CA1047282A - Magnesium alloys - Google Patents
Magnesium alloysInfo
- Publication number
- CA1047282A CA1047282A CA242,644A CA242644A CA1047282A CA 1047282 A CA1047282 A CA 1047282A CA 242644 A CA242644 A CA 242644A CA 1047282 A CA1047282 A CA 1047282A
- Authority
- CA
- Canada
- Prior art keywords
- temperature
- weight
- alloy
- hours
- alloy according
- 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
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C23/00—Alloys based on magnesium
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C23/00—Alloys based on magnesium
- C22C23/06—Alloys based on magnesium with a rare earth metal as the next major constituent
-
- 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
- C22F1/06—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of magnesium or alloys based thereon
Landscapes
- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Materials Engineering (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Crystallography & Structural Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Manufacture And Refinement Of Metals (AREA)
- Powder Metallurgy (AREA)
- Dental Preparations (AREA)
- Conductive Materials (AREA)
- Transition And Organic Metals Composition Catalysts For Addition Polymerization (AREA)
- Materials For Medical Uses (AREA)
- Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
- Adornments (AREA)
Abstract
ABSTRACT OF THE DISCLOSURE
Magnesium alloys having improved high-temperature properties, especially improved resistance to creep, con-tain from 1.25 to 3.0% silver, 0.5 to 2.5% of rare metals including at least 60% neodymium and from 2.5 to 7.0%
yttrium. Optimum properties are obtained by high-temperature solution treatment followed by ageing at a lower temperature.
The present invention discloses a light weight magnesium ally that has improved mechanical properties up to approximately 250°C.
Magnesium alloys having improved high-temperature properties, especially improved resistance to creep, con-tain from 1.25 to 3.0% silver, 0.5 to 2.5% of rare metals including at least 60% neodymium and from 2.5 to 7.0%
yttrium. Optimum properties are obtained by high-temperature solution treatment followed by ageing at a lower temperature.
The present invention discloses a light weight magnesium ally that has improved mechanical properties up to approximately 250°C.
Description
~047282 Thi~ invention relates to magnesium alloys.
Magnesium alloys have a very low weight in compari~on with alloys of other metals and accordin~ly find applications, particularly in the aerospace industry, where a low weight i9 important. Such alloys having advantageous mechanical properties, in particular a high proof stress, are described in British Patent Specification 875,929.
Alloye within the scope of the latter specification have been used in aerospace components which are subject to relatively high stress, such as aircraft compressor housing~, helicopter main gearboxe~ and undercarriage components. ~o obtain adequate mechanical properties it is necé~sary to ~ubject the~e alloy~ to a two-etage heat treatment entailing solution treatment at a high temperature, followed by quenching an ageing at a lower -~ temperature to improve the mechanical properties by precipitation hardening.
Mechanical properties thu~ obtained are well maintained during exposure to elevated temperatures up to 200C. However, on exposure to temperatures above 200C, mechanical properties deteriorate signi~icantly, limiting the applications of such alloys in aircraft and other machiner, e~pecially in engines and gearboxes operating in thi~ temperature range.
~ here have now been found magne~ium alloys having ~atisfaotory tensile properties at room temperature which ; retain their advantageou~ properties, at least to ~ome degree, at temperatures of the order of 250C a~d show _ 2 _ ~
q~
"
:.
' ' ' ' ' . ' , improved re~istance to creep at these temperatures.
According to one aspect o~ the invention. there i8 provided a magnesium-based alloy containing the ; following con~tituents by weight (other than iron and other impurities):
Silver 1.25 - 3.0%
Rare earth metal~ of which ; least 60~ is neodymium0.5 - 3.0~
Yttrium 2.5 - 7%
Thorium 0 - 1%
Zirconium ~ 0 - 1~
Zinc ~ 5%
, Cadmium 0 - 1.0~o v ~ithium 0 - 6.0%
Calcium 0 - 0.8%
Gallium 0 - 2.0%
~, Indium 0 - 2.0%
~hallium 0 - 5.0%
~ead 0 - 1.0%
Bismuth 0 - 1.0%
Copper 0 - o.s%
~, Mnnganese 0 - 2.0~
~, In a preferred embodiment the alloy contain~
from 3 to 5X by weight of yttrium and from 1 to 2.~%
.
by weight of rare earth metals. It should be noted that yttrium i8 not itaelf considered ae a rare earth ~' metal.
" ~he rare earth metals may be 100% neodymium, but as thi~ material is expen~ive in the pure state it i~
;; 3o preferred to use a mixture of metals, ~ometimes known . .
.'.~
. . .
;' ~.0472~2 as didymium, which containes at least 60% by weight of neodymium with the remainder consisting substantially as the other heavy rare earth metals such as gadolinium.
It is desixable for cerium and lanthanum to be absent or at least present in very small quantities and accordingly the content of lanthanum and cerium together in the rare earch metal mixture should not exceed 25% by weight. It has been found that the presence of cerium gives inferior yield and ultimate tensile strengths at both low and high temperatures.
An increasing silver content increases the cost of the alloy but on the other hand'reducing the silver .''. .
content below 2% gives a reduction in yield strength.
' Alloys containing 2 - 3% silver are therefore preferred.
The yttrium may be 3dded to the alloy as pure yttrium but it may be preferred to add it as an ' yttrium/rare earth metal mixture containing at least 60%, . . ~
preferably at least 65% by weight of yttrium.
, It has been found that all or part of the thorium of magnesium alloys containing 0.5 - 2.1% of neodymium and 0.3 - 1.9~ of thori~m with the total amount of these .. . .
`~ two elements being from 1.5 to 2.5%, may be replaced ~;~ by a suitable amount of yttrium to give equally good i' : or better tensile properties at elevated temperatures.
. . .
; The presence of yttrium has the further advantage . . .
~ that resistance to creep at elevated temperatures ;'..
~ - 4 -:. " , 10~7Z82 i 8 impro~ed.
It is normally desirable for the alloy to contnin up to 1% of zirconium as a grain refiner. It iY preferred that the zirconium content ~thould be at least 0.l~,' Pnrt of the zirconium may be replaced by up to 0.2~S mangane~e, but in thi~ ca~e the amounts of zirconium and mnngane~e are limited by their mutual ~olubility.
The remaitling elements mentioned abo~e (zinc~cndmium, lithium, calcium, gallium, indium, thallium, lead and bi~muth) may be pre~ent in the above mentioned amollnt~; they do not interfere with the action of the other con~tituents.
Heat treatment i~ normally required to obtain the optimum mechanical properties for the~e alloys. Thi~
comprises a high-temperature ~olution treatmellt at a temperature from l~50C to ~olidu6 of the alloy for R
~ufficient time to obtain ~olution, generally at lea~t 2 hour~, followed by quenching and ageing at a lot~er temperature such as from 100 to 350C for at least 7~ hour.
Typical heat treatment conditions are ~ hour~ at 5~0C
followed by ageing at 200C for 16 hours.
Alternative heat treatment condition~ are initiM1 i solution treatment at 480C for ~ hour~, follo~ed by furthersolution treatment at 520C for 4 hour~t and n~ein~ at 2~0C
~; .
for 8 hour~t.
The solidu~ of the alloy varies according to it~
.: ' ; exact compo~ition and fall~ appreciably at yttrium content~
above 6%. The temperature of ~olution treatment mny the have to be lowered accordingly.
Alloy~ according to the pre~ent invention will bo de~cribed by way of illu~tration by the followin~ Examples.
-5- ~
','.';' ~ :
.:
. . . ~
104~2 L9MPIæS
Alloys having the compositions given in the table below were prepared and cast to make te~t specimens by a conventional method.
The specimens were then solution heat-treated for 8 hours at 520 or 525C, followed by quenohing and ageing for 16 hours at 200C.
; The yield strength, ultimate tensile strength and elongation at fracture of the specimens were measured at ambient temperature and at 250C in accordance with British Standard 3688. The re~ults are given in the Table.
, "1 ~ .
.. , ' ., , , ' ' ',:, '" :
'~
.~ ' ' .~. , '~ ` , ; - 6 -, .
- - , .. --. ~.. . .~ . . .. ......... .
,. ~
, .
~., , , ~ -' - , ' " ',:
.
.
iO47Z82 .
1i3 C~ ~D ~X) 0 H ;~
,~0~ ae .
h u^ ___ _ P. ~ u~ ~ ~ o ~
s o ~ E ~ CO ao O ~ ~ O ~1 ~1:) tD
h td . ~ ~ ~- N ~1 ~- t~
,. ~_ P
,' ~
r/ E
~ ~ .
~.~ ~: ~Z ~1 ~ ~I O ~ O ~ O (5` oo ~t f 0 _ a~ u~
~'~ E l ,~
" ~ .
~, _ _ . ' ,` . . .
.
. ~1 H
~ U~ ~ H ~ ~
- ~ h oo . I
p, ~U ~q C5~ O ~ ~ o ~J o() ': `
O ~ E~ ~D a) oo ~ 0 ~ o ~
h ~ . N ~U ~ J N N
,: ~ P
~ _ ` .~' :~, ~ ~; ~1 ~ ~ ~O C~J ~ ~ U~ 0 ., " P~ 0 `_ ~ O~ O O O O C~ C~ O ~ ~
~ E-~ ~ ~ N N N N ~ ~ N N N
_ ,, , ~ l l l l l l l l l l .
,~' . .
~` ~ 2 ,.. , ~ i i,~ _ o ~ Ir~ N Lf~ N~ ~ 00 ~
h U~ U~
., æ c;l . . . - . . . . .
, O O O O O O O O O O
,.- ~1 ~ ~D ~D ~9 ~ C~
Cl~ ~
.: ~
O O O C~J O O ~ I
.. . ~ J tU O ~- N ~U
.~,., .
~ :'. ~ ~ r' 0 ;'.': qD O O O O O O O O ~D C`
".;. . ~
~J N ~J N N ~ 1 tU ~J
~, _ , .
, `
.~ - 7 -...
. ~ ~
~: i :
It will be noted from these results that the higher-temperature properties of the yttrium containing alloys were considerably better than tho~e of ~imilar alloy~ containing no yttrium.
The same procedure wa~ followed with a magnesium alloy containing 2.09~ Ag, 3.04% Y and 0.52% Zr but no neodymium. The yield strength. ultimate ten~ile strength and elongation at 250C were respectively 107 N/mm2, 134 N/mm2 and 1%; these figures are much lower than tho~e of the neodymium-containing alloy~.
In order to estimate the creep behaviour of the alloys of the invention, alloys having ~he following approximate composition were tested at 250C for creep according to British Standard 3500 and the results are given below.
" .
Ag NdZr Y ~.2/100 (Stress in N/mm2)
Magnesium alloys have a very low weight in compari~on with alloys of other metals and accordin~ly find applications, particularly in the aerospace industry, where a low weight i9 important. Such alloys having advantageous mechanical properties, in particular a high proof stress, are described in British Patent Specification 875,929.
Alloye within the scope of the latter specification have been used in aerospace components which are subject to relatively high stress, such as aircraft compressor housing~, helicopter main gearboxe~ and undercarriage components. ~o obtain adequate mechanical properties it is necé~sary to ~ubject the~e alloy~ to a two-etage heat treatment entailing solution treatment at a high temperature, followed by quenching an ageing at a lower -~ temperature to improve the mechanical properties by precipitation hardening.
Mechanical properties thu~ obtained are well maintained during exposure to elevated temperatures up to 200C. However, on exposure to temperatures above 200C, mechanical properties deteriorate signi~icantly, limiting the applications of such alloys in aircraft and other machiner, e~pecially in engines and gearboxes operating in thi~ temperature range.
~ here have now been found magne~ium alloys having ~atisfaotory tensile properties at room temperature which ; retain their advantageou~ properties, at least to ~ome degree, at temperatures of the order of 250C a~d show _ 2 _ ~
q~
"
:.
' ' ' ' ' . ' , improved re~istance to creep at these temperatures.
According to one aspect o~ the invention. there i8 provided a magnesium-based alloy containing the ; following con~tituents by weight (other than iron and other impurities):
Silver 1.25 - 3.0%
Rare earth metal~ of which ; least 60~ is neodymium0.5 - 3.0~
Yttrium 2.5 - 7%
Thorium 0 - 1%
Zirconium ~ 0 - 1~
Zinc ~ 5%
, Cadmium 0 - 1.0~o v ~ithium 0 - 6.0%
Calcium 0 - 0.8%
Gallium 0 - 2.0%
~, Indium 0 - 2.0%
~hallium 0 - 5.0%
~ead 0 - 1.0%
Bismuth 0 - 1.0%
Copper 0 - o.s%
~, Mnnganese 0 - 2.0~
~, In a preferred embodiment the alloy contain~
from 3 to 5X by weight of yttrium and from 1 to 2.~%
.
by weight of rare earth metals. It should be noted that yttrium i8 not itaelf considered ae a rare earth ~' metal.
" ~he rare earth metals may be 100% neodymium, but as thi~ material is expen~ive in the pure state it i~
;; 3o preferred to use a mixture of metals, ~ometimes known . .
.'.~
. . .
;' ~.0472~2 as didymium, which containes at least 60% by weight of neodymium with the remainder consisting substantially as the other heavy rare earth metals such as gadolinium.
It is desixable for cerium and lanthanum to be absent or at least present in very small quantities and accordingly the content of lanthanum and cerium together in the rare earch metal mixture should not exceed 25% by weight. It has been found that the presence of cerium gives inferior yield and ultimate tensile strengths at both low and high temperatures.
An increasing silver content increases the cost of the alloy but on the other hand'reducing the silver .''. .
content below 2% gives a reduction in yield strength.
' Alloys containing 2 - 3% silver are therefore preferred.
The yttrium may be 3dded to the alloy as pure yttrium but it may be preferred to add it as an ' yttrium/rare earth metal mixture containing at least 60%, . . ~
preferably at least 65% by weight of yttrium.
, It has been found that all or part of the thorium of magnesium alloys containing 0.5 - 2.1% of neodymium and 0.3 - 1.9~ of thori~m with the total amount of these .. . .
`~ two elements being from 1.5 to 2.5%, may be replaced ~;~ by a suitable amount of yttrium to give equally good i' : or better tensile properties at elevated temperatures.
. . .
; The presence of yttrium has the further advantage . . .
~ that resistance to creep at elevated temperatures ;'..
~ - 4 -:. " , 10~7Z82 i 8 impro~ed.
It is normally desirable for the alloy to contnin up to 1% of zirconium as a grain refiner. It iY preferred that the zirconium content ~thould be at least 0.l~,' Pnrt of the zirconium may be replaced by up to 0.2~S mangane~e, but in thi~ ca~e the amounts of zirconium and mnngane~e are limited by their mutual ~olubility.
The remaitling elements mentioned abo~e (zinc~cndmium, lithium, calcium, gallium, indium, thallium, lead and bi~muth) may be pre~ent in the above mentioned amollnt~; they do not interfere with the action of the other con~tituents.
Heat treatment i~ normally required to obtain the optimum mechanical properties for the~e alloys. Thi~
comprises a high-temperature ~olution treatmellt at a temperature from l~50C to ~olidu6 of the alloy for R
~ufficient time to obtain ~olution, generally at lea~t 2 hour~, followed by quenching and ageing at a lot~er temperature such as from 100 to 350C for at least 7~ hour.
Typical heat treatment conditions are ~ hour~ at 5~0C
followed by ageing at 200C for 16 hours.
Alternative heat treatment condition~ are initiM1 i solution treatment at 480C for ~ hour~, follo~ed by furthersolution treatment at 520C for 4 hour~t and n~ein~ at 2~0C
~; .
for 8 hour~t.
The solidu~ of the alloy varies according to it~
.: ' ; exact compo~ition and fall~ appreciably at yttrium content~
above 6%. The temperature of ~olution treatment mny the have to be lowered accordingly.
Alloy~ according to the pre~ent invention will bo de~cribed by way of illu~tration by the followin~ Examples.
-5- ~
','.';' ~ :
.:
. . . ~
104~2 L9MPIæS
Alloys having the compositions given in the table below were prepared and cast to make te~t specimens by a conventional method.
The specimens were then solution heat-treated for 8 hours at 520 or 525C, followed by quenohing and ageing for 16 hours at 200C.
; The yield strength, ultimate tensile strength and elongation at fracture of the specimens were measured at ambient temperature and at 250C in accordance with British Standard 3688. The re~ults are given in the Table.
, "1 ~ .
.. , ' ., , , ' ' ',:, '" :
'~
.~ ' ' .~. , '~ ` , ; - 6 -, .
- - , .. --. ~.. . .~ . . .. ......... .
,. ~
, .
~., , , ~ -' - , ' " ',:
.
.
iO47Z82 .
1i3 C~ ~D ~X) 0 H ;~
,~0~ ae .
h u^ ___ _ P. ~ u~ ~ ~ o ~
s o ~ E ~ CO ao O ~ ~ O ~1 ~1:) tD
h td . ~ ~ ~- N ~1 ~- t~
,. ~_ P
,' ~
r/ E
~ ~ .
~.~ ~: ~Z ~1 ~ ~I O ~ O ~ O (5` oo ~t f 0 _ a~ u~
~'~ E l ,~
" ~ .
~, _ _ . ' ,` . . .
.
. ~1 H
~ U~ ~ H ~ ~
- ~ h oo . I
p, ~U ~q C5~ O ~ ~ o ~J o() ': `
O ~ E~ ~D a) oo ~ 0 ~ o ~
h ~ . N ~U ~ J N N
,: ~ P
~ _ ` .~' :~, ~ ~; ~1 ~ ~ ~O C~J ~ ~ U~ 0 ., " P~ 0 `_ ~ O~ O O O O C~ C~ O ~ ~
~ E-~ ~ ~ N N N N ~ ~ N N N
_ ,, , ~ l l l l l l l l l l .
,~' . .
~` ~ 2 ,.. , ~ i i,~ _ o ~ Ir~ N Lf~ N~ ~ 00 ~
h U~ U~
., æ c;l . . . - . . . . .
, O O O O O O O O O O
,.- ~1 ~ ~D ~D ~9 ~ C~
Cl~ ~
.: ~
O O O C~J O O ~ I
.. . ~ J tU O ~- N ~U
.~,., .
~ :'. ~ ~ r' 0 ;'.': qD O O O O O O O O ~D C`
".;. . ~
~J N ~J N N ~ 1 tU ~J
~, _ , .
, `
.~ - 7 -...
. ~ ~
~: i :
It will be noted from these results that the higher-temperature properties of the yttrium containing alloys were considerably better than tho~e of ~imilar alloy~ containing no yttrium.
The same procedure wa~ followed with a magnesium alloy containing 2.09~ Ag, 3.04% Y and 0.52% Zr but no neodymium. The yield strength. ultimate ten~ile strength and elongation at 250C were respectively 107 N/mm2, 134 N/mm2 and 1%; these figures are much lower than tho~e of the neodymium-containing alloy~.
In order to estimate the creep behaviour of the alloys of the invention, alloys having ~he following approximate composition were tested at 250C for creep according to British Standard 3500 and the results are given below.
" .
Ag NdZr Y ~.2/100 (Stress in N/mm2)
2% 2~0.5~ - 28 i 2~ 2%0.5~ 4% 55 ,, .
.
, . . . .
;.
~; . .
,.. .
~ -8-.
:' ~ ';
.~ , , .
. .
. : :., .
. . . .
.
, . . . .
;.
~; . .
,.. .
~ -8-.
:' ~ ';
.~ , , .
. .
. : :., .
. . . .
Claims (12)
PROPERTY OR PRIVILEGE IS CLAIMED ARE DEFINED AS FOLLOWS:
1. A magnesium-based alloy containing the following constituents by weight (other than iron and other impurities):
the balance magnesium.
the balance magnesium.
2. An alloy according to claim 1, which contains from 3 to 5% by weight of yttrium and from 1 to 2.5% by weight of rare earth metals.
3. An alloy according to claim 2, which contains at least 0.4% by weight of zirconium.
4. An alloy according to claims 1, 2, or 3 which also contains up to 0.2% manganese, the maximum and permis-sible amount of manganese being controlled by its mutual solubility with the zirconium if present.
5. An alloy according to claims 1, 2, or 3, containing from 2 to 3% by weight of silver.
6. An alloy according to claims 1, 2, or 3, in which the rare earths contain not more than 25% by weight of cerium and lanthanum taken together.
7. An alloy according to claim 1, containing up to 0.2% manganese, the maximum and permissible amount of manganese being controlled by its mutual solubility with zirconium if present; from 2 to 3% by weight of silver, and the rare earths containing not more then 25% by weight of cerium and lanthanum taken together.
8. An article composed of an alloy according to claim 1 which has been solution heat treated at a temperature from 450°C to the solidus of the alloy, followed by quenching and ageing at a temperature from 100°C to 350°C.
9. An article composed of an alloy according to claim 7 which has been solution heat treated at a temperature from 450°C to the solidus of the alloy, followed by quenching and ageing at a temperature from 100°C to 350°C.
10. An article according to claim 8 or 9, which has been solution treated for a period of at least two hours and aged for a period of at least half an hour.
11. An article according to claims 8 or 9, which has been solution heat treated at a temperature of about 520°C
for a period of 8 hours and aged at a temperature of about 200 DC for 16 hours.
for a period of 8 hours and aged at a temperature of about 200 DC for 16 hours.
12. An article according to claim 8 or 9, which has been solution heat treated firstly at 480°C for 8 hours and secondly at 520°C for 4 hours followed by ageing at a temperature of 250°C for 8 hours.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB5602174A GB1463608A (en) | 1974-12-30 | 1974-12-30 | Magnesium alloys |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1047282A true CA1047282A (en) | 1979-01-30 |
Family
ID=10475539
Family Applications (3)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA242,645A Expired CA1066923A (en) | 1974-12-30 | 1975-12-29 | Magnesium alloys |
| CA242,643A Expired CA1053484A (en) | 1974-12-30 | 1975-12-29 | Magnesium alloys |
| CA242,644A Expired CA1047282A (en) | 1974-12-30 | 1975-12-29 | Magnesium alloys |
Family Applications Before (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA242,645A Expired CA1066923A (en) | 1974-12-30 | 1975-12-29 | Magnesium alloys |
| CA242,643A Expired CA1053484A (en) | 1974-12-30 | 1975-12-29 | Magnesium alloys |
Country Status (14)
| Country | Link |
|---|---|
| JP (3) | JPS594497B2 (en) |
| AU (2) | AU507250B2 (en) |
| BE (3) | BE837170A (en) |
| CA (3) | CA1066923A (en) |
| CH (3) | CH611650A5 (en) |
| DE (3) | DE2558519C2 (en) |
| FR (3) | FR2296698A1 (en) |
| GB (1) | GB1463608A (en) |
| IL (3) | IL48762A (en) |
| IN (3) | IN155906B (en) |
| IT (3) | IT1052035B (en) |
| NL (3) | NL7515190A (en) |
| NO (3) | NO142580C (en) |
| SE (3) | SE421635B (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6240872U (en) * | 1985-08-27 | 1987-03-11 | ||
| JPS63174477U (en) * | 1987-01-21 | 1988-11-11 | ||
| DE10003970B4 (en) * | 2000-01-25 | 2005-09-22 | Technische Universität Clausthal | Process for producing magnesium alloys having a superplastic microstructure |
| JP3592310B2 (en) | 2001-06-05 | 2004-11-24 | 住友電工スチールワイヤー株式会社 | Magnesium-based alloy wire and method of manufacturing the same |
| AUPS311202A0 (en) * | 2002-06-21 | 2002-07-18 | Cast Centre Pty Ltd | Creep resistant magnesium alloy |
| WO2007139438A2 (en) * | 2006-05-26 | 2007-12-06 | Obschestvo S Ogranichennoi Otvetstvennostuy 'vniibt-Burovoy Instrument' | Worm gerotor pump |
| BRPI0912151A2 (en) * | 2008-06-06 | 2018-11-06 | Synthes Gmbh | resorbable magnesium alloy |
| DE102010008393A1 (en) | 2010-02-10 | 2011-10-06 | Technische Universität Dresden | Substrate for soil improvement with water-retaining property, process for its preparation and its use |
| GB201413327D0 (en) | 2014-07-28 | 2014-09-10 | Magnesium Elektron Ltd | Corrodible downhole article |
| GB201700714D0 (en) | 2017-01-16 | 2017-03-01 | Magnesium Elektron Ltd | Corrodible downhole article |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1243398B (en) * | 1958-05-16 | 1967-06-29 | Magnesium Elektron Ltd | Cast or wrought magnesium alloy containing rare earth metals |
-
1974
- 1974-12-30 GB GB5602174A patent/GB1463608A/en not_active Expired
-
1975
- 1975-12-20 IN IN2366/CAL/75A patent/IN155906B/en unknown
- 1975-12-20 IN IN2365/CAL/1975A patent/IN142860B/en unknown
- 1975-12-22 NO NO754344A patent/NO142580C/en unknown
- 1975-12-22 NO NO754345A patent/NO142581C/en unknown
- 1975-12-23 IN IN2376/CAL/1975A patent/IN143219B/en unknown
- 1975-12-23 AU AU87815/75A patent/AU507250B2/en not_active Expired
- 1975-12-23 NO NO754367A patent/NO142582C/en unknown
- 1975-12-23 AU AU87814/75A patent/AU500182B2/en not_active Expired
- 1975-12-24 DE DE2558519A patent/DE2558519C2/en not_active Expired
- 1975-12-24 CH CH1677575A patent/CH611650A5/en not_active IP Right Cessation
- 1975-12-24 CH CH7516776A patent/CH608833A5/en not_active IP Right Cessation
- 1975-12-24 DE DE2558545A patent/DE2558545C2/en not_active Expired
- 1975-12-24 CH CH7516774A patent/CH608832A5/en not_active IP Right Cessation
- 1975-12-29 JP JP50159636A patent/JPS594497B2/en not_active Expired
- 1975-12-29 SE SE7514711A patent/SE421635B/en not_active IP Right Cessation
- 1975-12-29 SE SE7514709A patent/SE421634B/en not_active IP Right Cessation
- 1975-12-29 JP JP50159635A patent/JPS5856742B2/en not_active Expired
- 1975-12-29 CA CA242,645A patent/CA1066923A/en not_active Expired
- 1975-12-29 DE DE2558915A patent/DE2558915C2/en not_active Expired
- 1975-12-29 SE SE7514710A patent/SE448241B/en not_active IP Right Cessation
- 1975-12-29 IL IL48762A patent/IL48762A/en unknown
- 1975-12-29 CA CA242,643A patent/CA1053484A/en not_active Expired
- 1975-12-29 CA CA242,644A patent/CA1047282A/en not_active Expired
- 1975-12-29 IL IL48761A patent/IL48761A/en unknown
- 1975-12-29 IL IL48763A patent/IL48763A/en unknown
- 1975-12-29 JP JP50159634A patent/JPS5918457B2/en not_active Expired
- 1975-12-30 BE BE163186A patent/BE837170A/en not_active IP Right Cessation
- 1975-12-30 IT IT30858/75A patent/IT1052035B/en active
- 1975-12-30 FR FR7540123A patent/FR2296698A1/en active Granted
- 1975-12-30 BE BE163187A patent/BE837171A/en not_active IP Right Cessation
- 1975-12-30 FR FR7540121A patent/FR2296696A1/en active Granted
- 1975-12-30 IT IT30860/75A patent/IT1052037B/en active
- 1975-12-30 NL NL7515190A patent/NL7515190A/en not_active Application Discontinuation
- 1975-12-30 IT IT30859/75A patent/IT1052036B/en active
- 1975-12-30 BE BE163185A patent/BE837169A/en not_active IP Right Cessation
- 1975-12-30 NL NL7515192A patent/NL7515192A/en not_active Application Discontinuation
- 1975-12-30 FR FR7540122A patent/FR2296697A1/en active Granted
- 1975-12-30 NL NL7515191A patent/NL7515191A/en not_active Application Discontinuation
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