CN1173059C - Non-hardenable aluminium alloy as a semi-finished product for structures - Google Patents
Non-hardenable aluminium alloy as a semi-finished product for structures Download PDFInfo
- Publication number
- CN1173059C CN1173059C CNB018053572A CN01805357A CN1173059C CN 1173059 C CN1173059 C CN 1173059C CN B018053572 A CNB018053572 A CN B018053572A CN 01805357 A CN01805357 A CN 01805357A CN 1173059 C CN1173059 C CN 1173059C
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- Prior art keywords
- alloy
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- finished product
- iron
- aluminium
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- 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
- C22C21/06—Alloys based on aluminium with magnesium as the next major constituent
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Prevention Of Electric Corrosion (AREA)
- Manufacture And Refinement Of Metals (AREA)
- Powder Metallurgy (AREA)
- Manufacture Of Alloys Or Alloy Compounds (AREA)
- Extrusion Of Metal (AREA)
- Metal Rolling (AREA)
- Forging (AREA)
- Hard Magnetic Materials (AREA)
- Laminated Bodies (AREA)
- Conductive Materials (AREA)
Abstract
The invention relates to chemical compositions of alloys, particularly naturally hard semi-finished product alloys which should be used in said form as material for semi-finished products. The invention also relates to a naturally hard aluminium alloy for semi-finished product structures which is made of magnesium, titanium, beryllium, zircon, scandium and cerium and additionally manganese, copper, zinc and an element group containing iron and silicon, whereby the ratio of iron to the silicon ranges between 1 and 5.
Description
Technical field
The present invention relates to a kind of alloy composite, more specifically relate to the semifinished material alloy composite of air-set, said composition is used as the structure material material with this form.
Background technology
The aluminium alloy of air-set is used as semi-finished product for structures material (seeing GOST standard 4784-74) on metallurgy, but mainly is that form with the Amg6 alloy is used, and this alloy contains following composition (weight %):
Magnesium 5.8-6.8
Manganese 0.5-0.8
Titanium 0.02-0.1
Beryllium 0.0002-0.005
The aluminium surplus
Yet this alloy does not have enough strength characteristicies, especially has only 0.2% low yield strength in coldmoulding and hot-forming semifinished material.
A kind of aluminium alloy (see patent RUNo.2085607, IPC is categorized as C 21/061) that is used as the air-set of semi-finished product for structures material also belongs to prior art, and it has the prototype of following chemical constitution:
Magnesium 3.9-4.9
Titanium 0.01-0.1
Beryllium 0.0001-0.005
Zirconium 0.05-0.15
Scandium 0.20-0.50
Cerium 0.001-0.004
The aluminium surplus
This known alloy does not have enough static strengths and dynamic strength, and has the high working property, high anti-corrosion of manufacturing processed, good weldability and the operation of the height under cold condition possibility.
Summary of the invention
The purpose of this invention is to provide a kind of new, as aluminium alloy semifinished material, air-set, wherein except magnesium, titanium, beryllium, zirconium, scandium, and cerium, the element set that this aluminium alloy also will be used manganese, copper, zinc and be made up of iron and silicon, be the composition of its composition below, iron to the ratio of silicon in 1 to 5 scope:
Magnesium 5.0-5.6
Titanium 0.01-0..05
Beryllium 0.0001-0.005
Zirconium 0.05-0.15
Scandium 0.18-0.30
Cerium 0.001-0.004
Manganese 0.05-0.18
Copper 0.05-0.15
Zinc 0.05-0.15
Comprise iron and silicon
Element set 0.04-0.24
The aluminium surplus
Embodiment
The difference part of alloy of the present invention and conventional alloys is the element set that it has added manganese, copper, zinc and has been made up of iron and silicon, and these components in proportions are as follows, wherein iron to the ratio of silicon in 1 and 5 scope:
Magnesium 5.0-5.6
Titanium 0.01-0..05
Beryllium 0.0001-0.005
Zirconium 0.05-0.15
Scandium 0.18-0.30
Cerium 0.001-0.004
Manganese 0.05-0.18
Copper 0.05-0.15
Zinc 0.05-0.15
Comprise iron and silicon
Element set 0.04-0.24
The aluminium surplus
Technique effect is embodied in the raising of the static(al) of alloy and dynamic strength performance, be the raising of work-ing life, work reliability and the gravimetric value of structure under basic load and dynamic load, be embodied in especially on the structure properties of the various aircrafts of the aircraft that comprises the cryogenic fuel that burns and spaceship.
Because the ratio between chemical content of the present invention and the chemical constitution, this alloy has a quite ductile matrix, and this matrix is made up of the mixed crystal that is dissolved in magnesium, manganese, copper and zinc in the aluminium.
The high ductibility of matrix has caused the extra high operation possibility of this alloy under the circulation power load.In repeated load, the secondary sedimentation that occurs in the intermetallic particle that the precision that comprises aluminium, scandium, zirconium, titanium and other transition metal in the alloy distributes provides the high static strength of alloy and to the high-drag of crack propagation.The set-point of iron and silicon ratio makes the form optimization of compound between original metal, and this intermetallic compound obtains from solidification, mainly is made up of aluminium, iron and silicon, can improve the static strength of alloy, and its dynamic strength and plasticity remains unchanged.
Embodiment
Use aluminium A85, manganese MG90, copper MO, zinc TsO, binary prealloy (aluminium-titanium for example, aluminium-beryllium, aluminum-zirconium, aluminium-scandium, aluminium-cerium, aluminium-manganese, aluminium-iron, silumin) as additive, in electric furnace, make melt, cast out alloy plane ingot casting (table 1) by means of the semicontinuous casting technology according to 165 * 550mm size of the present invention, this ingot casting has a minimum (composition 1), best (composition 2), with (composition 3) proportion of composing of maximum, be included in the proportion of composing (composition 4 and 5) on the present invention's qualification, and conventional alloy (composition 6) (seeing Table 1).
Table 1
| Alloy | Composition | Chemical composition (weight %) | ||||||||||||
| Magnesium | Titanium | Beryllium | Zirconium | Scandium | Cerium | Manganese | Copper | Zinc | Iron | Silicon | Iron/silicon *) | Aluminium | ||
| Alloy of the present invention | 1 | 5.0 | 0.01 | 0.0001 | 0.05 | 0.18 | 0.001 | 0.05 | 0.05 | 0.05 | 0.02 | 0.02 | 1 | Surplus |
| 2 | 5.3 | 0.03 | 0.003 | 0.1 | 0.24 | 0.02 | 0.12 | 0.1 | 0.1 | 0.10 | 0.03 | 3.33 | Surplus | |
| 3 | 5.6 | 0.05 | 0.005 | 0.15 | 0.30 | 0.004 | 0.18 | 0.15 | 0.15 | 0.2 | 0.05 | 5 | Surplus | |
| Element transfinites | ||||||||||||||
| 4 | 4.5 | 0.005 | 0.00005 | 0.01 | 0.12 | 0.0005 | 0.02 | 0.01 | 0.01 | 0.01 | 0.02 | 0.5 | Surplus | |
| 5 | 6.0 | 0.1 | 0.01 | 0.2 | 0.36 | 0.008 | 0.25 | 0.25 | 0.25 | 0.5 | 0.08 | 6.25 | Surplus | |
| Known alloy | ||||||||||||||
| 6 | 4.4 | 0.05 | 0.003 | 0.1 | 0.3 | 0.002 | - | - | - | - | - | - | Surplus- | |
*): iron level is to the ratio of silicone content
If this alloy is to produce under the metallurgical production condition, the scrap metal that is made by aluminum-manganese alloy can be used as additive so.
Ingot casting is homogenized and be machined to 140 millimeters thickness, is hot-rolled down to 7 millimeters thickness subsequently under 400 ℃ temperature, is cold-rolled to 4 millimeters thickness again.Cold rolled sheet is thermal treatment in electric furnace, and heat treated sheet material is used as test material.
The standard crosscut sample that takes out from sheet material be used to measure the static(al) tensile strength (Rm, Rp0.02, A) and dynamic strength:
-measure the cycle life (N) that short term strength (LCF) lost efficacy, wherein use notch factor to be K
t=2.5, maximum stress is σ
MaxThe sample of=160MPa;
-stress intensity coefficient is Δ K=31.2Mpa
0.5Crack propagation velocity da/dN in the scope;
The critical stress intensity factor Kc of-plane stress state, the width of sample are 160mm (B)
All tests are all at room temperature carried out.
Table 2 is listed test result.
Table 2 has verified that alloy ratio conventional alloys of the present invention has higher static(al) and dynamic strength.Use the weight minimizing 10-15% according to the structure of alloy of the present invention, in order to reduce working cost, this is very important for aerospace industry.According to the high anti-corrosion and good weldability that alloy of the present invention has the height operation possibility under static(al) and dynamic condition and had as a kind of natural hardened alloy according to alloy of the present invention, this makes this alloy can be applied to building the vehicles that brand-new aircraft and spaceship, seagoing vessel, automobile and other members usefulness are weldingly connected.Can be used as the starting material of welding assembly and the weld filler of conduct welding usefulness according to alloy of the present invention.
Table 2
| Alloy | Composition | The characteristic of thermal treatment sheet material | |||||
| R m [MPa] | R po.2 [MPa] | A [％] | LCF [cycle] (K t＝2.5； σ max＝160 MPa) | Da/dN [mm/ cycle] (Δ K=31.2 MPa √ m) | Kc (MPa√m) (B＝160mm) | ||
| Alloy of the present invention | 1 | 390 | 275 | 17 | 150×10 3 | 2.3×10 -3 | 62 |
| 2 | 400 | 280 | 16 | 140×10 3 | 2.5×10 -3 | 63 | |
| 3 | 410 | 290 | 15 | 140×10 3 | 3.3×10 -3 | 62 | |
| Element transfinites | 4 | 370 | 260 | 18 | 130×10 3 | 3.8×10 -3 | 62 |
| 5 | 420 | 315 | 13 | 110×10 3 | 4.0×10 -3 | 60 | |
| Known alloy | 6 | 380 | 275 | 15 | 130×10 3 | 3.8×10 -3 | 62 |
Claims (1)
1. aluminium alloy as the air-set of semi-finished product for structures material,
It is characterized in that except magnesium, titanium, beryllium, zirconium, scandium, and cerium, this aluminium alloy will be the composition of its composition by manganese, copper, zinc and the element set of being made up of iron and silicon below also, wherein iron to the ratio of silicon in 1 to 5 scope:
Magnesium 5.0-5.6
Titanium 0.01-0.05
Beryllium 0.0001-0.005
Zirconium 0.05-0.15
Scandium 0.18-0.30
Cerium 0.001-0.004
Manganese 0.05-0.18
Copper 0.05-0.15
Zinc 0.05-0.15
Comprise iron and silicon
Element set 0.04-0.24
The aluminium surplus
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP00128050A EP1217085B1 (en) | 2000-12-21 | 2000-12-21 | Non hardenable aluminium alloy as semi-product for structures |
| EP00128050.2 | 2000-12-21 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1404533A CN1404533A (en) | 2003-03-19 |
| CN1173059C true CN1173059C (en) | 2004-10-27 |
Family
ID=8170749
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB018053572A Expired - Fee Related CN1173059C (en) | 2000-12-21 | 2001-12-14 | Non-hardenable aluminium alloy as a semi-finished product for structures |
Country Status (9)
| Country | Link |
|---|---|
| EP (1) | EP1217085B1 (en) |
| JP (1) | JP4212893B2 (en) |
| CN (1) | CN1173059C (en) |
| AT (1) | ATE251231T1 (en) |
| CA (1) | CA2398667C (en) |
| DE (1) | DE50003940D1 (en) |
| ES (1) | ES2207459T3 (en) |
| RU (1) | RU2277603C2 (en) |
| WO (1) | WO2002050325A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111989414A (en) * | 2018-04-18 | 2020-11-24 | 纽弗雷公司 | Fastener made of scandium-containing aluminum alloy |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8852365B2 (en) | 2009-01-07 | 2014-10-07 | The Boeing Company | Weldable high-strength aluminum alloys |
| CN102912199A (en) * | 2012-10-29 | 2013-02-06 | 虞海香 | Aluminum alloy sheet for vehicle body |
| CN104313414A (en) * | 2014-11-06 | 2015-01-28 | 广西柳州银海铝业股份有限公司 | Aluminum-magnesium alloy and preparation method of plate of aluminum-magnesium alloy |
| WO2016130426A1 (en) | 2015-02-11 | 2016-08-18 | Scandium International Mining Corporation | Scandium-containing master alloys and methods for making the same |
| EP3181711B1 (en) | 2015-12-14 | 2020-02-26 | Apworks GmbH | Aluminium alloy containing scandium for powder metallurgy technologies |
| RU2636781C2 (en) * | 2015-12-25 | 2017-11-28 | ООО "СМВ Инжиниринг" | High-strength thermally non-strengthened aluminium alloy and method for its production |
| RU2726520C1 (en) * | 2019-09-03 | 2020-07-14 | федеральное государственное автономное образовательное учреждение высшего образования "Самарский национальный исследовательский университет имени академика С.П. Королёва" | Welded thermally non-hardened alloy based on al-mg system |
| CN113231601A (en) * | 2021-04-15 | 2021-08-10 | 安徽天平机械股份有限公司 | Reduction gearbox shell casting method |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2038405C1 (en) * | 1993-02-19 | 1995-06-27 | Всероссийский научно-исследовательский институт авиационных материалов | Aluminium-base alloy |
| FR2717827B1 (en) * | 1994-03-28 | 1996-04-26 | Jean Pierre Collin | Aluminum alloy with high Scandium contents and process for manufacturing this alloy. |
| RU2085607C1 (en) * | 1995-06-30 | 1997-07-27 | Борис Иванович Бондарев | Deformable thermally cryogenic unreinforced aluminium- based alloy |
| DE19838018C2 (en) * | 1998-08-21 | 2002-07-25 | Eads Deutschland Gmbh | Welded component made of a weldable, corrosion-resistant, high-magnesium aluminum-magnesium alloy |
-
2000
- 2000-12-21 ES ES00128050T patent/ES2207459T3/en not_active Expired - Lifetime
- 2000-12-21 AT AT00128050T patent/ATE251231T1/en not_active IP Right Cessation
- 2000-12-21 DE DE50003940T patent/DE50003940D1/en not_active Expired - Lifetime
- 2000-12-21 EP EP00128050A patent/EP1217085B1/en not_active Expired - Lifetime
-
2001
- 2001-12-14 CN CNB018053572A patent/CN1173059C/en not_active Expired - Fee Related
- 2001-12-14 CA CA2398667A patent/CA2398667C/en not_active Expired - Fee Related
- 2001-12-14 WO PCT/EP2001/014797 patent/WO2002050325A1/en active Application Filing
- 2001-12-14 JP JP2002551202A patent/JP4212893B2/en not_active Expired - Fee Related
- 2001-12-14 RU RU2003116892/02A patent/RU2277603C2/en not_active IP Right Cessation
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111989414A (en) * | 2018-04-18 | 2020-11-24 | 纽弗雷公司 | Fastener made of scandium-containing aluminum alloy |
Also Published As
| Publication number | Publication date |
|---|---|
| CA2398667C (en) | 2010-05-18 |
| ATE251231T1 (en) | 2003-10-15 |
| JP4212893B2 (en) | 2009-01-21 |
| EP1217085A1 (en) | 2002-06-26 |
| RU2277603C2 (en) | 2006-06-10 |
| WO2002050325A1 (en) | 2002-06-27 |
| JP2004516385A (en) | 2004-06-03 |
| CA2398667A1 (en) | 2002-06-27 |
| ES2207459T3 (en) | 2004-06-01 |
| CN1404533A (en) | 2003-03-19 |
| DE50003940D1 (en) | 2003-11-06 |
| EP1217085B1 (en) | 2003-10-01 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20041027 Termination date: 20171214 |