US20050028905A1 - Process for manufacture of fasteners from titanium or a titanium alloy - Google Patents
Process for manufacture of fasteners from titanium or a titanium alloy Download PDFInfo
- Publication number
- US20050028905A1 US20050028905A1 US10/910,971 US91097104A US2005028905A1 US 20050028905 A1 US20050028905 A1 US 20050028905A1 US 91097104 A US91097104 A US 91097104A US 2005028905 A1 US2005028905 A1 US 2005028905A1
- Authority
- US
- United States
- Prior art keywords
- titanium
- intermediate form
- titanium alloy
- set forth
- alloy
- 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.)
- Abandoned
Links
- 238000000034 method Methods 0.000 title claims abstract description 29
- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 25
- 230000008569 process Effects 0.000 title claims abstract description 23
- 239000010936 titanium Substances 0.000 title claims abstract description 23
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 title claims abstract description 22
- 229910052719 titanium Inorganic materials 0.000 title claims abstract description 22
- 238000004519 manufacturing process Methods 0.000 title description 2
- 229910045601 alloy Inorganic materials 0.000 claims description 15
- 239000000956 alloy Substances 0.000 claims description 15
- 238000010438 heat treatment Methods 0.000 claims description 6
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 4
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 4
- 238000005242 forging Methods 0.000 claims description 4
- 239000012535 impurity Substances 0.000 claims description 4
- 239000001301 oxygen Substances 0.000 claims description 4
- 229910052760 oxygen Inorganic materials 0.000 claims description 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 3
- 239000001257 hydrogen Substances 0.000 claims description 3
- 229910052739 hydrogen Inorganic materials 0.000 claims description 3
- 125000004435 hydrogen atom Chemical class [H]* 0.000 claims description 3
- 238000010791 quenching Methods 0.000 claims description 3
- 230000000171 quenching effect Effects 0.000 claims description 3
- 229910021535 alpha-beta titanium Inorganic materials 0.000 claims description 2
- 229910052782 aluminium Inorganic materials 0.000 claims description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 2
- 229910052799 carbon Inorganic materials 0.000 claims description 2
- 238000001816 cooling Methods 0.000 claims description 2
- 229910052757 nitrogen Inorganic materials 0.000 claims description 2
- 229910052720 vanadium Inorganic materials 0.000 claims description 2
- LEONUFNNVUYDNQ-UHFFFAOYSA-N vanadium atom Chemical compound [V] LEONUFNNVUYDNQ-UHFFFAOYSA-N 0.000 claims description 2
- 238000003483 aging Methods 0.000 claims 1
- 238000002844 melting Methods 0.000 claims 1
- 230000008018 melting Effects 0.000 claims 1
- 239000000314 lubricant Substances 0.000 description 6
- 238000004140 cleaning Methods 0.000 description 5
- 239000000463 material Substances 0.000 description 5
- 230000032683 aging Effects 0.000 description 3
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- 239000002253 acid Substances 0.000 description 2
- 239000000356 contaminant Substances 0.000 description 2
- 238000011109 contamination Methods 0.000 description 2
- 238000005530 etching Methods 0.000 description 2
- 239000011261 inert gas Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 150000003839 salts Chemical class 0.000 description 2
- 230000000930 thermomechanical effect Effects 0.000 description 2
- 229910001040 Beta-titanium Inorganic materials 0.000 description 1
- 229910052786 argon Inorganic materials 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 239000000383 hazardous chemical Substances 0.000 description 1
- 239000001307 helium Substances 0.000 description 1
- 229910052734 helium Inorganic materials 0.000 description 1
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 1
- 238000007654 immersion Methods 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- CWQXQMHSOZUFJS-UHFFFAOYSA-N molybdenum disulfide Chemical compound S=[Mo]=S CWQXQMHSOZUFJS-UHFFFAOYSA-N 0.000 description 1
- 229910052982 molybdenum disulfide Inorganic materials 0.000 description 1
- 238000001556 precipitation Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Classifications
-
- 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
Definitions
- This invention relates to processes for making fasteners and other parts from titanium or a titanium alloy, and in particular to a process in which a titanium or titanium alloy part is solution heat treated before being thermomechanically formed.
- the titanium alloy Ti-6A1-4V has been used to make high strength fasteners, such as bolts and screws.
- the alloy is supplied in bar, rod, or wire form depending on the type and size of fastener to be made. Hitherto, the bar, rod, or wire has been supplied to the consumer in the annealed condition.
- the consumer forms the fasteners by such techniques as forging, heading, or extrusion, or a combination of those techniques.
- the fastener blanks are usually formed at an elevated temperature starting from about 1200° F. (649° C.), but usually not below about 800° F. (427° C.).
- the fastener blanks are then cleaned by immersion in a molten salt bath, which is followed with acid etching.
- the fastener blanks are next heat treated to achieve a desired strength level.
- the known heat treatment is a two-stage treatment.
- the parts are solution treated, typically in an inert atmosphere, at about 1650 to 1775° F. (899 to 968° C.) for about 1 hour and then water quenched.
- the parts are precipitation hardened by an aging treatment at about 800 to 1050° F. (427 to 566° C.) for 2 to 8 hours and then cooled in an inert gas or in a vacuum. Hitherto, the aging step has been performed directly after the solution-treating step.
- the solution treatment is the most problematic step in the heat treatment cycle because during solution treatment contamination of the fasteners must be prevented. Titanium and its alloys are very reactive, especially at elevated temperatures such as those typically used for solution treatment. Any foreign material which comes into contact with the titanium or titanium alloy during solution heat treatment will result in contamination of the material. Common sources of foreign material in the solution treating process are contaminants in the furnace atmosphere or residual processing materials such as lubricants on the surfaces of the titanium blanks. In order to avoid the problems associated with the presence of such contaminants, special furnace atmospheres must be maintained and the fasteners must be thoroughly cleaned before they are placed in the heat treating furnace. Cleaning of the fasteners presents another problem because it involves the use of aggressive chemicals which pose environmental hazards and disposal concerns. Additionally, the cleaning operation can change the chemistry of the fasteners, such as by adding hydrogen, and can alter the dimensions of the fastener by dissolving metal from the blank. These problems make the cleaning step unreliable, time consuming, and costly.
- Fasteners are also manufactured by direct machining of solution treated titanium alloy bar. The machined fasteners are then age hardened. However, that process does not involve a forging operation. Therefore, it is not susceptible to the problems discussed above.
- Beta titanium alloys such as Ti 3-8-6-4-4 and others, are supplied in the solution treated condition for forming into fasteners. The fasteners are then aged to achieve the desired properties.
- the beta alloys there are significant metallurgical differences between the beta alloys and the other known titanium alloys such as alpha, near-alpha, an alpha-beta alloys.
- a process of making parts from titanium and titanium alloy wire, rod, or bar is provided.
- titanium means unalloyed titanium as well as alpha, near-alpha, and alpha-beta titanium alloys.
- the process includes the step of preparing an intermediate form of titanium.
- the intermediate form is solution treated under conditions of temperature and time that are sufficient to produce a desired level of strength when the alloy is subsequently age hardened.
- the solution treated material is then formed into a desired part or component, such as a fastener or a preform for a fastener.
- the forming step is conducted with the alloy at an elevated temperature and the as-formed part is rapidly cooled from the finish temperature. Subsequent to the forming step, the part is age hardened to achieve the desired level of strength and hardness.
- an intermediate form of a titanium alloy is prepared by any known method.
- Preferred intermediate forms include wire, rod, and bar.
- the Ti-6A1-4V alloy is a known titanium alloy that contains about 6 weight percent (%) aluminum, about 4% vanadium, and the balance is titanium and usual impurities.
- the impurities present in the alloy are restricted such that the alloy contains not more than about 0.10% carbon, not more than about 0.05% nitrogen, not more than about 0.0125% hydrogen, and not more than about 0.20% oxygen.
- the oxygen is preferably limited to about 0.14-0.17%.
- the method by which the intermediate form is made is not critical and any of the known methods for making titanium alloy wire, rod, or bar may be used.
- the intermediate form of the titanium alloy is then solution treated at about 1650-1775° F. (899-968° C.) for a time of at least about 1 minute up to about 2 hours, and then water quenched.
- the intermediate form is heated at the solution temperature for about 1 hour.
- the intermediate form may be coated with a lubricant.
- the preferred lubricant is a dry film lubricant, which consists of graphite and molybdenum disulfide. Other lubricants that are known to those skilled in the art for similar purposes may also be suitable.
- the lubricated wire, rod, or bar is then subjected to thermomechanical working to form the desired part.
- the preferred forming operation is forging, and heading is particularly preferred for making small parts from wire or rod.
- extruding techniques can be used in connection with the preparation of parts by this process.
- the intermediate form Prior to forming, the intermediate form is cut to a starting size, heated to an elevated starting temperature, and then mechanically worked to the desired size and shape.
- the elevated starting temperature for the thermomechanical forming is selected to be as close to the solution treating temperature as practicable.
- a lower forming temperature can be used for applications where adequate lubrication, extended die life, or dimensional control of the part or preform is important.
- the parts are formed from a starting temperature of about 1600° F.
- the as-formed parts are rapidly cooled from the finishing temperature, preferably by water quenching.
- the as-formed parts are then age hardened, preferably in a vacuum heat treating furnace.
- the parts may also be aged in an inert atmosphere such as argon or helium. It is also expected that the parts can be aged in air.
- the heat-treated parts are then ground or machined as necessary to final dimension and shape.
Landscapes
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Physics & Mathematics (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Forging (AREA)
- Solid-Phase Diffusion Into Metallic Material Surfaces (AREA)
- Manufacture And Refinement Of Metals (AREA)
- Inorganic Compounds Of Heavy Metals (AREA)
Abstract
A process for making parts from titanium or a titanium alloy is disclosed. The process includes the step of preparing an intermediate form of titanium or a titanium alloy. The intermediate form is then solution heat treated under conditions of temperature and time that are selected to produce a desired level of strength when the titanium or titanium alloy part is subsequently age hardened. The solution treated intermediate form is then thermomechanically formed into a desired part or a preform for a desired part. The part or preform is then age-hardened under conditions of temperature and time that are selected to produced the desired level of strength in the finished part.
Description
- This application claims the benefit of priority of U.S. Provisional Application Ser. No. 60/492,526, filed on Aug. 5, 2003.
- This invention relates to processes for making fasteners and other parts from titanium or a titanium alloy, and in particular to a process in which a titanium or titanium alloy part is solution heat treated before being thermomechanically formed.
- The titanium alloy Ti-6A1-4V has been used to make high strength fasteners, such as bolts and screws. The alloy is supplied in bar, rod, or wire form depending on the type and size of fastener to be made. Hitherto, the bar, rod, or wire has been supplied to the consumer in the annealed condition. The consumer forms the fasteners by such techniques as forging, heading, or extrusion, or a combination of those techniques. The fastener blanks are usually formed at an elevated temperature starting from about 1200° F. (649° C.), but usually not below about 800° F. (427° C.). The fastener blanks are then cleaned by immersion in a molten salt bath, which is followed with acid etching.
- The fastener blanks are next heat treated to achieve a desired strength level. The known heat treatment is a two-stage treatment. In the first stage, the parts are solution treated, typically in an inert atmosphere, at about 1650 to 1775° F. (899 to 968° C.) for about 1 hour and then water quenched. In the second stage of the heat treatment, the parts are precipitation hardened by an aging treatment at about 800 to 1050° F. (427 to 566° C.) for 2 to 8 hours and then cooled in an inert gas or in a vacuum. Hitherto, the aging step has been performed directly after the solution-treating step.
- The solution treatment is the most problematic step in the heat treatment cycle because during solution treatment contamination of the fasteners must be prevented. Titanium and its alloys are very reactive, especially at elevated temperatures such as those typically used for solution treatment. Any foreign material which comes into contact with the titanium or titanium alloy during solution heat treatment will result in contamination of the material. Common sources of foreign material in the solution treating process are contaminants in the furnace atmosphere or residual processing materials such as lubricants on the surfaces of the titanium blanks. In order to avoid the problems associated with the presence of such contaminants, special furnace atmospheres must be maintained and the fasteners must be thoroughly cleaned before they are placed in the heat treating furnace. Cleaning of the fasteners presents another problem because it involves the use of aggressive chemicals which pose environmental hazards and disposal concerns. Additionally, the cleaning operation can change the chemistry of the fasteners, such as by adding hydrogen, and can alter the dimensions of the fastener by dissolving metal from the blank. These problems make the cleaning step unreliable, time consuming, and costly.
- The known solution treating operations are also troublesome because the process often results in the final parts being unacceptable. In some cases the parts become contaminated with impurities because of less than desirable furnace atmospheres or residual lubricants on the parts. In other cases the parts have poor mechanical properties because of inadequate quenching. Moreover, parts can become distorted or they may stick together during solution treatment, or they may become bent or develop flat spots. It is also a fact that solution heat treating equipment is expensive and costly to operate for parts manufacturers. Elimination of the need to solution treat the headed fastener blanks, along with the associated relaxation of cleaning requirements, would permit significant improvements in the efficiency of the manufacturing process and greater uniformity of product quality.
- Fasteners are also manufactured by direct machining of solution treated titanium alloy bar. The machined fasteners are then age hardened. However, that process does not involve a forging operation. Therefore, it is not susceptible to the problems discussed above.
- Beta titanium alloys, such as Ti 3-8-6-4-4 and others, are supplied in the solution treated condition for forming into fasteners. The fasteners are then aged to achieve the desired properties. However, there are significant metallurgical differences between the beta alloys and the other known titanium alloys such as alpha, near-alpha, an alpha-beta alloys.
- In accordance with the present invention a process of making parts from titanium and titanium alloy wire, rod, or bar is provided. Here and throughout the remainder of this specification the term titanium means unalloyed titanium as well as alpha, near-alpha, and alpha-beta titanium alloys. The process includes the step of preparing an intermediate form of titanium. The intermediate form is solution treated under conditions of temperature and time that are sufficient to produce a desired level of strength when the alloy is subsequently age hardened. The solution treated material is then formed into a desired part or component, such as a fastener or a preform for a fastener. The forming step is conducted with the alloy at an elevated temperature and the as-formed part is rapidly cooled from the finish temperature. Subsequent to the forming step, the part is age hardened to achieve the desired level of strength and hardness.
- In a preferred embodiment of the process according to the present invention, an intermediate form of a titanium alloy, preferably Ti-6A1-4V, is prepared by any known method. Preferred intermediate forms include wire, rod, and bar. The Ti-6A1-4V alloy is a known titanium alloy that contains about 6 weight percent (%) aluminum, about 4% vanadium, and the balance is titanium and usual impurities. The impurities present in the alloy are restricted such that the alloy contains not more than about 0.10% carbon, not more than about 0.05% nitrogen, not more than about 0.0125% hydrogen, and not more than about 0.20% oxygen. In the preferred titanium alloy used in this process, the oxygen is preferably limited to about 0.14-0.17%. The method by which the intermediate form is made is not critical and any of the known methods for making titanium alloy wire, rod, or bar may be used.
- The intermediate form of the titanium alloy is then solution treated at about 1650-1775° F. (899-968° C.) for a time of at least about 1 minute up to about 2 hours, and then water quenched. Preferably, the intermediate form is heated at the solution temperature for about 1 hour. Prior to forming a desired product from the intermediate form, the intermediate form may be coated with a lubricant. The preferred lubricant is a dry film lubricant, which consists of graphite and molybdenum disulfide. Other lubricants that are known to those skilled in the art for similar purposes may also be suitable.
- The lubricated wire, rod, or bar is then subjected to thermomechanical working to form the desired part. The preferred forming operation is forging, and heading is particularly preferred for making small parts from wire or rod. For some applications extruding techniques can be used in connection with the preparation of parts by this process. Prior to forming, the intermediate form is cut to a starting size, heated to an elevated starting temperature, and then mechanically worked to the desired size and shape. The elevated starting temperature for the thermomechanical forming is selected to be as close to the solution treating temperature as practicable. A lower forming temperature can be used for applications where adequate lubrication, extended die life, or dimensional control of the part or preform is important. Preferably, the parts are formed from a starting temperature of about 1600° F. (871° C.), but preferably not below about 1300° F. (704° C.) or 1200° F. (649° C.). Lower finishing temperatures may be used under appropriate circumstances. However, it is expected that the finishing temperature would, in any event, not be below about 800° F. (427° C.). The as-formed parts are rapidly cooled from the finishing temperature, preferably by water quenching.
- The as-formed parts are then age hardened, preferably in a vacuum heat treating furnace. The parts may also be aged in an inert atmosphere such as argon or helium. It is also expected that the parts can be aged in air. When the parts are aged in a vacuum furnace, it may be preferable to clean the parts to prevent their being contaminated in the heat treating furnace. Such cleaning is accomplished by first immersing the parts in a molten salt bath and then acid etching. Aging is conducted at a temperature of about 800 to 1050° F. (427 to 566° C.) for about 2 to 8 hours, followed by cooling in inert gas or in a vacuum.
- The heat-treated parts are then ground or machined as necessary to final dimension and shape.
- It will be recognized by those skilled in the art that changes or modifications may be made to the above-described embodiment without departing from the broad inventive concept of the invention. It should therefore be understood that this invention is not limited to the particular embodiment described herein, but is intended to include all changes and modifications that are within the scope and spirit of the invention as set forth in the following claims.
Claims (10)
1. A process for making parts from titanium or a titanium alloy comprising the steps of:
preparing an intermediate form of titanium or of a titanium alloy selected from the group consisting of an alpha alloy, a near-alpha alloy, and an alpha-beta alloy; then
solution heat treating the intermediate form under conditions of temperature and time that are selected to produce a desired level of strength when the titanium or titanium alloy are subsequently age hardened; then
thermomechanically forming the solution treated intermediate form into a desired part or a preform for a desired part; and then
age hardening the as-formed part or preform under conditions of temperature and time that are selected to produced the desired level of strength.
2. The process as set forth in claim 1 wherein the intermediate form is prepared from an alpha-beta titanium alloy.
3. The process as set forth in claim 1 wherein the intermediate form is prepared from a titanium alloy comprising about 6% aluminum, about 4% vanadium, and the balance titanium and usual impurities.
4. The process as set forth in claim 1 wherein the step of preparing the intermediate form comprises the step of forming the titanium alloy into an elongated form selected from the group consisting of wire, rod, and bar.
5. The process as set forth in claim 1 wherein the step of thermomechanically forming the solution treated intermediate form comprises the steps of cutting the elongated form into pieces having a substantially uniform length, heating the pieces to an elevated temperature, and then forming the desired part or preform by a forming operation selected from the group consisting of forging, heading, extruding, and a combination thereof.
6. The process as set forth in claim 5 wherein the step of thermomechanically forming the solution treated intermediate form comprises the step of rapidly cooling the part from the elevated temperature after said forming step.
7. The process as set forth in claim 1 wherein the step of preparing the intermediate form of titanium or the titanium alloy comprises the step of preparing the titanium or titanium alloy such that it contains not more than about 0.10% carbon, not more than about 0.05% nitrogen, not more than about 0.0125% hydrogen, and not more than about 0.20% oxygen.
8. The process as set forth in claim 7 wherein the step of preparing the titanium or titanium alloy comprises the step of controlling the melting of the titanium or titanium alloy such that it contains not more than about 0.17% oxygen.
9. The process as set forth in claim 1 , wherein the step of solution treating the intermediate form comprises the step of heating the intermediate form at a temperature of about 1650-1775° F. (899-968° C.) for at least about 1 minute up to about 2 hours, and then quenching the intermediate form in water.
10. The process as set forth in claim 1 wherein the step of thermomechanically forming the solution treated intermediate form comprises the step of mechanically working the intermediate form at a temperature of about 1600-800° F. (871-427° C.).
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/910,971 US20050028905A1 (en) | 2003-08-05 | 2004-08-04 | Process for manufacture of fasteners from titanium or a titanium alloy |
US11/847,401 US8845832B2 (en) | 2003-08-05 | 2007-08-30 | Process for manufacture of fasteners from a titanium alloy |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US49252603P | 2003-08-05 | 2003-08-05 | |
US10/910,971 US20050028905A1 (en) | 2003-08-05 | 2004-08-04 | Process for manufacture of fasteners from titanium or a titanium alloy |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/847,401 Continuation-In-Part US8845832B2 (en) | 2003-08-05 | 2007-08-30 | Process for manufacture of fasteners from a titanium alloy |
Publications (1)
Publication Number | Publication Date |
---|---|
US20050028905A1 true US20050028905A1 (en) | 2005-02-10 |
Family
ID=34193128
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/910,971 Abandoned US20050028905A1 (en) | 2003-08-05 | 2004-08-04 | Process for manufacture of fasteners from titanium or a titanium alloy |
Country Status (8)
Country | Link |
---|---|
US (1) | US20050028905A1 (en) |
EP (1) | EP1654393B1 (en) |
JP (1) | JP2007501327A (en) |
AT (1) | ATE378436T1 (en) |
CA (1) | CA2535038C (en) |
DE (1) | DE602004010138T2 (en) |
RU (1) | RU2368696C2 (en) |
WO (1) | WO2005017225A1 (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2007051637A1 (en) * | 2005-11-03 | 2007-05-10 | Hempel, Robert P. | Cold-workable ti alloy |
US10808298B2 (en) | 2015-01-12 | 2020-10-20 | Ati Properties Llc | Titanium alloy |
US11111552B2 (en) | 2013-11-12 | 2021-09-07 | Ati Properties Llc | Methods for processing metal alloys |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2741047C1 (en) * | 2019-12-06 | 2021-01-22 | Общество с ограниченной ответственностью "Би Концепт", (ООО "Би Концепт") | Protective-lubricant material for hot metal forming |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2804409A (en) * | 1956-02-06 | 1957-08-27 | Titanium Metals Corp | Heat treating titanium-base alloy products |
US5032189A (en) * | 1990-03-26 | 1991-07-16 | The United States Of America As Represented By The Secretary Of The Air Force | Method for refining the microstructure of beta processed ingot metallurgy titanium alloy articles |
US5118363A (en) * | 1988-06-07 | 1992-06-02 | Aluminum Company Of America | Processing for high performance TI-6A1-4V forgings |
US5173134A (en) * | 1988-12-14 | 1992-12-22 | Aluminum Company Of America | Processing alpha-beta titanium alloys by beta as well as alpha plus beta forging |
US6190473B1 (en) * | 1999-08-12 | 2001-02-20 | The Boenig Company | Titanium alloy having enhanced notch toughness and method of producing same |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH03130351A (en) * | 1989-10-16 | 1991-06-04 | Nippon Steel Corp | Production of titanium and titanium alloy having fine and equiaxial structure |
EP0425461A1 (en) * | 1989-10-27 | 1991-05-02 | Sandvik Special Metals Corp. | Continuous solution heat treatment of precipitation hardenable alloys |
-
2004
- 2004-08-04 AT AT04780090T patent/ATE378436T1/en active
- 2004-08-04 JP JP2006522698A patent/JP2007501327A/en active Pending
- 2004-08-04 CA CA2535038A patent/CA2535038C/en not_active Expired - Fee Related
- 2004-08-04 DE DE602004010138T patent/DE602004010138T2/en active Active
- 2004-08-04 WO PCT/US2004/025192 patent/WO2005017225A1/en active IP Right Grant
- 2004-08-04 RU RU2006106723/02A patent/RU2368696C2/en not_active IP Right Cessation
- 2004-08-04 US US10/910,971 patent/US20050028905A1/en not_active Abandoned
- 2004-08-04 EP EP04780090A patent/EP1654393B1/en not_active Not-in-force
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2804409A (en) * | 1956-02-06 | 1957-08-27 | Titanium Metals Corp | Heat treating titanium-base alloy products |
US5118363A (en) * | 1988-06-07 | 1992-06-02 | Aluminum Company Of America | Processing for high performance TI-6A1-4V forgings |
US5173134A (en) * | 1988-12-14 | 1992-12-22 | Aluminum Company Of America | Processing alpha-beta titanium alloys by beta as well as alpha plus beta forging |
US5032189A (en) * | 1990-03-26 | 1991-07-16 | The United States Of America As Represented By The Secretary Of The Air Force | Method for refining the microstructure of beta processed ingot metallurgy titanium alloy articles |
US6190473B1 (en) * | 1999-08-12 | 2001-02-20 | The Boenig Company | Titanium alloy having enhanced notch toughness and method of producing same |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2007051637A1 (en) * | 2005-11-03 | 2007-05-10 | Hempel, Robert P. | Cold-workable ti alloy |
US11111552B2 (en) | 2013-11-12 | 2021-09-07 | Ati Properties Llc | Methods for processing metal alloys |
US10808298B2 (en) | 2015-01-12 | 2020-10-20 | Ati Properties Llc | Titanium alloy |
US11319616B2 (en) | 2015-01-12 | 2022-05-03 | Ati Properties Llc | Titanium alloy |
US11851734B2 (en) | 2015-01-12 | 2023-12-26 | Ati Properties Llc | Titanium alloy |
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RU2006106723A (en) | 2007-09-20 |
EP1654393A1 (en) | 2006-05-10 |
JP2007501327A (en) | 2007-01-25 |
DE602004010138T2 (en) | 2008-08-28 |
EP1654393B1 (en) | 2007-11-14 |
RU2368696C2 (en) | 2009-09-27 |
WO2005017225A1 (en) | 2005-02-24 |
DE602004010138D1 (en) | 2007-12-27 |
ATE378436T1 (en) | 2007-11-15 |
CA2535038A1 (en) | 2005-02-24 |
CA2535038C (en) | 2012-09-25 |
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