WO2017123186A1 - Alliages à base de titane/aluminium ayant une meilleure résistance au fluage par renforcement de la phase gamma - Google Patents

Alliages à base de titane/aluminium ayant une meilleure résistance au fluage par renforcement de la phase gamma Download PDF

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WO2017123186A1
WO2017123186A1 PCT/US2016/012786 US2016012786W WO2017123186A1 WO 2017123186 A1 WO2017123186 A1 WO 2017123186A1 US 2016012786 W US2016012786 W US 2016012786W WO 2017123186 A1 WO2017123186 A1 WO 2017123186A1
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tial
alloy
based alloy
phase
alloys
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Judson Sloan Marte
JR. Michael Francis Xavier GIGLIOTTI
Pazhayannur Ramanathan Subramanian
Toshimitsu Tetsui
Voramon Supatarawanich DHEERADHADA
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National Institute for Materials Science
General Electric Co
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National Institute for Materials Science
General Electric Co
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C14/00—Alloys based on titanium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
    • C22F1/18—High-melting or refractory metals or alloys based thereon
    • C22F1/183—High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon

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  • the subject matter disclosed herein generally relates to a TiAl -based alloy, in particular, to a TiAl-based alloy suitable for use in high-temperature applications, for example, turbomachinery components such as gas turbine blades for aviation and power-generation. Specifically, the subject matter disclosed herein relates to a TiAl-based alloy having improved creep strength.
  • TiAl-based alloys a class of intermetallic alloys based on Ti and Al, have attracted much attention over the last several decades as novel light-weight high- temperature metallic materials, and have been the subject of intense research and development. As a result of such efforts, those alloys have been reduced to practice in recent years as components such as turbine last-stage blades of jet engines and/or turbine wheels in automotive turbochargers. As improvements in efficiency and fuel economy, as well as in CC reduction, are continuously sought in a wide variety of fields such as energy and transportation, there is a desire to expand the use of TiAl- based alloys which potentially contribute to such needs.
  • Improvement of creep strength of a TiAl-based alloy is typically achieved by adjustment of its composition and conditions for heat treatment to prepare a material substantially consisting of lamellar microstructures comprising layers of alpha2 (a2) phase (Ti3Al phase) and gamma ( ⁇ ) phase (TiAl phase).
  • the lamellar structure is formed during cooling process from elevated temperatures, and the phase transition process may be represented as follows: a ⁇ a + ⁇ a2 + ⁇ (1)
  • a TiAl-based alloy typically forms single phase at a high temperature around 1330°C or above depending on its composition, the material becomes single phase under a high temperature state such as high temperature heat treatment or immediately after casting.
  • a high temperature state such as high temperature heat treatment or immediately after casting.
  • gamma phase precipitates in the form of platelets (lamellae) within the alpha phase matrix, resulting in the formation of a lamellar structure comprising layers of alpha and gamma.
  • This alpha phase is eventually transformed into alpha2 phase. Therefore, grains of alpha phase present at high temperatures turn into grains of the lamellar microstructure (i.e., lamellar colonies) finally obtained.
  • the problem acknowledged herein is grain boundaries between alpha grains, i.e., interfaces between lamellar colonies in the final state.
  • gamma phase precipitates preferentially at grain boundaries between alpha grains during cooling.
  • the interface between the lamellar colonies is occupied by gamma phase extending in a thin planar form.
  • Alpha2 phase has a crystal structure of DO19, while gamma phase has a crystal structure of Llo, and hence the former structure is more complex. In consequence, alpha2 phase has greater high-temperature strength than gamma phase, although the former is more brittle.
  • model material as shown in FIG. 1 has lamellar colonies aligned along the longitudinal direction of the specimen, gamma phase present at the interface between lamellar colonies also extends longitudinally.
  • FIG. 2 shows a relationship between the direction of stress loaded on this type of specimen during the creep test and thin plate-like gamma phase present at the interface between lamellar colonies.
  • this gamma phase is subjected to tensile stress in a direction perpendicular to the plate thickness, but is hardly deformable in that direction because it is surrounded by lamellar structures of higher strength. Therefore, PST crystals as shown in FIG. 1 have been widely used as a test specimen in academic studies because creep mechanism can be analyzed while avoiding effects of relatively weak gamma phase.
  • FIG. 3 schematically illustrates a relationship between the direction of creep stress loaded during the high temperature use of a TiAl- based alloy having a fully lamellar structure manufactured by an industrial process and thin plate-like gamma phase at boundaries between lamellar colonies.
  • the present invention provides a TiAl-based alloy comprising: about 42.5 to about 45.5 atomic percent aluminum (Al); about 8.0 to about 15.0 atomic percent niobium (Nb); about 0.3 to about 0.8 atomic percent carbon (C); and about 0.3 to about 0.9 atomic percent silicon (Si).
  • the balance is titanium (Ti) and incidental impurities.
  • the present disclosure provides a method for producing an article comprising a step of casting a TiAl-based alloy having a composition as described above, as well as an article made from the TiAl-based alloy.
  • FIG. 1 is a perspective view of a model material obtained by directional solidification conventionally used in academic studies on creep mechanism of TiAl- based alloys (cited from Yamaguchi, M., et. al, Mat. Sci. Eng. A213 (1996) 25-31);
  • FIG. 2 is a schematic view showing a relationship between thin gamma phase at colony boundary of lamellar structure and the direction of stress loaded on a specimen as shown in FIG. 1 used for creep test;
  • FIG. 3 is a view showing a relationship between the direction of creep stress loaded during the high temperature use of a TiAl-based alloy having a fully lamellar structure manufactured by an industrial process and thin plate-like gamma phase present at boundaries between lamellar colonies;
  • FIG. 4 is a view showing an exemplary microstructure around the fracture position observed after the creep test of a TiAl-based alloy having a fully lamellar structure manufactured by an industrial process
  • FIG. 5 is a view of an exemplary microstructure of a TiAl-based alloy having a duplex structure
  • FIG. 6 is a view of a TiAl-based alloy ingot according to one embodiment
  • FIG. 7 shows a microstructure of a TiAl-based alloy (backscattered electron image; the same shall apply to the subsequent figures) of a composition of alloy 1 as a comparative example;
  • FIG. 8 shows a microstructure of a TiAl-based alloy of a composition of alloy
  • FIG. 9 shows a microstructure of a TiAl-based alloy of a composition of alloy
  • FIG. 10 shows a microstructure of a TiAl-based alloy of a composition of alloy
  • FIG. 11 shows a microstructure of a TiAl-based alloy of a composition of alloy
  • FIG. 12 shows a microstructure of a TiAl-based alloy of a composition of alloy
  • FIG. 13 shows a microstructure of a TiAl-based alloy of a composition of alloy
  • FIG. 14 shows a microstructure of a TiAl-based alloy of a composition of alloy
  • FIG. 15 shows a microstructure of a TiAl-based alloy of a composition of alloy
  • FIG. 16 shows a microstructure of a TiAl-based alloy of a composition of alloy
  • FIG. 17 shows a microstructure of a TiAl-based alloy of a composition of alloy
  • FIG. 18 shows a microstructure of a TiAl-based alloy of a composition of alloy
  • FIG. 19 shows a microstructure of a TiAl-based alloy of a composition of alloy
  • FIG. 20 shows a microstructure of a TiAl-based alloy of a composition of alloy
  • FIG. 21 shows a microstructure of a TiAl-based alloy of a composition of alloy
  • FIG. 22 shows a microstructure of a TiAl-based alloy of a composition of alloy
  • FIG. 23 shows a microstructure of a TiAl-based alloy of a composition of alloy
  • FIG. 24 shows a microstructure of a TiAl-based alloy of a composition of alloy 18 according to the present disclosure
  • FIG. 25 shows a microstructure of a TiAl-based alloy of a composition of alloy
  • FIG. 26 shows a microstructure of a TiAl-based alloy of a composition of alloy
  • FIG. 27 shows a microstructure of a TiAl-based alloy of a composition of alloy
  • FIG. 28 shows a microstructure of a TiAl-based alloy of a composition of alloy
  • FIG. 4 illustrates a microstructure around the fracture position observed after the creep test on this type of TiAl-based alloy. As can be seen, cracks are observed only at boundary gamma phase oriented perpendicular to the direction of stress loaded during the creep test. No cracks are found within the lamellar structure. This indicates that, in order to improve the creep strength of industrial TiAl-based alloys, it is necessary to strengthen not only the interior lamellar structure, but also the thin plate-like gamma phase at lamellar colony boundary.
  • FIG. 5 shows an exemplary microstructure of the duplex structure.
  • the duplex structure includes both equiaxed gamma grains and lamellar structures, and exhibits greater room temperature ductility as compared with the fully lamellar structure, due to finer microstructure as a whole, and also because of increased proportion of gamma phase which is more ductile than alpha2 phase.
  • the crystal structure of gamma phase is a Llo structure based on fee. Since it is intermetallic phase, Ti and Al atoms are located at specific lattice positions, rather than random arrangement of atoms in a crystal. Thus, unlike fee, the ratio of lattice constants of c-axis and a-axis ("c/a") is not equal to 1, and is characterized by somewhat larger c-axis.
  • gamma phase of Ti50:A150 atomic percent (%) has a slightly distorted lattice with a c/a ratio of about 1.02.
  • the present inventors have envisaged that if the c/a ratio of gamma phase is further increased the lattice can be further distorted, which affects to hinder movement of dislocation during creep deformation, making the gamma phase more resistant against creep deformation. It is also believed that this approach can be effectively utilized to improve the creep strength of the material through the improvement of strength of boundary gamma phase, because the gamma phase at the lamellar colony boundary is a key factor that dominates the material creep strength even for those materials solely comprising a fully lamellar structure which itself is advantageous for improvement of the creep strength, as described above.
  • Silicon (Si) is an additive for precipitation strengthening of TiAl-based alloys, and is typically used in a range of 0.1 -0.7 wt.% (JP 2008-184665A); 0.1 -0.4 at.% (JP 2000-199025A); 0.2-0.5 at.% (JP H10-130756A); 0.1-0.2 wt.% (JP H09-176764A); and 0.1-2 wt.% (JP H07-252562A). Although the volume fraction of precipitates may be increased depending on the amount of Si to be added, excess addition may cause coarsening of the precipitates, leading to an unfavorable reduction in the creep strength or embrittlement.
  • the TiAl-based alloy has a composition:
  • Al about 42.5-45.5 at.%
  • Nb about 8.0-15.0 at.%
  • the TiAl-based alloy may comprise Nb in a range of from about 9.0 atomic percent to about 11.0 at.%. In another embodiment, the TiAl-based alloy may comprise Nb in a range of about 9.3 at.% to about 11.0 at.%.
  • the TiAl-based alloy may further comprise at least one element selected from the group consisting of W, Zr, and Ta, in a total amount up to about 3.0 at.%.
  • W, Zr, and Ta may be added to further improve the creep strength by enhanced strengthening of gamma phase.
  • the present disclosure provides a method for producing an article comprising a step of casting a TiAl-based alloy having a composition as described above, as well as an article made from the TiAl-based alloy
  • a variety of articles including turbine blades, may be prepared by melting and casting a TiAl-based alloy having a composition as described above.
  • the method of producing an article may comprise a postprocessing step after casting a TiAl-based alloy.
  • a post-processing may include heat treatment and/or forging.
  • the post-casting heat treatment of the TiAl-based alloy may comprise holding the as-cast article at a high temperature.
  • the high-temperature holding may be conducted at a temperature for a period of time sufficient to make the entire material into a single phase region.
  • the cast article may be maintained at a temperature of about 1280°C or above, and more particularly, 1300°C or above, such as 1310-1390°C, for at least one hour, such as about 1-10 hours.
  • a material having a single alpha phase thus obtained may be subjected to controlled cooling regime.
  • the cooling condition may be suitably adjusted depending on a particular alloy composition so as to cause a desired level of gamma precipitation through transformation such as a ⁇ a + ⁇ a2 + ⁇ , to obtain a desired microstructure (for example, a fully lamellar structure, a duplex structure, or the like).
  • alloy microstructure may comprise up to about 20 at.% of primary gamma TiAl.
  • the material may be allowed to cool in a same furnace used for the high-temperature holding, without removing it from the furnace, or may be removed from the furnace and cooled under the controlled cooling regime. Alternatively, the material may be subjected to quenching.
  • the post processing step may comprise forging.
  • the alloy may be preheated to a high temperature, for example, to such a temperature range that the alloy comprises 5% or more beta phase.
  • the preheat temperature is on the order of 1300-1350°C.
  • the forging step may be carried out by placing a TiAl- based alloy onto forging dies.
  • the dies may be lubricated.
  • a glass sheet may be used as a lubricant, in which case the glass also acts as a thermal barrier during the initial portion of the forging operation.
  • the dies may be heated to minimize transfer of heat from the alloy to the dies. In one embodiment, the dies may be heated to about 900°C for this purpose.
  • the forging operation may be carried out by applying load to a TiAl-based alloy while the alloy is hot at a low strain-rate.
  • forging may be carried out at a constant strain-rate of about 0.6 in/in/min (10 "2 s "1 ) to strain of 50%. Then, the alloy may be allowed to air cool.
  • the article may be used in a wide variety of applications including, for example, various components in turbomachinery, such as turbine blades, compressor blades, seals, and other components within industrial gas turbines for power generation; low pressure turbine blades, high pressure compressor blades, shrouds, and seals within aircraft engines for propulsion and auxiliary power generation; impellers, radial compressors, and turbine wheels within turbochargers for diesel and gasoline reciprocating engines; and any other application that can benefit from use of the high- temperature light-weight materials with improved creep strength.
  • various components in turbomachinery such as turbine blades, compressor blades, seals, and other components within industrial gas turbines for power generation
  • impellers, radial compressors, and turbine wheels within turbochargers for diesel and gasoline reciprocating engines and any other application that can benefit from use of the high- temperature light-weight materials with improved creep strength.
  • Aluminum is an essential element constituting a TiAl-based alloy, and it was long considered that an Al level for a traditional TiAl-based alloy is suitably around 46 at.%.
  • the Al content affects the proportion of gamma phase to alpha2 phase in the lamellar structure. As it deceases the proportion of alpha2 phase increases, while the proportion of gamma phase increases as the Al content increases.
  • the Al level also affects the c/a ratio of gamma phase, such that a higher Al content results in a greater c/a.
  • niobium (Nb) basically substitutes for Ti
  • a portion of Nb also substitutes for Al. The addition of Nb appears to have similar effects to some increase in the Al level, and therefore the Al level should be reduced when a large amount of Nb is to be added.
  • the Al content has complicated effects on the structure of the TiAl-based alloy as well as the lattice of gamma phase.
  • the present inventors identified a range of 42.5-45.5 at.% Al to be suitable for improvement of creep strength.
  • the Al content at a level of 46 at.% provides a sufficient proportion of alpha2 phase in the lamellar structure for a conventional TiAl-based alloy.
  • a suitable Al content is somewhat lower than the conventional TiAl-based alloy, because the addition of a large amount of Nb appears to have similar effects to some increase in the Al level, as described hereinbefore.
  • the c/a ratio of gamma phase tends to become too small to achieve a sufficient level of creep strength by strengthening of gamma phase.
  • the creep strength can decrease in association with an undesirably increased proportion of gamma phase and correspondingly decreased proportion of alpha2 phase in the lamellar structure.
  • Niobium at a range of 8.0-15.0 at.% strengthens gamma phase through an increased c/a ratio of gamma phase, and can significantly improve the creep strength of a TiAl-based alloy regardless of its microstructural morphology.
  • Nb content at a level of less than 8 at.% a certain degree of enhancement in the creep strength may be observed as in the prior art, but is still insufficient to achieve a higher level of creep strength as described herein.
  • Niobium content greater than 15 at.% is generally undesirable, as it tends to decrease the creep strength due to formation of beta ( ⁇ ) or other detrimental phases, some of which arise as a result of other alloying elements and heat treatment conditions.
  • beta ( ⁇ ) phase is an intermetallic phase in B2 structure which is a derivative of bcc structure, and is characterized by poor high-temperature strength.
  • Niobium is a beta-stabilizing element for TiAl-based alloys. Excess Nb may cause formation of beta phase, even though such an effect is small for a unit amount of the additive.
  • Niobium is about ten times more expensive than the other elements in the alloy, and also increases the density of TiAl-based alloy. For these reasons, it may be advantageous to limit the amount of Nb. By taking all these effects, such as enhanced creep strength, and increased cost and specific gravity, associated with the Nb addition into consideration, the Nb content may be chosen in a range of 9.0-11.0 at.% in one embodiment, or in a range of 9.3-11.0 at.% in another embodiment.
  • Carbon is an interstitial solid solution element for strengthening gamma phase, thus leading to further strengthening of gamma phase in addition to strengthening by Nb.
  • the carbon content may be suitably in a range of 0.3-0.8 at.%. With the C content at a level of less than 0.3 at.%, a certain degree of enhancement in the creep strength may be observed, but is still insufficient to achieve a higher level of creep strength. Carbon content greater than 0.8 at.% may cause formation of detrimental carbides such as T12AIC beyond the solid solubility limit, although depending on other alloying elements and heat treatment conditions, which may lead to undesirably decreased creep strength.
  • silicon is added for precipitation strengthening of the whole structure.
  • Most of the Si addition precipitates as fine Ti5Si3 particles, which leads to enhanced creep strength.
  • the Si content may be suitably in a range of 0.3-0.9 at.%. With the Si content at a level of less than 0.3 at.%, a certain degree of enhancement in the creep strength may be observed as in the prior art, but is still insufficient to achieve a higher level of creep strength.
  • the Si content at a level of greater than 0.9 at.% may cause coarsening or excess precipitation of T15S13, although depending on other alloying elementsand heat treatment conditions, which may lead to undesirably decreased creep strength.
  • Optional elements W. Zr. Ta. Cr
  • Tungsten (W), zirconium (Zr) and tantalum (Ta) are elements which can contribute to further enhancement of the creep strength through additional strengthening of gamma phase, and may optionally be added alone or in any combination. In general, one or more of these element may be added in a total amount up to 3.0 at.%. The creep strength may be undesirably decreased at a level of greater than 3.0 at.%, due to formation of beta or other detrimental phases, although depending on other alloying elements and heat treatment conditions.
  • Chromium (Cr) may be added in an amount up to 0.5 at.%. Excess Cr may cause formation of beta phase, leading to undesirably decreased creep strength.
  • the TiAl-based alloy as disclosed herein shows a creep strength that is substantially higher as compared with conventional TiAl-based alloys. Accordingly, the TiAl-based alloy as disclosed herein may be advantageously used for a variety of components in various machineries in energy or transportation fields, including those components for which conventional TiAl-based alloys could not be used: for example, turbine blades in a higher temperature section in power generation gas turbines and/or aviation jet engines, and turbine wheels in automotive turbochargers operated at higher temperatures, whereby further improvement of efficiency and fuel economy, and CC reduction may be achieved.
  • a number of ingots were made from TiAl-based alloys with different compositions as shown in Table 1 by a high-frequency induction melting process using an yttria crucible.
  • Raw materials used for melting were: Ti sponge, Al pellets, and small Nb flakes with a thickness of about 0.5 mm, for Ti, Al and Nb, which were major elements in the alloys; and small particles for Si, Cr, W, Zr, and Ta. Carbon was added as TiC powder.
  • FIG. 6 shows an exemplary photograph showing appearance of a TiAl-based alloy ingot thus obtained.
  • the dimensions of the ingot were 40 mm diameter ( ⁇ ) ⁇ 100 mm, excluding a riser portion.
  • the weight was about 800 gram in the as-cast state, from which the riser portion was cut off to give about 450 g.
  • properties of a TiAl-based alloy depend not only on its particular composition, but also on its particular microstructural morphology.
  • creep strengths were compared in microstructural morphologies that were as similar as possible to each other so that predominantly the effects of varying compositions could be evaluated.
  • the target microstructural morphology was a fully lamellar structure which is advantageous for improvement of creep strength, and heat treatment conditions were adjusted for each alloy so as to make the resulting microstructures as similar as possible to each other. It should be noted that similar effects of alloy composition on creep strength are expected for other microstructural morphologies than the fully lamellar structure, although some decrease in the absolute values of creep strength may be observed.
  • ingots, from which a riser portion was cut off were subj ected to the heat treatments as shown in Table 1. These conditions were chosen for each alloy based on the results of preliminary conducted heat-treatment tests. In the preliminary conducted heat-treatment tests, a number of test specimens were cut from the ingot of each alloy and were subjected to various heat treatment conditions, and optimal condition for achieving a lamellar structure was chosen based on microstructural examination of cross section of the heat-treated samples. The microstructure examination was conducted by scanning electron microscopy in the backscattered electron imaging mode.
  • the heat treatment conditions shown in Table 1 basically include steps of: holding at a high temperature; controlled cooling, and holding at a relatively lower temperature. Each of these steps was conducted for the following purpose:
  • the holding time during the high-temperature heat treatment may be optimized to prevent coarsening of grains, resulting in a colony size that is not too coarse.
  • the cooling rate may be optimized to obtain a microstructure having a suitable proportion of alpha2 and gamma phases in the lamellar structure.
  • Microstructural examination and creep rupture test were conducted for each of the alloy ingots after the heat treatments. Creep rupture test was conducted at 870°C x 225MPa using a specimen with 4 mm diameter at parallel portion. The microstructure examination was conducted by scanning electron microscopy in the backscattered electron imaging mode. In the creep rupture test, creep strengths were compared between alloys based on creep rupture time.
  • Alloy 1 is a comparative alloy, and its microstructure in a backscattered electron image (hereinafter the same) is shown in FIG. 7. Alloy 1 is based on a chemical composition disclosed in JP 2008- 184665 A. The microstructure was a fully lamellar structure advantageous for improvement of creep strength, as intended. The creep rupture time at 870°C ⁇ 225MPa was 36 hours, which is better than a TiAl-based alloy free of Si or C, but is still insufficient for applications where higher level of creep strength is required.
  • Alloy 2 is a comparative alloy, and its microstructure is shown in FIG. 8. Alloy 2 contained 0.6 at.% Cr beyond the compositional range according to the invention. Beta phase, which is seen in white, was present at interfaces between lamellar structures. Small white particles dispersed are Ti5Si3 precipitates formed due to the addition of Si.
  • Nb is a weak beta-stabilizing element for TiAl-based alloys, but an excess amount of Nb tends to cause formation of beta phase.
  • Cr is a very strong beta-stabilizing element. It appears that the addition of 0.6 at.% Cr caused formation of beta phase, even for such an alloy composition as disclosed herein in which beta formation is normally absent.
  • the creep rupture time of Alloy 2 is shorter than the alloys according to the invention due to inferior high- temperature strength of beta phase.
  • Alloys 3-6 are alloys according to the invention, and their respective microstructures are shown in FIGS. 9-12. These alloys had different Al contents within the compositional range according to the invention. All of these alloys had a microstructure of lamellar structure, and showed a very long creep rupture time due to sufficient enhancement of gamma-phase strength.
  • Alloy 7 is a comparative alloy, and its microstructure is shown in FIG. 13. Alloy 7 represents a comparative alloy with a higher Al content outside the compositional range according to the invention. It had an excessive proportion of gamma phase (dark phase) with a reduced proportion of alpha2 phase (light phase) in the lamellar structure, resulting in a shorter creep rupture time than the alloys according to the invention.
  • Alloy 8 is a comparative alloy, and its microstructure is shown in FIG. 14. Alloy 8 represents a comparative alloy with a lower Nb content outside the compositional range according to the invention. Even though it had a microstructure of fully lamellar structure as intended, its creep rupture time was than the alloys according to the invention due to insufficient addition of Nb to strengthen gamma phase.
  • Alloys 9 and 10 are alloys according to the invention, and their respective microstructures are shown in FIGS. 15 & 16. Alloys 9 and 10 had different Nb contents within the compositional range according to the invention. Both alloys had a microstructure of fully lamellar structure as intended, and showed a very long creep rupture time due to sufficient enhancement of gamma-phase strength.
  • Alloy 11 is a comparative alloy, and its microstructure is shown in FIG. 17. Alloy 11 represents a comparative alloy with a higher Nb content outside the compositional range according to the invention. A beta phase, seen in white, was observed at a boundary between lamellar colonies. While Nb is a relatively weak beta-phase stabilizing element for TiAl-based alloys, as described hereinbefore, it appears that the addition of excess amount of Nb caused the formation of beta phase. The creep rupture time of Alloy 11 is shorter than the alloys according to the invention due to inferior high-temperature strength of beta phase.
  • Alloys 12-14 are alloys according to the invention, and their respective microstructures are shown in FIGS. 18-20. Alloys 12-14 had different C contents within the compositional range according to the invention. These alloys had a microstructure of lamellar structure, and showed a very long creep rupture time due to sufficient enhancement of gamma-phase strength.
  • Alloy 15 is a comparative alloy, and its microstructure is shown in FIG. 21. Alloy 15 represents a comparative alloy with a higher C content outside the compositional range according to the invention. Because of excess C content beyond the solid solubility limit, formation of coarse carbide (T12AIC) was observed. The creep rupture time was therefore shorter than the alloys according to the invention.
  • Alloys 16-18 are alloys according to the invention, and their respective microstructures are shown in FIGS. 22-24. Alloys 16-18 had different Si contents within the compositional range according to the invention. These alloys had a microstructure of lamellar structure, and showed a very long creep rupture time due to sufficient strengthening of the entire structure by precipitates and enhancement of gamma-phase strength.
  • Alloy 19 is a comparative alloy, and its microstructure is shown in FIG. 25. Alloy 19 represents a comparative alloy with a higher Si content outside the compositional range according to the invention. The creep rupture time was shorter than the alloys according to the invention because a large amount of coarse silicide (Ti5Si3) was formed.
  • Alloys 20-22 are alloys according to the invention, and their respective microstructures are shown in FIGS. 26-28. Alloys 20, 21 and 23 respectively included addition of 0.75 at.% W, 1.5 at.% Zr, and 1.5 at.% Ta. All of these alloys had a fully lamellar structure similar to those of alloys without such an additional element, and showed further increased creep rupture time by an enhancement of gamma-phase strength by these elements.
  • TiAl-based alloys of the present invention encompass modifications of the proportion in composition within the scope obvious to those skilled in the art, for example, modifications of the composition within the allowable range necessarily involved in manufacture and/or those within the allowable range according to fluctuations of the purchase price of the base compositions or variance of supply conditions.
  • the TiAl-based alloy as disclosed herein may be suitably used in components operated at higher temperature as compared with those for which conventional TiAl-based alloys have been used.
  • the TiAl-based alloy as disclosed herein may be suitably used as various components in turbomachinery, for example, turbine blades, compressor blades, seals, and other components within industrial gas turbines for power generation; low pressure turbine blades, high pressure compressor blades, shrouds, and seals within aircraft engines for propulsion and auxiliary power generation; impellers, radial compressors, and turbine wheels within turbochargers for diesel and gasoline reciprocating engines.
  • the TiAl-based alloy as disclosed herein can be advantageously used for a high-temperature component in power generation gas turbines and/or aviation jet engines with a reduced weight or a larger component size, for which conventional TiAl-based alloys could not be used, whereby contributing to a further reduction of carbon dioxide emission and fuel consumption through improvement of energy efficiency.

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Abstract

Cette invention concerne un alliage à base de TiAl ayant une excellente résistance au fluage à haute température. Selon un mode de réalisation, l'alliage à base de TiAl comprend, en pourcentage atomique, d'environ 42,5 à environ 45,5 % d'aluminium (Al), d'environ 8,0 à environ 15,0 % de niobium (Nb), d'environ 0,3 à environ 0,8 % de carbone (C), et d'environ 0,3 à environ 0,9 % de silicium (Si), le reste étant du titane (Ti) et les inévitables impuretés. L'invention concerne en outre un procédé de fabrication d'un article, comprenant l'étape de coulage de l'alliage à base de TiAl, et un article fabriqué à partir de l'alliage à base de TiAl.
PCT/US2016/012786 2016-01-11 2016-01-11 Alliages à base de titane/aluminium ayant une meilleure résistance au fluage par renforcement de la phase gamma Ceased WO2017123186A1 (fr)

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111647771A (zh) * 2020-04-17 2020-09-11 中国航发北京航空材料研究院 一种多元素复合抗氧化Ti2AlNb合金及其制备方法
CN116516213A (zh) * 2023-03-23 2023-08-01 北京科技大学 一种含Si高Nb-TiAl合金的制备方法
CN116516212A (zh) * 2023-03-23 2023-08-01 北京科技大学 一种高温高强的高Nb-TiAl合金的制备方法
CN117089790A (zh) * 2023-09-07 2023-11-21 哈尔滨工业大学 一种具有细小全片层结构的高铌TiAl合金的蠕变成形/短时热处理复合制备方法

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH07252562A (ja) 1994-03-17 1995-10-03 Nissan Motor Co Ltd Ｔｉ−Ａｌ系軽量耐熱部材およびその製造方法
JPH09176764A (ja) 1995-12-25 1997-07-08 Mitsubishi Heavy Ind Ltd ＴｉＡｌ系金属間化合物基合金
JPH10130756A (ja) 1996-10-28 1998-05-19 Mitsubishi Heavy Ind Ltd ＴｉＡｌ金属間化合物基合金
JP2000199025A (ja) 1999-01-05 2000-07-18 Mitsubishi Heavy Ind Ltd ＴｉＡｌ系金属間化合物基合金およびその製造方法、タ―ビン部材およびその製造方法
JP2008184665A (ja) 2007-01-30 2008-08-14 Daido Steel Co Ltd 高温クリープ特性に優れたＴｉＡｌ合金及びその製造方法
WO2015182454A1 (fr) * 2014-05-28 2015-12-03 国立研究開発法人物質・材料研究機構 ALLIAGE DE MOULAGE À BASE DE TiAl ET SON PROCÉDÉ DE PRODUCTION
EP3012337A1 (fr) * 2013-06-19 2016-04-27 National Institute for Materials Science Alliage à base de ti-al forgé à chaud et son procédé de production

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH07252562A (ja) 1994-03-17 1995-10-03 Nissan Motor Co Ltd Ｔｉ−Ａｌ系軽量耐熱部材およびその製造方法
JPH09176764A (ja) 1995-12-25 1997-07-08 Mitsubishi Heavy Ind Ltd ＴｉＡｌ系金属間化合物基合金
JPH10130756A (ja) 1996-10-28 1998-05-19 Mitsubishi Heavy Ind Ltd ＴｉＡｌ金属間化合物基合金
JP2000199025A (ja) 1999-01-05 2000-07-18 Mitsubishi Heavy Ind Ltd ＴｉＡｌ系金属間化合物基合金およびその製造方法、タ―ビン部材およびその製造方法
JP2008184665A (ja) 2007-01-30 2008-08-14 Daido Steel Co Ltd 高温クリープ特性に優れたＴｉＡｌ合金及びその製造方法
EP3012337A1 (fr) * 2013-06-19 2016-04-27 National Institute for Materials Science Alliage à base de ti-al forgé à chaud et son procédé de production
WO2015182454A1 (fr) * 2014-05-28 2015-12-03 国立研究開発法人物質・材料研究機構 ALLIAGE DE MOULAGE À BASE DE TiAl ET SON PROCÉDÉ DE PRODUCTION

Non-Patent Citations (8)

* Cited by examiner, † Cited by third party
Title
ASAI, T., MAT. SCI. ENG., vol. A329-331, 2002, pages 828 - 834
H.N. LEE: "Intermetallics", vol. 10, 2002, ELSEVIER, article "Directional solidification and creep deformation of a Ti-46A1-1.5Mo-0.2C (at.%) alloy", pages: 841 - 850
K. MARUYAMA: "Intermetallics", vol. 13, 2005, ELSEVIER, article "Effects of a 2 spacing on creep deformation characteristics of hard oriented PST crystals of TiAl-based alloy", pages: 1116 - 1121
LEE, H.N., INTERMETALLICS, vol. 10, 2002, pages 841 - 850
M. YAMAGUCHI: "Materials Science and Engineering", vol. A213, 1996, ELSEVIER, article "Recent progress in our understanding of deformation and fracture of two-phase and single-phase TiAl alloys", pages: 25 - 31
MARUYAMA, K., INTERMETALLICS, vol. 13, 2005, pages 1116 - 1121
TETSUYA ASAI: "Materials Science and Engineering", vol. A329-331, 2002, ELSEVIER, article "Microstructure in Ti-48at.%Al PST crystal subjected to creep deformation", pages: 828 - 834
YAMAGUCHI, M., MAT. SCI. ENG., vol. A213, 1996, pages 25 - 31

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111647771A (zh) * 2020-04-17 2020-09-11 中国航发北京航空材料研究院 一种多元素复合抗氧化Ti2AlNb合金及其制备方法
CN111647771B (zh) * 2020-04-17 2021-10-15 中国航发北京航空材料研究院 一种多元素复合抗氧化Ti2AlNb合金及其制备方法
CN116516213A (zh) * 2023-03-23 2023-08-01 北京科技大学 一种含Si高Nb-TiAl合金的制备方法
CN116516212A (zh) * 2023-03-23 2023-08-01 北京科技大学 一种高温高强的高Nb-TiAl合金的制备方法
CN116516213B (zh) * 2023-03-23 2024-06-07 北京科技大学 一种含Si高Nb-TiAl合金的制备方法
CN117089790A (zh) * 2023-09-07 2023-11-21 哈尔滨工业大学 一种具有细小全片层结构的高铌TiAl合金的蠕变成形/短时热处理复合制备方法

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