. The method of any of clauses 23-25, comprising hot working the solid material. Clause 27. The method of any of clauses 23-26, comprising thermally treating the solid material.

Clause 28. The method of any of clauses 23-27, wherein the solid material is a rolled product. Clause 29. The method of any of clauses 23-28, wherein the solid material is a forged product.

Clause 30. The method of any of clauses 23-29, wherein the solid material is an extruded product.

Clause 31. The method of any of clauses 23-30, wherein the solid material is crack-free.

[0077] Other clauses based on any of the above paragraphs of the specification and the attached drawings are contemplated and apply to the present patent application.

[0078] While a number of embodiments of the present invention have been described, it is understood that these embodiments are illustrative only, and not restrictive, and that many modifications may become apparent to those of ordinary skill in the art. Further still, the various steps may be carried out in any desired order (and any desired steps may be added and/or any desired steps may be eliminated).

Claims

What is claimed is:

1. A titanium aluminide alloy comprising:

42.5 to 45.75 at. % Al;

1.75 to 4.2 at. % Nb;

0.8 to 1.55 at. % Cr;

at least one of:

(a) 0.10 to 1.25 at. % B; and

(b) 0.15 to 0.45 at. % Si;

up to 4.0 at. % Ta;

up to 0.75 at. % W; and

up to 0.55 at. % Mo;

the balance being titanium, optional incidental elements, and impurities.

2. The titanium aluminide alloy of claim 1, wherein the titanium aluminide alloy includes at least 0.1 at. % Ta.

3. The titanium aluminide alloy of claim 1, wherein the titanium aluminide alloy includes at least 0.1 at. % W.

4. The titanium aluminide alloy of claim 1, wherein the titanium aluminide alloy includes at least 0.1 at. % Mo.

5. The titanium aluminide alloy of claim 1, wherein the titanium aluminide alloy comprises both 0.10 to 1.25 at. % B and 0.15 to 0.45 at. % Si.

6. The titanium aluminide alloy of claim 1, wherein the titanium aluminide alloy comprises from 0.10 to 1.25 at. % B, wherein the B is from Bminto Bmax, wherein Bmin and Bmax are calculated as:

Bmax (in at. %) = (791 - 14.6A1 - 8TCr - 8.5Mo - 5. lNb - 3.3Ta + 7.3W) / 102.

7. The titanium aluminide alloy of claim 1, wherein the titanium aluminide alloy realizes a non-equilibrium freezing range of from 120 to l90°C, wherein the non-equilibrium freezing range (in °C) is calculated as 4TTi - 3.7A1 + 39.5Cr + 2l. lMo + l2. lNb + l9.8Ta + 18.4W - 34.4Si.

8. The titanium aluminide alloy of any of claims 1-7, wherein the titanium aluminide alloy realizes a hot cracking susceptibility of from 2600 to 5000°C, wherein the hot cracking susceptibility (in °C) is calculated as -246. lTi + 129.5A1 + 6483Cr + H54Mo + 625Nb + 697Ta - 924W - 2251 Si.

9. A shape cast product made from the titanium aluminide alloy of claim 1.

10. The titanium aluminide alloy of claim 1, wherein the titanium aluminide alloy is in the form of an aerospace component.

11. The aerospace component of claim 10, wherein the aerospace component is a turbine blade.

12. An additive manufacturing feedstock comprising the titanium aluminide alloy of claim 1.

13. The additive manufacturing feedstock of claim 12, wherein the additive manufacturing feedstock is a powder, a wire, a sheet and combinations thereof.

14. An additively manufactured product, wherein the additively manufactured product is produced from the powder of claim 13.

15. An additively manufactured product made from the titanium aluminide alloy of claim 1.

16. The additively manufactured product of any of claim 15, wherein the additively manufactured product realizes a tensile yield strength (TYS) at room temperature of at least 600 MPa, or at least 625 MPa, or at least 650 MPa, or at least 675 MPa, or at least 700 MPa, or at least 725 MPa.

17. The additively manufactured product of any of claim 15, wherein the additively manufactured product realizes an ultimate tensile strength (UTS) at room temperature of at least 700 MPa, or at least 725 MPa, or at least 750 MPa, or at least 775 MPa, or at least 800 MPa, or at least 825 MPa, or at least 850 MPa, or at least 875 MPa.

18. The additively manufactured product of any of claim 15, wherein the additively manufactured product realizes an elongation at room temperature of at least 1.0%, or at least 1.25%, or at least 1.5%.

19. The additively manufactured product of any of claim 15, wherein the additively manufactured product realizes a tensile yield strength (TYS) at 700°C of at least 450 MPa, or at least 475 MPa, or at least 500 MPa, or at least 525 MPa, or at least 550 MPa, or at least 575 MPa.

20. The additively manufactured product of any of claim 15, wherein the additively manufactured product realizes an ultimate tensile strength (UTS) at 700°C of at least 650 MPa, or at least 675 MPa, or at least 700 MPa, or at least 725 MPa, or at least 750 MPa, or at least 775 MPa, or at least 790 MPa.

21. The additively manufactured product of any of claim 15, wherein the additively manufactured product realizes an elongation at 700°C of at least 1.5%, or at least 1.75%, or at least 2.0%, or at least 2.25%, or at least 2.5%, or at least 2.75%, or at least 3.0%, or at least 3.25%, or at least 3.5%, or at least 3.75%, or at least 4.0%, or at least 4.25%, or at least 4.5%.

22. The additively manufactured product of any of claim 15, wherein the additively manufactured product is in a thermally treated condition.