EP1002882A1 - A beta titanium alloy - Google Patents
A beta titanium alloy Download PDFInfo
- Publication number
- EP1002882A1 EP1002882A1 EP99308274A EP99308274A EP1002882A1 EP 1002882 A1 EP1002882 A1 EP 1002882A1 EP 99308274 A EP99308274 A EP 99308274A EP 99308274 A EP99308274 A EP 99308274A EP 1002882 A1 EP1002882 A1 EP 1002882A1
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- EP
- European Patent Office
- Prior art keywords
- titanium alloy
- beta titanium
- beta
- carbon
- oxygen
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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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
Definitions
- the present invention relates to beta titanium alloys, particularly to burn resistant beta titanium alloys.
- Titanium alloys are used in gas turbine engines, particularly for compressor blades and compressor vanes in the low pressure compressor and the high pressure compressor.
- titanium is a highly reactive metal and may burn in appropriate circumstances. For example if the tip of a titanium alloy compressor blade rubs on the compressor casing, during operation of the gas turbine engine, the friction may lead to ignition of the titanium alloy compressor blade.
- titanium alloy which is burn resistant, preferably it does not burn, if friction occurs between a titanium alloy compressor blade and a compressor casing, during operation of the gas turbine engine.
- a non burning beta titanium alloy is known from published UK patent application GB2238057A, which comprises at least 20wt% vanadium, at least 10wt% chromium and at least 40wt% titanium.
- This alloy may comprise up to 2.5wt% carbon and up to 0.3wt% oxygen. This mentions that the carbon addition improves the post creep ductility of the alloy and the carbon forms carbides. There is no discussion of the oxygen in the alloy. None of the alloy examples comprise oxygen. The alloy does not comprise any aluminium. Thus this alloy is relatively expensive to produce because the vanadium is added as an element rather than as a vanadium-aluminium master alloy.
- a beta titanium alloy is known, from UK patent GB1175683 which, comprises 25-40wt% vanadium, 5-15wt% chromium, 0-10wt% aluminium and the balance titanium and impurities.
- This alloy may comprise up to 2wt% carbon and up to 0.3wt% oxygen. The carbon is added to increase the strength of the alloy and the oxygen is an impurity. None of the alloy examples comprise oxygen. This alloy is relatively cheap to produce because the vanadium is added in the form of vanadium-aluminium master alloy.
- the present invention seeks to provide a novel beta titanium alloy which minimises the above mentioned problem.
- the present invention provides beta titanium alloy comprising at least 10wt% of one or more beta stabilising elements, 0.1 to 0.4wt% carbon up to 0.2wt% oxygen and the balance titanium and incidental impurities, wherein the carbon is present in the form of titanium carbide precipitates distributed throughout the beta titanium alloy matrix, the titanium carbide precipitates refine the grain size of the beta titanium alloy matrix and remove oxygen from the beta titanium alloy matrix to reduce precipitation of alpha titanium in the beta titanium alloy matrix to increase the ductility of the beta titanium alloy.
- the beta stabilising element are selected from the group comprising vanadium, molybdenum, tantalum, niobium, chromium, tungsten, manganese and iron.
- the beta titanium alloy comprises aluminium.
- the present invention provides a beta titanium alloy comprising 20 to 30wt% vanadium, 13 to 17wt% chromium, 1,0 to 3.0wt% aluminium, 0.1 to 0.4wt% carbon, up to 0.2wt% oxygen and the balance titanium plus incidental impurities.
- the beta titanium alloy comprises 1.5 to 2.5wt% aluminium.
- the beta titanium alloy comprises 0.15 to 0.3wt% carbon.
- the beta titanium alloy comprises less than 0.15wt% oxygen.
- the beta titanium alloy comprises 23-27wt% vanadium, 13-17wt% chromium, 1-3wt% aluminium, up to 0.15wt% oxygen, 0.1 to 0.3wt% carbon and the balance titanium plus incidental impurities.
- the beta titanium alloy comprises 25wt% vanadium, 15wt% chromium, 2wt% aluminium, up to 0.15wt% oxygen, 0.1 to 0.3wt% carbon and the balance titanium plus incidental impurities.
- the present invention also provides an article comprising a beta titanium alloy, the beta titanium alloy comprising at least 10wt% of one or more beta stabilising elements, 0.1 to 0.4wt% carbon up to 0.2wt% oxygen and the balance titanium and incidental impurities, wherein the carbon is present in the form of titanium carbide precipitates distributed throughout the beta titanium alloy matrix, the titanium carbide precipitates refine the grain size of the beta titanium alloy matrix and remove oxygen from the beta titanium alloy matrix to reduce precipitation of alpha titanium in the beta titanium alloy matrix to increase the ductility of the beta titanium alloy.
- the beta titanium alloy comprises 20 to 30wt% vanadium, 13 to 17wt% chromium, 1.0 to 3.0wt% aluminium, 0.1 to 0.4wt% carbon, up to 0.2wt% oxygen and the balance titanium plus incidental impurities.
- the beta titanium alloy comprises 23-27wt% vanadium, 13-17wt% chromium, 1-3wt% aluminium, up to 0.15wt% oxygen, 0.1 to 0.3wt% carbon and the balance titanium plus incidental impurities.
- the beta titanium alloy comprises 25wt% vanadium, 15wt% chromium, 2wt% aluminium, up to 0.15wt% oxygen, 0.1 to 0.3wt% carbon and the balance titanium plus incidental impurities.
- the article comprises a component for a gas turbine engine.
- the component comprises a compressor blade or a compressor vane.
- the component may comprise a tip portion for a compressor blade.
- Figure 1 shows a compressor blade comprising a beta titanium alloy according to the present invention.
- Figure 2 shows a compressor blade having a tip portion comprising a beta titanium alloy according to the present invention.
- Figure 3 is a graph of elongation against oxygen content for beta titanium alloys with varying degrees of carbon addition.
- a gas turbine engine compressor blade 10 as shown in figure 1, comprises an aerofoil 12, a platform 14 and a root 16.
- the compressor blade 10 comprises a beta titanium alloy, preferably a burn resistant beta titanium alloy, according to the present invention.
- the beta titanium alloy compressor blade may be forged, or cast, or produced by other thermomechanical processes.
- a gas turbine engine compressor blade 20, as shown in figure 2, comprises an aerofoil 22, a platform 24 and a root 26.
- the compressor blade 10 also comprises a tip portion 28 on the extremity of the aerofoil 22 remote from the platform 24 and root 26.
- the tip portion 28 comprises a beta titanium alloy, preferably a burn resistant titanium alloy according to the present invention.
- the tip portion 28 may comprise weld filler deposited onto the aerofoil 22 by using the burn resistant beta titanium alloy as the weld filler during welding, e.g. tungsten inert gas (TIG) welding. The weld filler subsequently being machined to size and shape.
- the tip portion 28 may comprise a block of the burn resistant beta titanium alloy which is welded onto the aerofoil, e.g. tungsten inert gas (TIG) welding, laser welding, electron beam welding etc. The block subsequently being machined to size and shape.
- the burn resistant titanium alloy according to the present invention comprises 20 to 30wt% vanadium, 13 to 17w% chromium, 1.0 to 3.0wt% aluminium, 0.1 to 0.4wt% carbon, up to 0.2wt% oxygen and the balance titanium plus incidental impurities.
- the beta titanium alloy comprises 23-27wt% vanadium, 13-17wt% chromium, 1-3wt% aluminium, up to 0.15wt% oxygen, 0.1 to 0.3wt% carbon and the balance titanium plus incidental impurities.
- the beta titanium alloy comprises 25wt% vanadium, 15wt% chromium, 2wt% aluminium, up to 0.15wt% oxygen, 0.1 to 0.3wt% carbon and the balance titanium plus incidental impurities.
- the burn resistant beta titanium alloy in particular has a favourable combination of carbon and oxygen which enhances the ductility of the burn resistant titanium alloy. It has been found that there is a synergy between the oxygen and carbon levels. In particular it has been found that the carbon reacts with the titanium to form titanium carbide (Ti 2 C) precipitates which refine the grain size of the beta titanium alloy matrix.
- titanium carbide (Ti 2 C) precipitates have an affinity for the oxygen and the oxygen becomes attached to the titanium carbide (Ti 2 C) precipitates and thus the oxygen is removed from the beta titanium alloy matrix.
- the presence of oxygen in the beta titanium alloy matrix has the effect of promoting the precipitation of alpha titanium in the beta titanium alloy matrix.
- the presence of alpha titanium in the beta titanium alloy reduces the ductility of the beta titanium alloy.
- the titanium carbide precipitates remove oxygen from the beta titanium alloy matrix there is less oxygen available to promote the precipitation of the alpha titanium, and thus the precipitation of alpha titanium in the beta titanium alloy matrix is reduced. Therefore this increases the ductility of the beta titanium alloy.
- the carbon does not remove all the oxygen from the beta titanium alloy matrix.
- titanium carbide Ti 2 C precipitates are formed when more than 0.1wt% carbon is present in the beta titanium alloys mentioned above. These titanium carbide precipitates getter the oxygen and refine the grains. The carbon addition improves the stability of the beta titanium alloys.
- the increase in the ductility of the beta titanium alloy provided by the synergy between the oxygen and the carbon enables aluminium to be added to the beta titanium alloy, and this enables the use of cheaper master alloys, e.g. vanadium aluminium master alloys.
- Alloys with the composition listed in table 1 were produced using a plasma melter from mixtures of master alloys and elemental raw materials. Either titanium sponge with 0.04wt% oxygen or titanium granules with 0.086wt% oxygen were used according to the desired oxygen levels. The base level of carbon with no deliberate addition of carbon is 0.02wt% carbon which was brought in by impurities in the raw materials.
- the alloy samples were all forged at 1050°C to produce pancakes about 16mm thick.
- the samples were then heat treated at 850°C for 2 hours air cooled, or heat treated at 1050°C for 0.5 hours air cooled followed by ageing at 700°C for 4 hours air cooled or heat treated at 1050°C for 0.5 hours air cooled then followed by ageing at 700°C for 4 hours air cooled and then followed by heat treatment at 550°C for 500 hours air cooled.
- the alloy samples were cut, polished and etched for conventional optical microscopy and scanning electron microscopy. Additionally X-ray diffraction, EDX and transmission electron microscopy were performed on the alloy samples. All the alloy samples were tested in tension at room temperature, and the results are listed in table 2 and illustrated graphically in figure 3.
- alloy samples without carbon failed by cleavage fracture, whereas alloy samples with carbon failed by a ductile, or by a mixture of ductile/brittle, manner.
- the titanium carbide precipitates formed are stable to heat treatment and these titanium carbide precipitates refine the as forged and heat treated microstructure and as cast microstructure.
- the refined microstructure may deform more uniformly and may have an effect on the ductility of the beta titanium alloy.
- the titanium carbide precipitates getter oxygen, increase the ductility of the beta titanium alloy matrix and suppress the formation of the alpha titanium in the beta titanium alloy matrix.
- the refined beta titanium alloy matrix has smaller grains and thus there are more grain boundaries. The amounts of alpha titanium precipitation present on each grain boundary is less and this further increases ductility by reducing embrittlement due to alpha titanium.
- the carbon level must not be too high in the beta titanium alloys, since the precipitation of too much titanium carbide is detrimental to ductility.
- beta titanium alloys It is well known in the art that the addition of carbon to beta titanium alloys produces titanium carbides. It is also well known that beta titanium alloys become brittle due to titanium carbide precipitation. Thus this improvement in ductility of the beta titanium alloy due to the higher than normal addition of carbon in the presence of the oxygen is completely unexpected.
- beta stabilising element may be one or more of the elements vanadium, molybdenum, tantalum, niobium, chromium, tungsten, manganese, copper, nickel and iron.
- the advantages provided by the present invention are an increase in the ductility of the beta titanium alloy provided by the synergy between the oxygen and the carbon. This enables aluminium to be added to the beta titanium alloy, and this enables the use of cheaper master alloys, e.g. vanadium aluminium master alloys. There may also be an improvement in the processing temperature range.
- compressor blades and compressor vanes Although the invention has been described with reference to the use as compressor blades and compressor vanes, it may also be used to make compressor casings and other suitable components for gas turbine engines or other engines and for other applications.
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
(Composition in weight%) | |||||||
Alloy Code | Elements | ||||||
Ti | V | Cr | Al | C | | ||
A8 | Balance | ||||||
25 | 15 | 2 | 0.02 | 0.065 | |||
| Balance | 25 | 15 | 2 | 0.02 | 0.095 | |
| Balance | 25 | 15 | 2 | 0.02 | 0.135 | |
| Balance | 25 | 15 | 2 | 0.10 | 0.115 | |
| Balance | 25 | 15 | 2 | 0.20 | 0.110 | |
| Balance | 25 | 15 | 2 | 0.30 | 0.095 | |
| Balance | 25 | 15 | 2 | 0.09 | 0.165 | |
| Balance | 25 | 15 | 2 | 0.21 | 0.15 | |
| Balance | 25 | 15 | 2 | 0.31 | 0.15 |
(Tensile Properties) | ||||
Alloy Code | Heat Treat Conditions | 0.2% Proof Stress (MPa) | Ultimate Tensile Strength (MPa) | Elongation (%) |
| 1 | 828 | 858 | 21.0 |
A14 | 1 | 805 | 842 | 1.5 |
2 | 892 | 892 | 1.4 | |
3 | 953 | 955 | 0.6 | |
| 1 | 835 | 853 | 0.5 |
2 | 902 | 0.1 | ||
3 | 949 | 949 | 0.3 | |
| 1 | 916 | 921 | 24.0 |
2 | 878 | 891 | 16.4 | |
3 | 887 | 896 | 4.9 | |
| 1 | 899 | 939 | 20.3 |
2 | 894 | 923 | 15.0 | |
3 | 849 | 891 | 11.8 | |
| 1 | 867 | 905 | 16.6 |
2 | 866 | 882 | 14.0 | |
3 | 849 | 891 | 4.6 | |
| 1 | 891 | 0 | |
2 | 938 | 944 | 0.5 | |
| 1 | 900 | 914 | 8.4 |
2 | 882 | 903 | 8.7 | |
3 | 890 | 911 | 9.9 | |
| 1 | 935 | 964 | 10.9 |
2 | 903 | 915 | 1.0 | |
3 | 885 | 927 | 10.5 |
Claims (17)
- A beta titanium alloy comprising 20 to 30wt% vanadium, 13 to 17wt% chromium, 1.0 to 3.0wt% aluminium, 0.1 to 0.4wt% carbon, up to 0.2wt% oxygen and the balance titanium plus incidental impurities, wherein the carbon is present in the form of titanium carbide precipitates distributed throughout the beta titanium alloy matrix, the titanium carbide precipitates refine the grain size of the beta titanium alloy matrix and remove oxygen from the beta titanium alloy matrix to reduce precipitation of alpha titanium in the beta titanium alloy matrix to increase the ductility of the beta titanium alloy.
- A beta titanium alloy as claimed in claim 1 wherein the beta titanium alloy comprises 1.5 to 2.5wt% aluminium.
- A beta titanium alloy as claimed in claim 1 or claim 2 wherein the beta titanium alloy comprises 0.15 to 0.3wt% carbon.
- A beta titanium alloy as claimed in any of claims 1 to 3 wherein the beta titanium alloy comprises less than 0.15wt% oxygen.
- A beta titanium alloy as claimed in any of claims 1 to 4 wherein the beta titanium alloy comprises 23-27wt% vanadium, 13-17wt% chromium, 1-3wt% aluminium, up to 0.15wt% oxygen, 0.1 to 0.3wt% carbon and the balance titanium plus incidental impurities.
- A beta titanium alloy as claimed in claim 5 wherein the beta titanium alloy comprises 25wt% vanadium, 15wt% chromium, 2wt% aluminium, up to 0.15wt% oxygen, 0.1 to 0.3wt% carbon and the balance titanium plus incidental impurities.
- An article (10) comprising a beta titanium alloy, the beta titanium alloy comprising 20 to 30wt% vanadium, 13 to 17wt% chromium, 1.0 to 3.0wt% aluminium, 0.1 to 0.4wt% carbon, up to 0.2wt% oxygen and the balance titanium plus incidental impurities, wherein the carbon is present in the form of titanium carbide precipitates distributed throughout the beta titanium alloy matrix, the titanium carbide precipitates refine the grain size of the beta titanium alloy matrix and remove oxygen from the beta titanium alloy matrix to reduce precipitation of alpha titanium in the beta titanium alloy matrix to increase the ductility of the beta titanium alloy.
- An article as claimed in claim 7 wherein the beta titanium alloy comprises 23-27wt% vanadium, 13-17wt% chromium, 1-3wt% aluminium, up to 0.15wt% oxygen, 0.1 to 0.3wt% carbon and the balance titanium plus incidental impurities.
- An article as claimed in claim 8 wherein the beta titanium alloy comprises 25wt% vanadium, 15wt% chromium, 2wt% aluminium, up to 0.15wt% oxygen, 0.1 to 0.3wt% carbon and the balance titanium plus incidental impurities.
- An article as claimed in claim 7, claim 8 or claim 9 wherein the article (10) comprises a component for a gas turbine engine.
- An article as claimed in claim 10 wherein the component (10) comprises a compressor blade or a compressor vane.
- An article as claimed in claim 10 wherein the component (28) comprises a tip portion for a compressor blade (20).
- A beta titanium alloy comprising at least 10wt% of one or more beta stabilising elements, aluminium, 0.1 to 0.4wt% carbon up to 0.2wt% oxygen and the balance titanium and incidental impurities, wherein the carbon is present in the form of titanium carbide precipitates distributed throughout the beta titanium alloy matrix, the titanium carbide precipitates refine the grain size of the beta titanium alloy matrix and remove oxygen from the beta titanium alloy matrix to reduce precipitation of alpha titanium in the beta titanium alloy matrix to increase the ductility of the beta titanium alloy.
- A beta titanium alloy as claimed in claim 13 wherein the beta stabilising element is selected from the group comprising vanadium, molybdenum, tantalum, niobium, chromium, tungsten, manganese and iron.
- A beta titanium alloy as claimed in claim 13 or claim 14 wherein the beta titanium alloy comprises 1.5 to 2.5wt% aluminium.
- A beta titanium alloy as claimed in claim 13, claim 14 or claim 15 wherein the beta titanium alloy comprises 0.15 to 0.3wt% carbon.
- A beta titanium alloy as claimed in any of claims 13 to 16 wherein the beta titanium alloy comprises less than 0.15wt% oxygen.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB9824611 | 1998-11-11 | ||
GBGB9824611.9A GB9824611D0 (en) | 1998-11-11 | 1998-11-11 | A beta titanium alloy |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1002882A1 true EP1002882A1 (en) | 2000-05-24 |
EP1002882B1 EP1002882B1 (en) | 2002-12-11 |
Family
ID=10842177
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP99308274A Expired - Lifetime EP1002882B1 (en) | 1998-11-11 | 1999-10-20 | A beta titanium alloy |
Country Status (4)
Country | Link |
---|---|
US (3) | US20020108682A1 (en) |
EP (1) | EP1002882B1 (en) |
DE (1) | DE69904430T2 (en) |
GB (1) | GB9824611D0 (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2423089A (en) * | 2005-02-11 | 2006-08-16 | Rolls Royce Plc | Beta titanium eutectoid alloys |
WO2007029897A1 (en) * | 2005-09-09 | 2007-03-15 | Hanmaun Energy Science Institute Co. | A composition of titanium alloy strengthened by carbide precipitation and its heat treatment method |
WO2010026179A1 (en) * | 2008-09-05 | 2010-03-11 | Snecma | Method for making a circular revolution thermomechanical part including a carrier substrate containing titanium coated with steel or a superalloy, and titanium fire-resistant compressor casing for a turbine engine obtained by said method |
WO2010026181A1 (en) * | 2008-09-05 | 2010-03-11 | Snecma | Method for making a circular revolution thermomechanical part comprising a carrier substrate containing titanium coated with steel or a superalloy, and titanium fire-resistant compressor casing for a turbine engine obtained by said method |
WO2010026182A1 (en) * | 2008-09-05 | 2010-03-11 | Snecma | Method for making a circular revolution thermomechanical part comprising a carrier substrate containing titanium coated with steel or a superalloy, and titanium fire-resistant compressor casing for a turbine engine obtained by said method |
CN109913733A (en) * | 2019-04-08 | 2019-06-21 | 大连大学 | A kind of high corrosion-resistant Ti40-xCu40Al20GdxThe preparation method of flame-retardant alloy |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20040168751A1 (en) * | 2002-06-27 | 2004-09-02 | Wu Ming H. | Beta titanium compositions and methods of manufacture thereof |
US20040261912A1 (en) * | 2003-06-27 | 2004-12-30 | Wu Ming H. | Method for manufacturing superelastic beta titanium articles and the articles derived therefrom |
CA2489432A1 (en) * | 2002-06-27 | 2004-01-08 | Memry Corporation | Method for manufacturing superelastic .beta. titanium articles and the articles derived therefrom |
US20050091847A1 (en) * | 2003-10-31 | 2005-05-05 | Beneteau Douglas P. | Method for repairing gas turbine compressor rotor blades |
US7506440B2 (en) * | 2005-06-28 | 2009-03-24 | General Electric Company | Titanium treatment to minimize fretting |
US20060289088A1 (en) * | 2005-06-28 | 2006-12-28 | General Electric Company | Titanium treatment to minimize fretting |
US9016551B2 (en) | 2006-11-02 | 2015-04-28 | The Boeing Company | Method and apparatus to construct metal securement member for an aircraft |
US8168117B2 (en) * | 2006-11-09 | 2012-05-01 | United Technologies Corporation | Method to improve stability of burn-resistant titanium alloy |
JP6238056B2 (en) * | 2013-11-26 | 2017-11-29 | 三菱日立パワーシステムズ株式会社 | Dummy ring assembly for removing a vane segment and a method for removing a vane segment using the same |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5176762A (en) * | 1986-01-02 | 1993-01-05 | United Technologies Corporation | Age hardenable beta titanium alloy |
US5759484A (en) * | 1994-11-29 | 1998-06-02 | Director General Of The Technical Research And Developent Institute, Japan Defense Agency | High strength and high ductility titanium alloy |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
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US2829974A (en) * | 1952-10-08 | 1958-04-08 | Rem Cru Titanium Inc | Titanium-base alloys |
US3854891A (en) * | 1972-09-25 | 1974-12-17 | Allegheny Ludlum Ind Inc | Titanium composite |
US5068003A (en) * | 1988-11-10 | 1991-11-26 | Sumitomo Metal Industries, Ltd. | Wear-resistant titanium alloy and articles made thereof |
-
1998
- 1998-11-11 GB GBGB9824611.9A patent/GB9824611D0/en not_active Ceased
-
1999
- 1999-10-20 DE DE69904430T patent/DE69904430T2/en not_active Expired - Lifetime
- 1999-10-20 EP EP99308274A patent/EP1002882B1/en not_active Expired - Lifetime
- 1999-10-26 US US09/427,032 patent/US20020108682A1/en not_active Abandoned
-
2005
- 2005-05-31 US US11/139,466 patent/US20060021680A1/en not_active Abandoned
-
2009
- 2009-01-08 US US12/350,293 patent/US20100047076A1/en not_active Abandoned
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
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US5176762A (en) * | 1986-01-02 | 1993-01-05 | United Technologies Corporation | Age hardenable beta titanium alloy |
US5759484A (en) * | 1994-11-29 | 1998-06-02 | Director General Of The Technical Research And Developent Institute, Japan Defense Agency | High strength and high ductility titanium alloy |
Non-Patent Citations (3)
Title |
---|
LI, Y.G. (UNIVERSITY OF BIRMINGHAM (ENGLAND)) ET AL: "Effect of aluminium on ordering of highly stabilised beta -Ti-V-Cr alloys", MATERIALS SCIENCE AND TECHNOLOGY (AUG. 1998) 14, (8), 732-737, PHOTOMICROGRAPHS, DIFFRACTION PATTERNS, 15 REF. ISSN: 0267-0836, XP002128836 * |
LI, Y.G. (UNIVERSITY OF BIRMINGHAM (ENGLAND)) ET AL: "Structure and stability of precipitates in 500 deg C exposed Ti-25V-15Cr-xAl alloys.", ACTA MATERIALIA (1998) 46, (16), 5777-5794, PHOTOMICROGRAPHS, DIFFRACTION PATTERNS, NUMERICAL DATA, GRAPHS, 11 REF. ISSN: 1359-6454, XP002128837 * |
LI, Y.G. (UNIVERSITY OF BIRMINGHAM (UK)) ET AL: "Order-disorder transformation and deformation structure in beta TiVCrAl alloys.", ELECTRON MICROSCOPY 1998. VOLUME 2. MATERIALS SCIENCE 1 (1998), 59-60, PHOTOMICROGRAPHS, 3 REF. INSTITUTE OF PHYSICS PUBLISHING. TECHNO HOUSE, REDCLIFFE WAY, BRISTOL, BS1 6NX, UK CONFERENCE: 14TH INTERNATIONAL CONGRESS ON ELECTRON MICROSCOPY, CANCUN,, XP002128835 * |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2423089A (en) * | 2005-02-11 | 2006-08-16 | Rolls Royce Plc | Beta titanium eutectoid alloys |
WO2007029897A1 (en) * | 2005-09-09 | 2007-03-15 | Hanmaun Energy Science Institute Co. | A composition of titanium alloy strengthened by carbide precipitation and its heat treatment method |
WO2010026179A1 (en) * | 2008-09-05 | 2010-03-11 | Snecma | Method for making a circular revolution thermomechanical part including a carrier substrate containing titanium coated with steel or a superalloy, and titanium fire-resistant compressor casing for a turbine engine obtained by said method |
WO2010026181A1 (en) * | 2008-09-05 | 2010-03-11 | Snecma | Method for making a circular revolution thermomechanical part comprising a carrier substrate containing titanium coated with steel or a superalloy, and titanium fire-resistant compressor casing for a turbine engine obtained by said method |
WO2010026182A1 (en) * | 2008-09-05 | 2010-03-11 | Snecma | Method for making a circular revolution thermomechanical part comprising a carrier substrate containing titanium coated with steel or a superalloy, and titanium fire-resistant compressor casing for a turbine engine obtained by said method |
FR2935623A1 (en) * | 2008-09-05 | 2010-03-12 | Snecma | METHOD FOR MANUFACTURING CIRCULAR REVOLUTION THERMOMECHANICAL PIECE COMPRISING STEEL-COATED OR SUPERALLIATION TITANIUM-BASED CARRIER SUBSTRATE, TITANIUM-FIRE RESISTANT TURBOMACHINE COMPRESSOR CASE |
FR2935624A1 (en) * | 2008-09-05 | 2010-03-12 | Snecma | METHOD FOR MANUFACTURING CIRCULAR REVOLUTION THERMOMECHANICAL PIECE COMPRISING STEEL-COATED OR SUPERALLIATION TITANIUM-BASED CARRIER SUBSTRATE, TITANIUM-FIRE RESISTANT TURBOMACHINE COMPRESSOR CASE |
FR2935625A1 (en) * | 2008-09-05 | 2010-03-12 | Snecma | METHOD FOR MANUFACTURING A CIRCULAR REVOLUTION THERMAMECHANICAL PART COMPRISING A STEEL-COATED OR SUPERALLIATION TITANIUM-BASED CARRIER SUBSTRATE, TITANIUM-FIRE RESISTANT TURBOMACHINE COMPRESSOR CASE |
US8888448B2 (en) | 2008-09-05 | 2014-11-18 | Snecma | Method for the manufacture of a circular revolution thermomechanical part including a titanium-based load-bearing substrate lined with steel or superalloy, a turbomachine compressor housing which is resistant to titanium fire obtained according to this method |
CN109913733A (en) * | 2019-04-08 | 2019-06-21 | 大连大学 | A kind of high corrosion-resistant Ti40-xCu40Al20GdxThe preparation method of flame-retardant alloy |
Also Published As
Publication number | Publication date |
---|---|
DE69904430D1 (en) | 2003-01-23 |
DE69904430T2 (en) | 2003-10-30 |
US20100047076A1 (en) | 2010-02-25 |
US20060021680A1 (en) | 2006-02-02 |
EP1002882B1 (en) | 2002-12-11 |
US20020108682A1 (en) | 2002-08-15 |
GB9824611D0 (en) | 1999-01-06 |
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