US2383511A - Method of making same - Google Patents
Method of making same Download PDFInfo
- Publication number
- US2383511A US2383511A US2383511DA US2383511A US 2383511 A US2383511 A US 2383511A US 2383511D A US2383511D A US 2383511DA US 2383511 A US2383511 A US 2383511A
- Authority
- US
- United States
- Prior art keywords
- alloy
- aluminum
- sheet
- composite
- making same
- 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 - Lifetime
Links
- 238000004519 manufacturing process Methods 0.000 title description 6
- 239000000956 alloy Substances 0.000 description 30
- 229910045601 alloy Inorganic materials 0.000 description 28
- REDXJYDRNCIFBQ-UHFFFAOYSA-N aluminium(3+) Chemical class [Al+3] REDXJYDRNCIFBQ-UHFFFAOYSA-N 0.000 description 22
- 229910000838 Al alloy Inorganic materials 0.000 description 18
- 229910052782 aluminium Inorganic materials 0.000 description 16
- 239000002131 composite material Substances 0.000 description 16
- FYYHWMGAXLPEAU-UHFFFAOYSA-N magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 12
- 229910052749 magnesium Inorganic materials 0.000 description 12
- 239000011777 magnesium Substances 0.000 description 12
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminum Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 10
- RYGMFSIKBFXOCR-UHFFFAOYSA-N copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 8
- 229910052802 copper Inorganic materials 0.000 description 8
- 239000010949 copper Substances 0.000 description 8
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 8
- 229910052710 silicon Inorganic materials 0.000 description 8
- 239000010703 silicon Substances 0.000 description 8
- 238000005299 abrasion Methods 0.000 description 6
- VYZAMTAEIAYCRO-UHFFFAOYSA-N chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 6
- 229910052804 chromium Inorganic materials 0.000 description 6
- 239000011651 chromium Substances 0.000 description 6
- PWHULOQIROXLJO-UHFFFAOYSA-N manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 description 6
- 229910052748 manganese Inorganic materials 0.000 description 6
- 239000011572 manganese Substances 0.000 description 6
- 230000005484 gravity Effects 0.000 description 4
- 238000010438 heat treatment Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- -1 aluminum silicon Chemical compound 0.000 description 2
- 238000005098 hot rolling Methods 0.000 description 2
- 238000010791 quenching Methods 0.000 description 2
- 230000000171 quenching Effects 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/01—Layered products comprising a layer of metal all layers being exclusively metallic
- B32B15/016—Layered products comprising a layer of metal all layers being exclusively metallic all layers being formed of aluminium or aluminium alloys
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
- B23K20/22—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating taking account of the properties of the materials to be welded
- B23K20/233—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating taking account of the properties of the materials to be welded without ferrous layer
- B23K20/2336—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating taking account of the properties of the materials to be welded without ferrous layer both layers being aluminium
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12736—Al-base component
- Y10T428/12764—Next to Al-base component
Definitions
- the present invention has for its object to provide an aluminum-alloy sheet composed of layers of aluminum alloys of difierent characteristics and which are mutually resistant to bonding.
- certain aluminum alloys have marked resistance to fatigue and hav relatively high yield strength, and yet do not possess substantial resistance to abrasion in handling.
- Other aluminum alloys lack the stated or other qualities and, at the same time, are highly resistant to abrasion.
- it has been proposed toroll together assembled slabs of the alloys in order to produce a composite sheet, but this was established as impractical because of poor adherence.
- i represents a greatly enlarged alloy sheet, as, for example, of aluminum, copper, manganese and magnesium, and 2 indicates the commercially pure aluminum bond, 3 representing an alloy sheet, as, for example, aluminum silicon, magnesium and chromium.
- a basic alloy slab I may employ aluminum alloyed with copper, manganese and magnesium, such as in the approximate percentages of 4.2% copper, 0.6% manganese, and 1.5% magnesium.
- This alloy has a specific gravity of 2.76 and weight in pounds per cubic inch of 0.100. It is therefore light, and
- one primary characteristic of the alloy is its resistance to fatigue, which remains substantially constant, the
- I may employ aluminum alloyed with silicon, magnesium and chromium such as in the approximatepercentages 0.7% silicon, 1.25% magnesium and 0.25% chromium.
- alloy material has a weight in pounds per cubic inch of 0.007 and a specific gravity of 2.69, with a hardness exceeding 40 Brinell in annealed state.
- minum contains small percentages oriron, silicon and copper, the latter two materials being in lesser degree and the total of these common alloys being upwards of 1%.
- commercially pure aluminum may be employed for my bonding material.
- a' s'calped ingot of the so-called basic alloy which may be of any desired thickness, such as 5", may have applied to the opposite faces thereof thinner plates or sheets such asplates of 0.250" composed of the associated Intermediate the ingot and each of the associated plates, I interpose a sheet of commercially pure aluminum which may be .020" thick, that thickness being sufllcient to insure exceedingly thin but uniform bonding layers in the final composite sheet.
- the composite body is then rolled down to the thickness desired for the specific purpose as, for example, one of the customary sheet thicknesses extensively used in the aircraft industry.
- the layers are permanently bonded into an integral structure.
- the aluminum-alloy sheet thus produced embodies in one structur the advantageous qualities oi both the base and the associated alloy structures, the surface exposed alloy associated with the basic alloy-being resistant to abrasion and possessing other inherent characteristics, so that the composite body has marked advantages over a sheet made of the composite alloys, according to usual practice.
- a composite metallic sheet comprising a plurality of hard aluminum-alloy layers exceeding 40 Brinell in hardness, and intermediate each Aug. 28', 1945.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Laminated Bodies (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
Description
Patented Aug. 28, 1945 METHOD OF MAKING SAME Richard s. Reynolds, Richmond, Va.
Application November 1, 1941, Serial No. 417,578
. 3 Claims.
The present invention has for its object to provide an aluminum-alloy sheet composed of layers of aluminum alloys of difierent characteristics and which are mutually resistant to bonding. As an example, certain aluminum alloys have marked resistance to fatigue and hav relatively high yield strength, and yet do not possess substantial resistance to abrasion in handling. Other aluminum alloys lack the stated or other qualities and, at the same time, are highly resistant to abrasion. In order to combine in one structure the advantage of both alloys, it has been proposed toroll together assembled slabs of the alloys in order to produce a composite sheet, but this was established as impractical because of poor adherence.
I have discovered a method of overcoming the problem which has heretofore prevented the commercial production of such composite aluminu alloy sheets.
In the drawing I have diagrammatically shown a composite aluminum alloy sheet in which i represents a greatly enlarged alloy sheet, as, for example, of aluminum, copper, manganese and magnesium, and 2 indicates the commercially pure aluminum bond, 3 representing an alloy sheet, as, for example, aluminum silicon, magnesium and chromium.
As a specific example, for a basic alloy slab I may employ aluminum alloyed with copper, manganese and magnesium, such as in the approximate percentages of 4.2% copper, 0.6% manganese, and 1.5% magnesium. This alloy has a specific gravity of 2.76 and weight in pounds per cubic inch of 0.100. It is therefore light, and
it has initial relatively high'yield strength. When annealed, it has a hardness of 42 Brinell which is very substantially increased by heat treatment alloy specified above.
and, quenching and by hot rolling. one primary characteristic of the alloy is its resistance to fatigue, which remains substantially constant, the
factor not beingv substantially changed by heat treatment.
Continuing the specific example, for-the associated alloy slab or slabs, I may employ aluminum alloyed with silicon, magnesium and chromium such as in the approximatepercentages 0.7% silicon, 1.25% magnesium and 0.25% chromium.
I Such. alloy material'has a weight in pounds per cubic inch of 0.007 and a specific gravity of 2.69, with a hardness exceeding 40 Brinell in annealed state.
minum contains small percentages oriron, silicon and copper, the latter two materials being in lesser degree and the total of these common alloys being upwards of 1%. Thus commercially pure" aluminum may be employed for my bonding material. 1
Particularly, a' s'calped ingot of the so-called basic alloy, which may be of any desired thickness, such as 5", may have applied to the opposite faces thereof thinner plates or sheets such asplates of 0.250" composed of the associated Intermediate the ingot and each of the associated plates, I interpose a sheet of commercially pure aluminum which may be .020" thick, that thickness being sufllcient to insure exceedingly thin but uniform bonding layers in the final composite sheet.
The composite body, generally heated as in standard ingot rolling practice, is then rolled down to the thickness desired for the specific purpose as, for example, one of the customary sheet thicknesses extensively used in the aircraft industry. By following this method, I have found that the layers are permanently bonded into an integral structure. In the specific example, the aluminum-alloy sheet thus produced embodies in one structur the advantageous qualities oi both the base and the associated alloy structures, the surface exposed alloy associated with the basic alloy-being resistant to abrasion and possessing other inherent characteristics, so that the composite body has marked advantages over a sheet made of the composite alloys, according to usual practice.
It will be understood that the specific example is used to illustrate the invention, and the invention is capable of wide application to the association of aluminum-alloy bodies which resist ins a plurality oihard aluminum-alloy layers exceeding 40 Brinell in hardness, the layers being Between the basic and each associated slab, I
characterized by resistance to mutual bonding under pressure, and intermediate each two layers a' toll of commercially pure aluminum bonding the assembly into a permanent integral sheet structure, the aluminum bonding containing less than 1% silicon.
2. A composite metallic sheet comprising a plurality of hard aluminum-alloy layers exceeding 40 Brinell in hardness, and intermediate each Aug. 28', 1945.
Filed May 2'7, 1944 Z 5 R Y ma m N R w Mm m m: b m m M v w
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2383511A true US2383511A (en) | 1945-08-28 |
Family
ID=3434746
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US2383511D Expired - Lifetime US2383511A (en) | Method of making same |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US2383511A (en) |
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2602413A (en) * | 1948-08-13 | 1952-07-08 | Aluminum Co Of America | Aluminous brazing product and method of brazing |
| US2612682A (en) * | 1946-04-05 | 1952-10-07 | Reynolds Metals Co | Method of cladding a copper-base metal to an aluminum core |
| US2821014A (en) * | 1951-05-31 | 1958-01-28 | Aluminum Co Of America | Composite aluminous metal article |
| US2990609A (en) * | 1958-03-11 | 1961-07-04 | Ohmi Rihei | Casting made of aluminum or aluminum alloy |
| US3054176A (en) * | 1959-07-06 | 1962-09-18 | Reynolds Metals Co | Forming system |
| US3168381A (en) * | 1960-09-01 | 1965-02-02 | Kaiser Aluminium Chem Corp | Aluminum alloy and article |
| US3226808A (en) * | 1960-05-26 | 1966-01-04 | Reynolds Metals Co | Method of making refrigerator evaporators or the like |
| US3240269A (en) * | 1965-06-02 | 1966-03-15 | Reynolds Metals Co | Composite refrigerator evaporator |
| US3312536A (en) * | 1963-06-19 | 1967-04-04 | Olin Mathieson | Composite aluminum alloy |
| US3312535A (en) * | 1963-07-16 | 1967-04-04 | Aluminum Co Of America | Aluminum reflectors |
| US3490124A (en) * | 1967-02-07 | 1970-01-20 | Texas Instruments Inc | Composite metal layers for fabricating deep drawn articles |
| US4141482A (en) * | 1977-04-25 | 1979-02-27 | Reynolds Metals Company | Laminated compacted particle aluminum sheet |
| US4510207A (en) * | 1982-10-05 | 1985-04-09 | Toyo Aluminium Kabushiki Kaisha | Composite aluminum foil for use as electrode in electrolytic capacitor |
| US5032468A (en) * | 1988-11-25 | 1991-07-16 | Vereinigte Aluminium Werke | Composite aluminum plate and target for physical coating processes produced therefrom and methods for producing same |
| US5268236A (en) * | 1988-11-25 | 1993-12-07 | Vereinigte Aluminum-Werke Ag | Composite aluminum plate for physical coating processes and methods for producing composite aluminum plate and target |
| US6626351B2 (en) | 2000-09-19 | 2003-09-30 | Tower Automotive Technology Products, Inc. | Method and apparatus for the manufacturing of structural members |
| US6679417B2 (en) | 2001-05-04 | 2004-01-20 | Tower Automotive Technology Products, Inc. | Tailored solutionizing of aluminum sheets |
-
0
- US US2383511D patent/US2383511A/en not_active Expired - Lifetime
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2612682A (en) * | 1946-04-05 | 1952-10-07 | Reynolds Metals Co | Method of cladding a copper-base metal to an aluminum core |
| US2602413A (en) * | 1948-08-13 | 1952-07-08 | Aluminum Co Of America | Aluminous brazing product and method of brazing |
| US2821014A (en) * | 1951-05-31 | 1958-01-28 | Aluminum Co Of America | Composite aluminous metal article |
| US2990609A (en) * | 1958-03-11 | 1961-07-04 | Ohmi Rihei | Casting made of aluminum or aluminum alloy |
| US3054176A (en) * | 1959-07-06 | 1962-09-18 | Reynolds Metals Co | Forming system |
| US3226808A (en) * | 1960-05-26 | 1966-01-04 | Reynolds Metals Co | Method of making refrigerator evaporators or the like |
| US3168381A (en) * | 1960-09-01 | 1965-02-02 | Kaiser Aluminium Chem Corp | Aluminum alloy and article |
| US3312536A (en) * | 1963-06-19 | 1967-04-04 | Olin Mathieson | Composite aluminum alloy |
| US3312535A (en) * | 1963-07-16 | 1967-04-04 | Aluminum Co Of America | Aluminum reflectors |
| US3240269A (en) * | 1965-06-02 | 1966-03-15 | Reynolds Metals Co | Composite refrigerator evaporator |
| US3490124A (en) * | 1967-02-07 | 1970-01-20 | Texas Instruments Inc | Composite metal layers for fabricating deep drawn articles |
| US4141482A (en) * | 1977-04-25 | 1979-02-27 | Reynolds Metals Company | Laminated compacted particle aluminum sheet |
| US4510207A (en) * | 1982-10-05 | 1985-04-09 | Toyo Aluminium Kabushiki Kaisha | Composite aluminum foil for use as electrode in electrolytic capacitor |
| US5032468A (en) * | 1988-11-25 | 1991-07-16 | Vereinigte Aluminium Werke | Composite aluminum plate and target for physical coating processes produced therefrom and methods for producing same |
| US5268236A (en) * | 1988-11-25 | 1993-12-07 | Vereinigte Aluminum-Werke Ag | Composite aluminum plate for physical coating processes and methods for producing composite aluminum plate and target |
| US6626351B2 (en) | 2000-09-19 | 2003-09-30 | Tower Automotive Technology Products, Inc. | Method and apparatus for the manufacturing of structural members |
| US6679417B2 (en) | 2001-05-04 | 2004-01-20 | Tower Automotive Technology Products, Inc. | Tailored solutionizing of aluminum sheets |
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