CN1292038A - Two phase titanium aluminide alloy - Google Patents
Two phase titanium aluminide alloy Download PDFInfo
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- CN1292038A CN1292038A CN99803452A CN99803452A CN1292038A CN 1292038 A CN1292038 A CN 1292038A CN 99803452 A CN99803452 A CN 99803452A CN 99803452 A CN99803452 A CN 99803452A CN 1292038 A CN1292038 A CN 1292038A
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- 239000000956 alloy Substances 0.000 title claims abstract description 120
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 120
- OQPDWFJSZHWILH-UHFFFAOYSA-N [Al].[Al].[Al].[Ti] Chemical compound [Al].[Al].[Al].[Ti] OQPDWFJSZHWILH-UHFFFAOYSA-N 0.000 title claims abstract description 33
- 229910021324 titanium aluminide Inorganic materials 0.000 title claims abstract description 33
- 239000010936 titanium Substances 0.000 claims abstract description 20
- 239000002245 particle Substances 0.000 claims abstract description 14
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 8
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 7
- 229910052750 molybdenum Inorganic materials 0.000 claims abstract description 7
- 229910052758 niobium Inorganic materials 0.000 claims abstract description 7
- 229910052748 manganese Inorganic materials 0.000 claims abstract description 5
- 229910052720 vanadium Inorganic materials 0.000 claims abstract description 5
- 229910052802 copper Inorganic materials 0.000 claims abstract description 3
- 238000001192 hot extrusion Methods 0.000 claims description 41
- 229910010038 TiAl Inorganic materials 0.000 claims description 25
- 239000013078 crystal Substances 0.000 claims description 11
- 238000010438 heat treatment Methods 0.000 claims description 10
- 239000004411 aluminium Substances 0.000 claims description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 4
- 239000010949 copper Substances 0.000 claims description 2
- 229910052759 nickel Inorganic materials 0.000 claims 1
- 238000009828 non-uniform distribution Methods 0.000 claims 1
- 238000005482 strain hardening Methods 0.000 claims 1
- 229910052719 titanium Inorganic materials 0.000 abstract description 10
- 229910052721 tungsten Inorganic materials 0.000 abstract description 9
- 238000005275 alloying Methods 0.000 abstract description 8
- 238000007792 addition Methods 0.000 abstract description 4
- 239000010419 fine particle Substances 0.000 abstract description 2
- 239000000523 sample Substances 0.000 description 30
- 239000000463 material Substances 0.000 description 24
- 238000000137 annealing Methods 0.000 description 23
- 239000000203 mixture Substances 0.000 description 16
- 238000007669 thermal treatment Methods 0.000 description 15
- 238000000034 method Methods 0.000 description 9
- 230000003287 optical effect Effects 0.000 description 7
- 238000012360 testing method Methods 0.000 description 7
- 150000001875 compounds Chemical class 0.000 description 6
- 238000001125 extrusion Methods 0.000 description 6
- 229910000765 intermetallic Inorganic materials 0.000 description 6
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 5
- 230000003078 antioxidant effect Effects 0.000 description 5
- 238000005266 casting Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 5
- 229910052751 metal Inorganic materials 0.000 description 5
- 230000008859 change Effects 0.000 description 4
- 238000007712 rapid solidification Methods 0.000 description 4
- 239000002131 composite material Substances 0.000 description 3
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- 238000004453 electron probe microanalysis Methods 0.000 description 3
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- 239000011159 matrix material Substances 0.000 description 3
- 230000003647 oxidation Effects 0.000 description 3
- 238000007254 oxidation reaction Methods 0.000 description 3
- 239000000126 substance Substances 0.000 description 3
- 229910000951 Aluminide Inorganic materials 0.000 description 2
- 239000000654 additive Substances 0.000 description 2
- 230000000996 additive effect Effects 0.000 description 2
- 229910000905 alloy phase Inorganic materials 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 2
- 239000003963 antioxidant agent Substances 0.000 description 2
- 235000006708 antioxidants Nutrition 0.000 description 2
- 238000005452 bending Methods 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 235000019504 cigarettes Nutrition 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- 238000004663 powder metallurgy Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 229910002058 ternary alloy Inorganic materials 0.000 description 2
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 2
- 239000010937 tungsten Substances 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 235000008733 Citrus aurantifolia Nutrition 0.000 description 1
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 240000008168 Ficus benjamina Species 0.000 description 1
- 229910016006 MoSi Inorganic materials 0.000 description 1
- 208000037656 Respiratory Sounds Diseases 0.000 description 1
- 241000282887 Suidae Species 0.000 description 1
- 229910004349 Ti-Al Inorganic materials 0.000 description 1
- 235000011941 Tilia x europaea Nutrition 0.000 description 1
- 229910004692 Ti—Al Inorganic materials 0.000 description 1
- 241000863032 Trieres Species 0.000 description 1
- UJXVAJQDLVNWPS-UHFFFAOYSA-N [Al].[Al].[Al].[Fe] Chemical compound [Al].[Al].[Al].[Fe] UJXVAJQDLVNWPS-UHFFFAOYSA-N 0.000 description 1
- 238000005054 agglomeration Methods 0.000 description 1
- 230000002776 aggregation Effects 0.000 description 1
- UQZIWOQVLUASCR-UHFFFAOYSA-N alumane;titanium Chemical compound [AlH3].[Ti] UQZIWOQVLUASCR-UHFFFAOYSA-N 0.000 description 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- 230000006399 behavior Effects 0.000 description 1
- 230000003197 catalytic effect Effects 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 239000003250 coal slurry Substances 0.000 description 1
- 239000011280 coal tar Substances 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000005097 cold rolling Methods 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000005034 decoration Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 239000012777 electrically insulating material Substances 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 229910052735 hafnium Inorganic materials 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000004615 ingredient Substances 0.000 description 1
- 239000001995 intermetallic alloy Substances 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- XEEYBQQBJWHFJM-UHFFFAOYSA-N iron Substances [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 1
- 229910021326 iron aluminide Inorganic materials 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 239000004571 lime Substances 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 150000002736 metal compounds Chemical class 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 150000004767 nitrides Chemical class 0.000 description 1
- 230000006911 nucleation Effects 0.000 description 1
- 238000010899 nucleation Methods 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
- 238000007750 plasma spraying Methods 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 238000005204 segregation Methods 0.000 description 1
- 230000000391 smoking effect Effects 0.000 description 1
- BNHGKKNINBGEQL-UHFFFAOYSA-M sodium;5-ethyl-5-(3-methylbutyl)pyrimidin-3-ide-2,4,6-trione Chemical compound [Na+].CC(C)CCC1(CC)C(=O)NC(=O)[N-]C1=O BNHGKKNINBGEQL-UHFFFAOYSA-M 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 229910052723 transition metal Inorganic materials 0.000 description 1
- 150000003624 transition metals Chemical class 0.000 description 1
- 238000009827 uniform distribution Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
- 229910052726 zirconium Inorganic materials 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/23—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces involving a self-propagating high-temperature synthesis or reaction sintering step
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/04—Making non-ferrous alloys by powder metallurgy
- C22C1/045—Alloys based on refractory metals
- C22C1/0458—Alloys based on titanium, zirconium or hafnium
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/04—Making non-ferrous alloys by powder metallurgy
- C22C1/047—Making non-ferrous alloys by powder metallurgy comprising intermetallic compounds
-
- 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
- C22C—ALLOYS
- C22C29/00—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides
- C22C29/005—Alloys based on carbides, oxides, nitrides, borides, or silicides, e.g. cermets, or other metal compounds, e.g. oxynitrides, sulfides comprising a particular metallic binder
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
- B22F2998/10—Processes characterised by the sequence of their steps
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- Manufacturing & Machinery (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Powder Metallurgy (AREA)
- Extrusion Of Metal (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Superconductors And Manufacturing Methods Therefor (AREA)
- Physical Vapour Deposition (AREA)
- Transition And Organic Metals Composition Catalysts For Addition Polymerization (AREA)
- Laminated Bodies (AREA)
Abstract
A two phase titanium aluminide alloy having a lamellar microstructure with little intercolony structures. The alloy can include fine particles such as boride particles at colony boundaries and/or grain boundary equiaxed structures. The alloy can include alloying additions such as <= 10 at % W, Nb and/or Mo. The alloy can be free of Cr, V, Mn, Cu and/or Ni and can include, in atomic %, 45 to 55 % Ti, 40 to 50 % Al, 1 to 5 % Nb, 0.3 to 2 % W, up to 1 % Mo and 0.1 to 0.3 % B. In weight %, the alloy can include 57 to 60 % Ti, 30 to 32 % Al, 4 to 9 % Nb, up to 2 % Mo, 2 to 8 % W and 0.02 to 0.08 % B.
Description
Technical field
The present invention relates to two-phase titanium aluminide (titanium aluminide) alloy composite, it can be used for resistive heating and other purposes, as is used for structural applications.
Background technology
Titanium aluminide alloy is the theme of many parts of patents and open source literature, and this comprises United States Patent (USP) 4,842,819; 4,917,858; 5,232,661; 5,348,702; 5,350,466; 5,370,839; 5,429,796; 5,503,794; 5,634,992 and 5,746,846; The open 63-171862 of Japanese Patent; 1-259139 and 1-42539; European patent disclose 365174 and people's such as V.R.Ryabov article be entitled as " performance of iron-Al series metal compounds " (Properties of theIntermetallic Compounds of System Iron-Alumihum " Published inMetal Metalloved; 27.No.4; 668-673,1969); People such as S.M.Barinov are entitled as " deformation and failure in the titanium aluminide " (" Deformation and Failure in TitaniumAluminide " Published in Izvestiva Akademii Nauk SSSR Metally, No.3,164-168,1984); Being entitled as of people such as W.Wunderlich " strengthen plasticity (" Enhanced Plasticity by DeformationTwinning of TI-Al-Base Alloys With Cr and Si " Published in Z.Metallkunde; 802-808,11/1990) by making the Ti-Al base alloy twin distortion that contains Cr and Si; (" Reserch; Development and Prospects ofTiAl Intermetallic compound Alloys " published in Titanium anZirconium.33 rolls up be entitled as " research and development of TiAl intermetallic alloy and the prospect " of T.Tsujimoto, No.3, the 19th page, 7/1985); N.Maeda is entitled as " high-temp plastic of intermetallic compound TiAl " (" High Temperature Plasticity of Intermetalliccompound TiAl " presented at Material of 53rd Meeting ofSuperplasticity, the 13rd page, 1/30/1990); Being entitled as of people such as N.Maeda " improved the plasticity of intermetallic compound " by the super-refinement of crystal grain (" Improvement in Ductility ofIntermetallic Compound through Grain Super-refinement " presented atAutumn Symposium of Japan Institute of Metals, 14 pages, 1989); People such as Nada are entitled as " mechanical property of TiAl intermetallic compound " (" Mechanical Properties ofTiAl Intermetallic Compound " presented at Autumn Symposium ofJapan Institute of Metals, page 2,1988); Being entitled as of Lipsitt " summary of the aluminide of titanium " (" Titaninm Aluminides-An Overview ", published in Mat.Res.Soc.Symp.Proc.39 volume, 351-364,1985); People such as P.L.Martin are entitled as that " alloying is to Ti
3The microstructure of Al and TiAl and Effect on Performance " (" The Effect of Alloying onMicrostructure and Properties of Ti
3Al and TiAl " published by ASM inTitanium 80.2 volumes, 1245-1254,1980); Being entitled as of people such as S.H.Whang " effect of the rapid solidification in the L1o TiAl compound alloy " (Effect of Rapid solidification in L1oTiAl Compound Alloys " ASM Symposium Proceedings on EnhancedPropeties in Structural Metals Via Rapid Soldification; Materials Weeek; the 7th page, 1986); And being entitled as of people such as D.Vujic " rapid solidification and add alloy " (" Effect of RapidSolidification and Alloying Addition on Lattice Distortion and AtiomicOrdering in Llo Alloys and Their Ternary Alloys " published inMetallurgical Transactions A to the lattice distortion in L1o TiAl alloy itself and the ternary alloy and the influence of atomic ordering, the 19A volume, 2445-2455,10/1988).
Available its handled the method that the TiAl aluminide makes it to reach desired properties and is disclosed in as in above-mentioned many parts of patents and the open source literature.In addition, US, 5,489,411 disclose a kind of powder metallurgy process, this method is by a kind of band that batches of plasma spraying, this band of thermal treatment is put the coarse side of two such bands together to discharge unrelieved stress, then they is placed on pressure together in conjunction with pushing between the roller, remake solution annealing, cold rolling and process annealing and make the paper tinsel of titanium aluminide.US.4,917,858 disclose a kind of powder metallurgy technology for preparing the calorize titanium foil with simple substance titanium, aluminium and other alloying element.US.5,634,992 disclose a kind of method of the γ of processing titanium aluminide, this method is by making castings fixed, add α and γ stratiform aggregate structure mutually at this clotty castings of the above thermal treatment of eutectoid temperature to form γ crystal grain, below eutectoid temperature, it is heat-treated so that the γ grain growing in this aggregate structure is heat-treated it below the α transition temperature again, have α in γ crystal grain so that any remaining aggregate structure forms again
2The tissue of lath.
The effort that continues in view of to the performance that improves titanium aluminide still needs improved alloy composite and economic working method.
The invention summary
According to first embodiment, the invention provides a kind of two-phase titanium aluminum alloy with stratiform (lamellar) microstructure that is subjected to the aggregate structure size control.This alloy can variform, provides as cast condition, hot extrusion state, cold-peace hot-work attitude or as-heat-treated condition.As finished product, this alloy can be made resistance heating element with 60-200 μ Ω cm resistivity.This alloy can contain on the aggregate structure border and to produce fine particle as second mutually or the auxiliary element of boride particle.This alloy can comprise the equiaxed grain structure of crystal boundary.This assistant alloy element for example, can comprise W, the Nb and/or the Mo that mostly are 10at% most.This alloy can be processed into yield strength greater than 80Ksi (560Mpa), and ultimate tensile strength is at least 1.5% thin slice greater than 90Ksi (630Mpa) and/or unit elongation.Aluminium content can be 40-50at%, is more preferably about 46at%.Titanium content is at least 45at%, is more preferably to be at least 50at%.For example, this alloy can contain the W of Nb, 0.5-2at% of Al, 1-5at% of Ti, 40-50at% of 45-55at% and the B of 0.1-0.3at%.This alloy does not preferably contain Cr, V, Mn and/or Ni.
Description of drawings
Fig. 1 a-d is in 1400 ℃ of hot extrusions, in 1000 ℃ of optical microscope photographs of 200 times having made 2 hours annealed PMTATiAl alloys.Fig. 1 a has showed the microstructure of PMTA-1, and Fig. 1 b has showed the microstructure of PMTA-2, and Fig. 1 c has showed the microstructure of PMTA-3, and Fig. 1 d has showed the microstructure of PMTA-4.
Fig. 2 a-d has showed in 1400 ℃ through hot extrusion, in 500 times of optical microscope photographs of 2 hours PMTA alloy of 1000 ℃ of annealing.Fig. 2 a-d has showed the microstructure of PMTA-1 to PMTA-4 respectively.
Fig. 3 has showed and has been 1400 ℃ through hot extrusion, observed ghost line band in the back scattering image of 2 hours PMTA-2 of 1000 ℃ of annealing, the uneven distribution of wherein having showed W.
Fig. 4 has showed in the time of 1400 ℃ through hot extrusion, in the back scattering figure of 2 hours PMTA-2 of 1000 ℃ of annealing.
Fig. 5 a be in 1400 ℃ through hot extrusion, in 1 day PMTA-3 of 1000 ℃ of annealing 200 show little photo, and Fig. 5 b is 500 times a Photomicrograph of same microstructure.
Fig. 6 a showed in 1400 ℃ through hot extrusion, in three days PMTA-2 of 1000 ℃ of annealing 200 show little tissue, and Fig. 6 b has showed 500 times same microstructure.
Fig. 7 a is that (Ti-45Al-5Cr, optical microscope photograph at%), Fig. 7 b have showed at the same microstructure of 1000 ℃ of annealing after three days, the equal 500 times ratio of enlargement of above-mentioned two photos for TiAl plate under the original state.
Fig. 8 a has showed the Photomicrograph of PMTA-6, and Fig. 8 b has showed the Photomicrograph of PMTA-7, the said two devices alloy all at 1380 ℃ through hot extrusion (magnification: 200 times).
Fig. 9 a is the Photomicrograph of PMTA-6, and Fig. 9 b is the Photomicrograph of PMTA-7, this two alloy all in 1365 ℃ through hot extrusion (magnification: 200 times).
Figure 10 is showed in 1380 ℃ of Photomicrographs that crystal grain is grown up unusually in the PMTA of hot extrusion.
Figure 11 a-d is after 1335 ℃ hot extrusion, the Photomicrograph of the PMTA-8 that heat-treats with different conditions, and the thermal treatment of Figure 11 a is 1000 ℃, 2 hours; Figure 11 b is 1340 ℃, 30 minutes; Figure 11 c is 1320 ℃, 30 minutes; Figure 11 d is 1315 ℃, 30 minutes (magnifications: 200X).
Figure 12 is the sample 1 that cuts from the ingot with PMTA-4 nominal composition and resistivity micro-ohm-thetagram of 2.
Figure 13 is the hemisphere total emissivity-thetagram of sample 1 and 2.
Figure 14 is sample 80259-1, the 80259-2 that cuts from the ingot identical with the ingot of sample 1 and 2, diffusivity-thetagram of 80259-3.
Figure 15 is the specific heat-thetagram of titanium aluminide of the present invention.
Figure 16 is coefficient of thermal expansion-thetagram of sample 80259-1H, the 80259-1C, 80259-2H, 80259-3H and the 80259-3C that cut from the ingot identical with the ingot of sample 1 and 2.
Preferable embodiment is described in detail in detail
The invention provides a kind of two-phase TiAl alloy, it has can make it be applicable to multiple Application Areas, as the heat physical properties and the mechanical property of resistance heating element.This alloy shows at the useful mechanical property and the corrosion resistance nature that are up under 1000 ℃ or the higher temperature.Extremely low (the about 4.0g/cm of the material proportion of this TiAl alloy
3), it has satisfactory room temperature and drawing by high temperature ductility and combination of strength, high resistivity and/or can be made into the sheet material of thickness＜10 mils.A kind of purposes of this sheet material is the resistance heating element of doing such as the appliances of cigarette lighter.Such as, this sheet can be formed the tubular heating element with a series of heater strips, these are individually for being disclosed in US.5,591,368 and 5,530, the igniting position of the cigarette in that class electricity smoking apparatus in 225 provides energy, and above-mentioned patent documentation is through being combined in herein with reference to its content.In addition, this alloy can not contain the element as Cr, V, Mn and/or Ni and so on.
With contain Cr, the V of 1-4at% and/or the TiAl alloy phase ratio of Mn in order to improve room temperature tensile ductility, by the present invention, the stretching ductility with two-phase TiAl alloy of lamellar structure mainly is subjected to aggregate structure, rather than is subjected to the control of these alloying elements.So the invention provides the high strength TiAi alloy that can not contain Cr, V, Mn and/or M.
Table 1 has been listed the nominal composition of this alloy that is studied, and wherein this basic alloy contains the Al of 46.5at% and the Ti of surplus.Add a small amount of alloying additive to inquire into to the mechanical property of this two-phase TiAl alloy and the influence of metallurgical performance.Find that maximum 4% Nb may influence oxidation-resistance, maximum 1.0% W influences the stability and the creep resisting ability of microstructure, and maximum 0.5% Mo influences hot workability.Be the lamellar structure in this two-phase of refinement TiAl alloy, add the B of as many as 0.18%.
By the metal of the commercially available pure level of arc melting and with its casting (drop casting) in 1 " diameter * 5 " make in the long copper mold and to have the listed composition of table 1, be denoted as 8 kinds of alloys of PMTA-1 to PMTA-9.All alloys all do not have casting flaw and successfully cast.Then 7 alloy pigs (PMTA-1 to PMTA-4 and PMTA-6 to PMTA-9) are sealed in the Mo jar, then with 5: 1-6: 1 extrusion ratio, 1335-1400 ℃ temperature through hot extrusion.Extruding condition is listed in table 2.With air cooling and in water this extruding rod of short period of time chilling control rate of cooling after the extruding.The out-of-shape of the alloy bar that in the time of 1365-1400 ℃, is squeezed into, and present quite slick surface and do not have the surface imperfection phenomenon in the PMTA-8 of 1335 ℃ of hot extrusions.But, in any hot extrude pressure bar, all do not find crackle.
With optics metallurgical analysis and the super probe analysis of electronics, detect the microstructure of this alloy as cast condition and heat treatment state (listing in the table 2).When as cast condition, all alloys all show the segregation that has to a certain degree and the lamellar structure of nucleation.Fig. 1 and 2 has showed 200X and 500X magnification hot extrusion alloy optical microscope photograph, and described alloy is to discharge the PMTA-1 to PMTA-4 that stress was handled 2 hours at 1000 ℃.It is lamellar structure fully that all alloys all present, and at the boundary of aggregate structure a spot of equiaxed grain structure is arranged.Seen some tiny particles at the aggregate structure boundary, electron probe microanalysis confirms that they are borides.Obvious difference on the microstructure characteristics does not appear in this 4 kinds of PMTA alloys yet.
The electron microprobe analysis revealed, though in the alloy of hot extrusion also uniform distribution not of tungsten.As in Fig. 3, find that the ghost band in darker contrast does not contain the tungsten of about 0.33at%W.Fig. 4 is the back scattering figure of PMTA-2, and it has shown in bright contrast, has formed the second phase particle (boride) in the aggregate structure border.The composition of this boride is determined and is listed in the table 3 with stratiform matrix composition.The second phase particle mainly is (Ti, W, Nb's) boride, and they are by decoration and being fixed on the border of stratiform aggregate.
Fig. 5 and 6 has showed in the PMTA-3 of the hot extrusion of 1000 ℃ of anneal respectively 1 day and 3 days and the optical microstructure of PMTA-2.In the sample of long term annealing, clearly observe the equiaxed grain structure of crystal boundary at these, and the increase of the annealing time of its amount during with 1000 ℃ strengthens.Being has a large amount of equiaxed grain structures in 3 days the sample of 1000 ℃ of annealing.
For comparison, and the TiAl sheet of assessment a slice 9 mil thick (Ti-54Al-5Cr, at%).Fig. 7 has showed the optical microstructure of this TiAlCr sheet under original state and annealing (1000 ℃, 3 days) state.Opposite with the two-phase lamellar structure of alloy of the present invention, this TiAlCr sheet has a kind of binary tissue, and its crystal structure does not have obvious chap in the time of 1000 ℃.
Intercept thickness 9-20 mil, the drawing sheet sample that sl. is 0.5 inch with the EDM machine from this hot extrusion alloy bar 1000 ℃ of annealing after 2 hours.Some sample was annealed maximum 3 days in 1000 ℃ before tension test again.On the Instron test machine,, under room temperature, carry out tension test with the strain rate of 0.1 inch per second.Stretch test result is listed in the table 4.
Discharge this alloy that stress handled 2 hours at 1000 ℃ and demonstrate under the room temperature that stretch percentage elongation is 1% or bigger in the air.When sample thickness when changing between 9 to 20 mils, this stretch percentage elongation is unaffected.As shown in table 4, in 4 kinds of alloys, alloy PMTA-4 has shown best stretching ductility.It should be noted that 1.6% stretch percentage elongation that derives from the sheet material sample of 20 mil thick conforms to 4% unit elongation from the bar-shaped sample gained of 0.12 inch of diameter of metering.The increase of the annealing time when this stretch percentage elongation demonstrates it along with 1000 ℃ has raising slightly, and maximum elongation is to obtain in 1 day sample of 1000 ℃ of annealing.
This all class alloys is all strong unusually, and its room temperature yield strength is greater than 100Ksi (700Mpa), and ultimate tensile strength is greater than 115Ksi (800Mpa).This high strength is owing to the complete lamellar structure that has produced refinement in these TiAl alloys.Compare mutually, the room temperature yield strength of TiAlCr sheet material has only 61ksi (420Mpa).Therefore the intensity of the strength ratio TiAlCr sheet material of this PMTA alloy is big by 67%.The intensity that contains this PMTA alloy of 0.5% Mo obviously improves, but the stretch percentage elongation of room temperature is low slightly.
Fig. 8 a-b and 9a-b have showed respectively when 1380 ℃ and 1365 ℃ through the PMTA-6 of hot extrusion and the optical microscope photograph of PMTA-7.Two kinds of alloys have all presented lamellated crystal structure and a spot of tissue between aggregate structure.When 1380 ℃ and 1365 ℃, in two kinds of alloys of hot extrusion, all observed big aggregate structure crystal grain (see figure 10), this may be crystal grain in containing the alloy of a small amount of B after hot extrusion excrescent result.There is not obvious difference aspect the microstructure characteristics in these two kinds of PMTA alloys.
Figure 11 a-11d has showed that thermal treatment is to the influence through the microstructure of the PMTA-8 of 1335 ℃ of hot extrusions.Thin more much smaller and have a tissue between more aggregate through this alloy phase of hot extrusion during through this alloy of hot extrusion and in 1380 ℃ and 1365 ℃ in 1335 ℃ than the size of its aggregate structure.In the hot extrusion organizational aspects, 1000 ℃ of thermal treatments of 2 hours do not produce any tangible change, and (Figure 11 a).But 1340 ℃, 30 minutes thermal treatment then causes very big aggregate structure (Figure 11 b).Thermal treatment temp is reduced to 1320-1315 ℃ (its difference is for 20-25 ℃) from 1340 ℃ then makes the size of aggregate structure fall suddenly (seeing Figure 11 c and 11d).Annealing in the time of 1320-1315 ℃ also goes out together to produce between more aggregate in PMTA-8 to be organized.By carrying out hot extrusion 1335 ℃ the time, unusual grain growing is almost eliminated fully.
Thickness changes to 22 mils by 8 mils, sl. is that the stretched sheet sample of 0.5 inch PMTA-6 to PMTA-8 is from carrying out 2 hours with the EDM machine, 1000 ℃ or 20 minutes, intercept on this hot extrusion alloy bar after 1320 ℃-1315 ℃ the final thermal treatment.In air,, on the Instron trier, carry out tension test being up under 800 ℃ the temperature with the strain rate of 0.1 inch per second.All stretch test results are listed in table 5-8.Through 2 hours, 1000 ℃ heat treated alloy PMTA-4 ,-6 and-7 all demonstrated good intensity under all temperature, and this intensity and extrusion temperature are irrelevant.Hot extrusion in the time of 1400-1365 ℃ has obtained lower room temperature and drawing by high temperature ductility (＜4%).When in 1335 ℃, carrying out hot extrusion, the stretching ductility that under all temperature, all has been improved significantly.Under all temperature, all demonstrate the highest intensity and stretching ductility in 1335 ℃ of PMTA-8 through hot extrusion.When sample thickness changed to 22 mils by 8 mils, stretching ductility is the variation of indicating system not.
Table 7 and 8 has been showed the tensile property respectively at 1320 ℃ and 20 minutes PMTA-6 of 1315 ℃ of thermal treatment and PMTA-7.Compare with the result of gained when 1000 ℃ of thermal treatment, the thermal treatment in the time of 1320-1315 ℃ has produced higher stretch percentage elongation, but has reduced the intensity under the test temperature.In all these alloys and thermal treatment, demonstrate best room temperature and drawing by high temperature ductility in 20 minutes PMTA-8 of 1315 ℃ of annealing again through hot extrusion in 1335 ℃.Under room temperature and 800 ℃, this alloy presents 3.3% and 11.7% stretching ductility respectively.Seem more much better than through 1315 ℃ heat treated PMTA-8 than known TiAl alloy heavily fortified point.
When attempting to check the bend ductility of TiAl alloy sheet material, make some heat treated through hot extrusion and 1320 ℃, the PMTA-7 of thick 11-20 mil and PMTA-8 alloy slice at room temperature bend.After bending to 42 °, every all fracture of alloy sheets.These results clearly illustrate that: the PMTA alloy with controlled microstructure at room temperature is bent.
Study PMTA-2 by sheet material sample (9-20 mil thick) being exposed in 800 ℃ the air ,-5 and-7 oxidation behavior.Periodically sample is taken out from stove to weigh and the surface check.These samples demonstrate that very little weight increases and without any peeling phenomenon.This shows, the rate of oxidation when alloy addition W and Nb have influenced 800 ℃ of this alloy, and W is more effective for the antioxidant property that improves this TiAl alloy.Among these alloys, the antioxidant property when PMTA-7 presents minimum weightening finish and best 800 ℃.The oxidation of PMTA-7 shows, the oxide compound scale has been clung and the sign that do not have micro-flaw and peel off fully.This observation clearly points out, the oxide compound scale of shape thereby is had excellent protective by on well attached to body material in the time of 800 ℃.
Figure 12 is resistivity (the micro-ohm)-thetagram of sample 1 and 2, described sample is from having the nominal composition of PMTA-4, promptly cutting on the ingot of the B of the W and 0.045% (weight) of the Nb, 2.4% (weight) of the Al of 30.8% (weight), 7.1% (weight); Figure 13 is the hemisphere total emissivity-thetagram of sample 1 and 2; Figure 14 is the sample 80259-1 that cuts from the ingot identical with the ingot of sample 1 and 2, diffusivity-temperature curve of 80259-2 and 80259-3; Figure 15 is the specific heat-temperature curve of titanium aluminide of the present invention; Figure 16 is coefficient of thermal expansion-temperature curve of the sample 80259-1H, the 80259-1C that cut from the ingot identical with the ingot of sample 1 and 2,80259-2H, 80259-3H, 80259-3C.
In a word, in the time of 1365 ℃-1400 ℃, mainly present and have the lamellar structure that organizes between the minor agglomeration may body, then present between a lot of thinner aggregate structures and more aggregate at 1335 ℃ of PMTA-8 and organize through extruding through the PMTA of hot extrusion alloy.20 minute the thermal treatment of PMTA-8 in the time of 1315-1320 ℃ has produced thinner lamellar structure.This alloy can comprise (Ti, W, the Nb) boride that is formed at the aggregate structure boundary.In addition, the W in the alloy of this hot extrusion distributes inhomogeneously, and this resistivity that shows the TiAl alloy of the additive that contains W may be very high.Mix 0.5at%Mo and improved the yield strength and the ultimate tensile strength of TiAl alloy significantly, but the stretch percentage elongation under the room temperature is reduced to a certain degree.In the PMTA1-4 of these 4 kinds of hot extrusions alloy, composition is the best of breed that the PMTA-4 of Ti-46.5 Al-3 Nb-0.5 W-0.2B (at%) has room temperature tensile ductility and intensity.Compare with TiAlCr (Ti-45Al-5Cr) sheet material, this PMTA-4 is higher by 67% than TiAlCr sheet intensity.The TiAlCr sheet does not at room temperature show bending ductility in addition, and the unit elongation of PMTA-4 is 1.4%.The stretch percentage elongation of TiAl alloy and scope are that the sheet of 9-20 mil is thick irrelevant.In 2 hours alloy PMTA-4 of 1000 ℃ of thermal treatments ,-6 and-7 all present under all temperature of 800 ℃ and good intensity that extrusion temperature is irrelevant being up to.But 1400-1365 ℃ extrusion temperature has produced lower room temperature and drawing by high temperature elongation (＜4%).When extrusion temperature was 1335 ℃, stretching ductility all was significantly improved under all temperature.1335 ℃ through hot extrusion, again in 1315 ℃ through 20 minutes annealed PMTA-8 (Ti-46.5 Al-3 Nb-1 W-0.5B) demonstrate best room temperature and drawing by high temperature ductility (room temperature: 3.3%; 800 ℃: 11.7%).Table 1 nominal alloy ingredient
Table 2 is used for the preparation and the heat-treat condition of PMTA alloy
Phase composite in the PMTA-2 alloy that table 3 is determined with the electron microprobe analysis
*Only metallic element table 4 in 1400 ℃ through the PMTA of hot extrusion alloy at room temperature tensile property
Table 5 in 1400 ℃ through hot extrusion again in 2 hours the tensile property of PMTA-4 of 1000 ℃ of annealing
Table 6 in 1365 ℃ through hot extrusion again in 2 hours the tensile property of PMTA-6 of 1000 ℃ of annealing
Table 7 is in 1365 ℃ of tensile properties through the PMTA-7 of hot extrusion
Table 8 is in the tensile property of the PMTA-8 of 1335 ℃ of hot extrusions
| Composition (at%) | |||||||
| Alloy number | ?Ti | ?Al | ?Cr | ?Nb | ?Mo | ?W | ?B |
| ?PMTA-1 | ?50.35 | ?46.5 | ?0 | ?2 | ?0.5 | ?0.5 | ?0.15 |
| ?PMTA-2 | ?50.35 | ?46.5 | ?0 | ?2 | ??- | ?1.0 | ?0.15 |
| ?PMTA-3 | ?49.85 | ?46.5 | ?0 | ?2 | ?0.5 | ?1.0 | ?0.15 |
| ?PMTA-4 | ?49.85 | ?46.5 | ?0 | ?3 | ??- | ?0.5 | ?0.15 |
| ?PMTA-5 | ?47.85 | ?46.5 | ?0 | ?4 | ??- | ?0.5 | ?0.15 |
| ?PMTA-6 | ?49.92 | ?46.5 | ?0 | ?3 | ??- | ?0.5 | ?0.08 |
| ?PMTA-7 | ?49.92 | ?46.5 | ?0 | ?3 | ??- | ?1.0 | ?0.08 |
| ?PMTA-8 | ?49.40 | ?46.5 | ?0 | ?3 | ??- | ?1.0 | ?0.10 |
| ?PMTA-9 | ?49.32 | ?46.5 | ?0 | ?3 | ??- | ?1.0 | ?0.18 |
| Table 1 (continuing) composition (weight %) | |||||||
| Alloy number | ?Ti | ?Al | ?Cr | ?Nb | ?Mo | ?W | ?B |
| ?PMTA-1 | ?60.46 | ?31.36 | ?0 | ?4.64 | ?1.20 | ?2.30 | ?0.04 |
| ?PMTA-2 | ?59.80 | ?31.02 | ?0 | ?4.60 | ?- | ?4.54 | ?0.04 |
| ?PMTA-3 | ?58.86 | ?30.83 | ?0 | ?4.57 | ?1.18 | ?4.52 | ?0.04 |
| ?PMTA-4 | ?59.55 | ?31.19 | ?0 | ?6.93 | ?- | ?2.29 | ?0.04 |
| ?PMTA-5 | ?57.71 | ?30.85 | ?0 | ?9.14 | ?- | ?2.26 | ?0.04 |
| ?PMTA-6 | ?59.56 | ?31.20 | ?0 | ?6.93 | ?- | ?2.29 | ?0.02 |
| ?PMTA-7 | ?57.98 | ?30.68 | ?0 | ?6.82 | ?- | ?4.50 | ?0.02 |
| ?PMTA-8 | ?57.98 | ?30.68 | ?0 | ?6.82 | ?- | ?4.50 | ?0.02 |
| ?PMTA-9 | ?57.97 | ?30.67 | ?0 | ?6.82 | ?- | ?4.49 | ?0.05 |
| Alloy number | Extrusion temperature (℃) | Thermal treatment (℃/time) |
| PMTA-1 | ?1400 | 1000 ℃, as many as 3 days |
| PMTA-2 | ?1400 | 1000 ℃, as many as 3 days |
| PMTA-3 | ?1400 | 1000 ℃, as many as 3 days |
| PMTA-4 | ?1400 | 1000 ℃, as many as 3 days |
| PMTA-5 | ||
| PMTA-6 | ?1380,1365 | 1000 ℃/2 hours |
| PMTA-7 | ?1380,1365 | 1000 ℃/2 hours, 1320 ℃/20 minutes |
| PMTA-8 | ?1335 | 1000 ℃/2 hours, 1315 ℃/20 minutes |
| Alloying element (at%) | ||||
| Phase | Ti | Al | W | Nb |
| Matrix phase (dark contrast) | Surplus | 44．96 | 0．82 | 1．32 |
| Matrix phase (bright contrast) | Surplus | 44．70 | 1．15 | 1．32 |
| Boride * | 77．69 | 8．66 | 9．98 | 3．67 |
| Alloy number | Form Nb-Mo-W (at%) | Stretch percentage elongation (%) | σy(ksi) | σuc(ksi) |
| 2 hours/1000 ℃ | ||||
| PMTA-1 | ?2/0.5/0.5 | ?1.0 | ?114 | ?118 |
| PMTA-2 | ?2/0/1.0 | ?1.2 | ?104 | ?117 |
| PMTA-3 | ?2/0.5/1.0 | ?1.1 | ?123 | ?132 |
| PMTA-4 | ?3/0/0.5 | ?1.4 | ?102 | ?115 |
| 1 day/1000 ℃ | ||||
| PMTA-3 | ?2/0.5/1.0 | ?1.4 | ?115 | ?131 |
| 3 days/1000 ℃ | ||||
| PMTA-2 | ?2/0/1.0 | ?0.8 | ?105 | ?109 |
| Probe temperature (℃) | Yield strength (ksi) | Ultimate tensile strength (ksi) | Extend main (%) |
| 22 | 102．0 | 115 | 1．4 |
| 600 | 101．0 | 127 | 2．4 |
| 700 | 96．5 | 130 | 2．7 |
| 800 | 97．8 | 118 | 2．4 |
| Probe temperature | Yield strength (ksi) | Ultimate tensile strength (ksi) | Unit elongation (%) |
| 22 | 121．0 | 136 | 1．3 |
| 300 | 101．0 | 113 | 1．2 |
| 700 | 93．6 | 125 | 2．7 |
| 800 | 86．5 | 125 | 3．9 |
| Probe temperature (℃) | Yield strength (ksi) | Ultimate tensile strength (ksi) | Unit elongation (%) |
| 1000 ℃, annealing in 2 hours | |||
| ?22 | ?116.0 | ?122 | ?1.0 |
| ?300 | ?101.0 | ?116 | ?1.5 |
| ?700 | ?105.0 | ?131 | ?2.7 |
| ?800 | ?87.2 | ?121 | ?3.1 |
| 1320 ℃, annealing in 20 minutes | |||
| ?20 | ?84.5 | ?106.0 | ?3.0 |
| ?300 | ?71.4 | ?89.8 | ?2.5 |
| ?700 | ?68.5 | ?97.2 | ?4.5 |
| ?800 | ?63.5 | ?90.2 | ?4.5 |
| Probe temperature (℃) | Yield strength (ksi) | Ultimate tensile strength (ksi) | Unit elongation (%) |
| 1000 ℃, annealing in 2 hours | |||
| ?22 | ?122.0 | ?140 | ?2.0 |
| ?300 | ?102.0 | ?137 | ?4.3 |
| ?700 | ?95.0 | ?131 | ?4.7 |
| ?800 | ?90.2 | ?124 | ?5.6 |
| 1315 ℃, annealing in 20 minutes | |||
| ?20 | ?96.2 | ?116 | ?3.3 |
| ?300 | ?79.4 | ?115 | ?6.1 |
| ?700 | ?72.2 | ?112 | ?7.5 |
| ?800 | ?72.0 | ?100 | ?11.7 |
Above-mentioned titanium aluminide can be made different shape or product, as make resistance heating element.But composition disclosed herein also can be used for other purpose, as is used for thermospray, and wherein said composition can be used as and has anti-oxidant and coating resistance to corrosion.Said composition also can be used as stator, porous filter of the discharging wall of base material, automobile and diesel motor of transfer lime, catalytic converter of parts, chemical reactor, anti-sulfurized material, the corrosion resistant material that is used for chemical industry, coal slurry or the coal tar of anti-oxidant and erosion-resisting electrode, stove and turbocharger etc.
With regard to resistance heating element, the shape that can change this heating unit sheet is with according to formula: (L/W * T) optimizes the resistance of well heater to R=ρ, in the formula, the resistance of R=well heater, the resistivity of ρ=heater material, L=heater length, W=heater width, and T=heater thickness.The resistivity of heater material can be by changing its composition, as adjusting the aluminium content of heater material; Change working method or mix alloy addition and changed.Such as, by in heater material, mixing alumina particle resistivity is obviously raise.This heater material can randomly contain ceramic particle to improve creep resisting ability and/or thermal conductivity.Such as, this heater material can contain the particle or the fiber of electro-conductive material, as nitride, carbide, boride and the MoSi of transition metal (Zr, Ti, Hf)
2So that good high temperature resistance (being up to 1200 ℃) creep property and good antioxidant property to be provided.This heater material also can add the particle of electrically insulating material, as Al
2O
3, Y
2O
3, Si
3N
4, ZrO
2,, reach the thermal expansivity that improves thermal conductivity and/or reduce this heater material so that the heater material of high temperature creep-resisting is provided.This electrical isolation/conductive particle/fiber can be added in the pulverulent mixture of Fe, Al, Ti or iron aluminide, or the reaction of the powder by element state forms this particle/fiber, thermopositive reaction takes place in this powder when making plus heater element.
Principle of the present invention, preferred embodiment scheme and operational method have above been stated.But, should not limit the invention to the specific embodiment of being discussed.Therefore, the foregoing description should be considered as illustratively, rather than restrictive, and those skilled in the art change and should be understood without prejudice to being made in these embodiments by the appended spirit that claim limited.
Claims (19)
1. titanium aluminide alloy, it is mainly by Al, the Nb of 2-15% of Ti, the 25-35% of (weight %) 50-65%, the Mo less than 5%, the W of 1-10% and the B of 0.01-0.2% constitute.
2. the titanium aluminide alloy of claim 1, it is in as cast condition, hot extrusion state, cold working attitude or as-heat-treated condition.
3. the titanium aluminide alloy of claim 1, wherein this alloy has two-phase stratiform microstructure, and tiny particle is positioned at the boundary of aggregate structure.
4. the titanium aluminide alloy of claim 3, wherein tiny boride particle is positioned at the aggregate structure boundary.
5. the titanium aluminide alloy of claim 3, the second wherein tiny phase particle is positioned at the boundary of aggregate structure.
6. the titanium aluminide alloy of claim 1, wherein this alloy has the two-phase microstructure that comprises the crystal boundary equiaxed structure.
7. the titanium aluminide alloy of claim 1 wherein contains Nb, the W of maximum 2% Mo, 2-8% of Al, 4-9% of Ti, 30-32% of 57-60% and the B of 0.02-0.08%.
8. the titanium aluminide alloy of claim 1, its yield strength is greater than 80ksi (560Mpa), the ultimate tensile strength stretch percentage elongation greater than 90Ksi (680Mpa) and/or at least 1%.
9. the titanium aluminide alloy of claim 1, wherein this alloy has such microstructure: W wherein is a non-uniform Distribution.
10. the titanium aluminide alloy of claim 1, wherein aluminium content is about 46-47at%.
11. the titanium aluminide alloy of claim 1, wherein the microstructure of this alloy is the lamellar structure in the essentially no equiaxed structure of aggregate structure boundary.
12. the titanium aluminide alloy of claim 1, wherein this alloy does not contain Mo or Cr.
13. the titanium aluminide alloy of claim 1 wherein contains the W of Nb, 2-8% of Al, 4-9% of Ti, 30-32% of 57-60% and the B of 0.02-0.08%.
14. the titanium aluminide alloy of claim 1, it contains the Ti of 45-55at%, the W of the Al of 40-50at%, the Nb of 1-5at%, 0.3-1.5at%, the B of 0.1-0.3at%.
15. the titanium aluminide alloy of claim 1, it comprises that thickness is the sheet of 8-30 mil.
16. the titanium aluminide alloy of claim 1, it does not contain Cr, V, Mn, Co, Cu and Ni.
17. the titanium aluminide alloy of claim 1, it comprise the Nb that contains 2-4at% ,≤TiAl of the B of the Mo of 1at%, the W of 0.5-2at% and 0.1-0.3at%.
18. the titanium aluminide alloy of claim 1, it contain 1-4at% Nb ,≤Mo of 1at% and the W of 0.25-2at%.
19. the titanium aluminide alloy of claim 1, wherein this alloy has formed resistance heating element, and this element is by maximum 10 volts, can be in being heated to 900 ℃ less than 1 second during maximum 6 amperes electric current.
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| US1748398A | 1998-02-02 | 1998-02-02 | |
| US09/017,483 | 1998-02-02 | ||
| US09/174,103 US6214133B1 (en) | 1998-10-16 | 1998-10-16 | Two phase titanium aluminide alloy |
| US09/174,103 | 1998-10-16 |
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| US5281285A (en) * | 1992-06-29 | 1994-01-25 | General Electric Company | Tri-titanium aluminide alloys having improved combination of strength and ductility and processing method therefor |
| US5370830A (en) * | 1992-09-23 | 1994-12-06 | Kimberly-Clark Corporation | Hydrosonic process for forming electret filter media |
| US5350466A (en) * | 1993-07-19 | 1994-09-27 | Howmet Corporation | Creep resistant titanium aluminide alloy |
| US5417781A (en) * | 1994-06-14 | 1995-05-23 | The United States Of America As Represented By The Secretary Of The Air Force | Method to produce gamma titanium aluminide articles having improved properties |
-
1999
- 1999-02-02 EP EP99935269A patent/EP1066415B1/en not_active Expired - Lifetime
- 1999-02-02 CA CA002319505A patent/CA2319505C/en not_active Expired - Fee Related
- 1999-02-02 AT AT99935269T patent/ATE221137T1/en active
- 1999-02-02 ID IDW20001685A patent/ID26231A/en unknown
- 1999-02-02 DE DE69902245T patent/DE69902245T2/en not_active Expired - Lifetime
- 1999-02-02 JP JP2000542498A patent/JP4664500B2/en not_active Expired - Fee Related
- 1999-02-02 AU AU50783/99A patent/AU751819B2/en not_active Ceased
- 1999-02-02 KR KR1020007008448A patent/KR100641905B1/en not_active IP Right Cessation
- 1999-02-02 CN CN99803452A patent/CN1100153C/en not_active Expired - Fee Related
- 1999-02-02 BR BR9908529-1A patent/BR9908529A/en not_active IP Right Cessation
- 1999-02-02 WO PCT/US1999/002212 patent/WO1999051787A1/en not_active Application Discontinuation
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2000
- 2000-07-28 NO NO20003891A patent/NO333617B1/en not_active IP Right Cessation
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102665946A (en) * | 2009-12-24 | 2012-09-12 | 浦项工科大学校产学协力团 | Method for producing a high-strength and highly ductile titanium alloy |
| CN103820674A (en) * | 2014-03-12 | 2014-05-28 | 北京工业大学 | W and Mn alloying beta phase solidifying high Nb-TiAl alloy and preparation method thereof |
| CN103820676A (en) * | 2014-03-12 | 2014-05-28 | 北京工业大学 | Cr and V alloying beta phase solidifying high Nb-TiAl alloy and preparation method thereof |
| CN103820676B (en) * | 2014-03-12 | 2016-03-02 | 北京工业大学 | A kind of Cr, V alloy β phase solidify high Nb containing TiAl based alloy and preparation method thereof |
| CN103820674B (en) * | 2014-03-12 | 2016-05-25 | 北京工业大学 | A kind of W, Mn alloying β solidify high Nb-TiAl Alloy And Preparation Method mutually |
| CN105821470A (en) * | 2016-04-14 | 2016-08-03 | 南京理工大学 | Dual-structure titanium aluminum (TiAl) alloy and preparation method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| DE69902245D1 (en) | 2002-08-29 |
| WO1999051787A1 (en) | 1999-10-14 |
| NO20003891D0 (en) | 2000-07-28 |
| AU751819B2 (en) | 2002-08-29 |
| EP1066415B1 (en) | 2002-07-24 |
| EP1066415A1 (en) | 2001-01-10 |
| DE69902245T2 (en) | 2003-03-27 |
| JP2002510750A (en) | 2002-04-09 |
| JP4664500B2 (en) | 2011-04-06 |
| EP1066415A4 (en) | 2001-05-09 |
| NO20003891L (en) | 2000-10-02 |
| NO333617B1 (en) | 2013-07-22 |
| BR9908529A (en) | 2000-12-05 |
| CA2319505A1 (en) | 1999-10-14 |
| ID26231A (en) | 2000-12-07 |
| CA2319505C (en) | 2009-10-06 |
| ATE221137T1 (en) | 2002-08-15 |
| KR100641905B1 (en) | 2006-11-06 |
| WO1999051787A9 (en) | 2000-06-22 |
| CN1100153C (en) | 2003-01-29 |
| AU5078399A (en) | 1999-10-25 |
| KR20010040579A (en) | 2001-05-15 |
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