GB1122912A - Improvements relating to aluminum base alloy plates - Google Patents
Improvements relating to aluminum base alloy platesInfo
- Publication number
- GB1122912A GB1122912A GB4868/66A GB486866A GB1122912A GB 1122912 A GB1122912 A GB 1122912A GB 4868/66 A GB4868/66 A GB 4868/66A GB 486866 A GB486866 A GB 486866A GB 1122912 A GB1122912 A GB 1122912A
- Authority
- GB
- United Kingdom
- Prior art keywords
- biscuit
- base alloy
- slab
- hours
- room temperature
- 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.)
- Expired
Links
- 239000000956 alloy Substances 0.000 title abstract 2
- 229910045601 alloy Inorganic materials 0.000 title abstract 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 title abstract 2
- 229910052782 aluminium Inorganic materials 0.000 title abstract 2
- 239000011777 magnesium Substances 0.000 abstract 4
- 235000015895 biscuits Nutrition 0.000 abstract 3
- 229910052749 magnesium Inorganic materials 0.000 abstract 3
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 abstract 1
- 230000032683 aging Effects 0.000 abstract 1
- 239000004411 aluminium Substances 0.000 abstract 1
- 239000012535 impurity Substances 0.000 abstract 1
- 238000004519 manufacturing process Methods 0.000 abstract 1
- 238000003303 reheating Methods 0.000 abstract 1
- 230000035882 stress Effects 0.000 abstract 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
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
- C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21B—ROLLING OF METAL
- B21B3/00—Rolling materials of special alloys so far as the composition of the alloy requires or permits special rolling methods or sequences ; Rolling of aluminium, copper, zinc or other non-ferrous metals
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Forging (AREA)
Abstract
A method of making an aluminium base alloy plate comprises providing a body containing 3% - 6% Cu, 0.8% - 3% Mg and 0.3% - 1% Mn, apart from impurities, the balance being Al and the magnesium content being governed by the relation: Mg min = 0.32 Cu when Mn is not greater than 0.5% Mg min = 0.2 + 0.32 Cu - 0.4 Mn when Mn is greater than 0.5%, the body having a length to base ratio of at least 2:1. The body is heated to at least 800 DEG F. to homogenize its internal structure and is then forged a biscuit having a height of not more than 40% of the original body length. The biscuit is reheated to 600 DEG - 900 DEG F. flattened slightly on its sides and further compressed in the original direction into a slab having a thickness of not more than 3/4 of the biscuit height. The slab may then be cooled to room temperature. Subsequently it is hot rolled at 600 DEG - 900 DEG F. to the final plate thickness of 1" - 8". If the stock cools excessively during a hot working operation, it may be interrupted for reheating. To develop high strength and hardness, the plate is solution heat-treated at 800 DEG - 950 DEG F. for 1-12 hours, then quenched and artificially aged at 300 DEG - 400 DEG F. for 6 - 24 hours. The aging step is preferably preceded by stress relief comprising applying a permanent stretch of 1 1/2 - 3% at substantially room temperature.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US430743A US3333989A (en) | 1965-02-05 | 1965-02-05 | Aluminum base alloy plate |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1122912A true GB1122912A (en) | 1968-08-07 |
Family
ID=23708835
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB4868/66A Expired GB1122912A (en) | 1965-02-05 | 1966-02-03 | Improvements relating to aluminum base alloy plates |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US3333989A (en) |
| DE (1) | DE1533497B1 (en) |
| GB (1) | GB1122912A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0038605A1 (en) * | 1980-04-18 | 1981-10-28 | The Boeing Company | Method of producing a plate product or an extruded product from an aluminium alloy |
| EP0473122A1 (en) * | 1990-08-27 | 1992-03-04 | Aluminum Company Of America | Damage tolerant aluminum alloy sheet for aircraft skin |
| EP0489408A1 (en) * | 1990-12-03 | 1992-06-10 | Aluminum Company Of America | Aircraft sheet |
| US5213639A (en) * | 1990-08-27 | 1993-05-25 | Aluminum Company Of America | Damage tolerant aluminum alloy products useful for aircraft applications such as skin |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4600556A (en) * | 1983-08-08 | 1986-07-15 | Inco Alloys International, Inc. | Dispersion strengthened mechanically alloyed Al-Mg-Li |
| CN108531836B (en) * | 2018-05-09 | 2019-12-20 | 湖南人文科技学院 | Heat treatment technology for preparing high-performance low-residual-stress aluminum alloy |
| CN108746447B (en) * | 2018-05-16 | 2020-03-17 | 江苏理工学院 | Manufacturing process of high-strength corrosion-resistant aluminum alloy forging |
| CN108642410B (en) * | 2018-05-16 | 2020-01-03 | 江苏理工学院 | Process method for improving comprehensive mechanical property of aluminum alloy plate |
| CN108890218B (en) * | 2018-05-16 | 2020-02-14 | 江苏理工学院 | Manufacturing process of high-strength heat-resistant aluminum alloy forging |
| CN108687160B (en) * | 2018-05-16 | 2020-02-14 | 江苏理工学院 | Aluminum alloy plate treatment process |
| CN113182379A (en) * | 2021-07-01 | 2021-07-30 | 中国航发北京航空材料研究院 | Preparation method of aluminum alloy plate |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2522575A (en) * | 1948-01-23 | 1950-09-19 | Rolls Royce | Forging aluminum alloy |
| US2671559A (en) * | 1949-02-03 | 1954-03-09 | Rosenkranz Wilhelm | Process of press forging metal alloys |
| US3265493A (en) * | 1963-05-31 | 1966-08-09 | Dow Chemical Co | Aluminum base pellet alloys containing copper and magnesium and process for producing the same |
-
1965
- 1965-02-05 US US430743A patent/US3333989A/en not_active Expired - Lifetime
-
1966
- 1966-02-03 GB GB4868/66A patent/GB1122912A/en not_active Expired
- 1966-02-04 DE DE19661533497D patent/DE1533497B1/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0038605A1 (en) * | 1980-04-18 | 1981-10-28 | The Boeing Company | Method of producing a plate product or an extruded product from an aluminium alloy |
| EP0473122A1 (en) * | 1990-08-27 | 1992-03-04 | Aluminum Company Of America | Damage tolerant aluminum alloy sheet for aircraft skin |
| US5213639A (en) * | 1990-08-27 | 1993-05-25 | Aluminum Company Of America | Damage tolerant aluminum alloy products useful for aircraft applications such as skin |
| EP0489408A1 (en) * | 1990-12-03 | 1992-06-10 | Aluminum Company Of America | Aircraft sheet |
Also Published As
| Publication number | Publication date |
|---|---|
| US3333989A (en) | 1967-08-01 |
| DE1533497B1 (en) | 1970-12-10 |
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