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EP1546422A4 - PROCESS FOR FORMING MOLYBDENE OXIDE ALLOYS OF LANTHANE RESISTANT TO STIFFENING - Google Patents

PROCESS FOR FORMING MOLYBDENE OXIDE ALLOYS OF LANTHANE RESISTANT TO STIFFENING

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Publication number
EP1546422A4
EP1546422A4 EP03794565A EP03794565A EP1546422A4 EP 1546422 A4 EP1546422 A4 EP 1546422A4 EP 03794565 A EP03794565 A EP 03794565A EP 03794565 A EP03794565 A EP 03794565A EP 1546422 A4 EP1546422 A4 EP 1546422A4
Authority
EP
European Patent Office
Prior art keywords
lanthana
molybdenum
weight percent
sintered body
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.)
Granted
Application number
EP03794565A
Other languages
German (de)
French (fr)
Other versions
EP1546422A1 (en
EP1546422B1 (en
Inventor
Maria B Winnicka
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Osram Sylvania Inc
Original Assignee
Osram Sylvania Inc
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Filing date
Publication date
Application filed by Osram Sylvania Inc filed Critical Osram Sylvania Inc
Publication of EP1546422A1 publication Critical patent/EP1546422A1/en
Publication of EP1546422A4 publication Critical patent/EP1546422A4/en
Application granted granted Critical
Publication of EP1546422B1 publication Critical patent/EP1546422B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/12—Both compacting and sintering
    • B22F3/16—Both compacting and sintering in successive or repeated steps
    • B22F3/162—Machining, working after consolidation
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/12—Both compacting and sintering
    • B22F3/16—Both compacting and sintering in successive or repeated steps
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/24—After-treatment of workpieces or articles
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C27/00—Alloys based on rhenium or a refractory metal not mentioned in groups C22C14/00 or C22C16/00
    • C22C27/04—Alloys based on tungsten or molybdenum
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
    • C22C32/001—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with only oxides
    • C22C32/0015—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with only oxides with only single oxides as main non-metallic constituents
    • C22C32/0031—Matrix based on refractory metals, W, Mo, Nb, Hf, Ta, Zr, Ti, V or alloys thereof
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/24—After-treatment of workpieces or articles
    • B22F2003/247—Removing material: carving, cleaning, grinding, hobbing, honing, lapping, polishing, milling, shaving, skiving, turning the surface
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/24—After-treatment of workpieces or articles
    • B22F2003/248—Thermal after-treatment
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy

Definitions

  • This invention relates generally to methods for forming dispersion-strengthened alloys of molybdenum. More particularly, this invention relates to methods of forming molybdenum-lanthana alloys having non-sag microstructures .
  • Molybdenum alloys which have been dispersion-strengthened with particles of lanthanum oxide (lanthana) , La 2 0 3 , are desirable for use in high temperature applications because of their high melting point and good mechanical properties at high temperatures, in particular, resistance to sag and creep.
  • the alloys are formed by combining molybdenum powder with from about 0.1 to about 5 weight percent (wt.%) of lanthanum oxide powder or an equivalent amount of a lanthanum oxide precursor, such as La(0H) 3 or La(N0 3 ) , which is then converted to the oxide by heating.
  • the size of the lanthanum oxide particles dispersed in the molybdenum matrix is generally preferred to be less than about 1 ⁇ m, however, the particles may be as large 5-10 ⁇ .
  • the sintered body is deformed by mechanical working, e.g., rolling, swaging, drawing, or hammering, and then is then recrystallized to generate the desired microstructure .
  • the preferred microstructure consists of large, interlocking grains which are elongated in the direction of the applied mechanical work.
  • the recrystallization behavior of the alloy is affected by the prior amount of deformation. When the undeformed or fully recrystallized alloy is being cold worked, the density of dislocations within the alloy increases. This occurs first at the grain boundaries and then progresses further into the bulk of the grains as the amount of cold work increases.
  • Prior art methods have employed high degrees of deformation (>60%) in order to achieve hi ' gh-temperature strength and creep-resistance.
  • Japanese Patent Publication 59-177345 (1984) describes a molybdenum-lanthana alloy for structural purposes.
  • the alloy has a high secondary recrystallization temperature and high high-temperature strength.
  • the alloy contains 1 to 5 wt.% lanthana (La 2 0 3 ) particles having an average size of not more than 3 ⁇ m which are uniformly dispersed in molybdenum.
  • the material is preferably worked from the sinter by a working factor of at least 60% and then heated above the secondary recrystallization temperature.
  • One disadvantage with the prior art methods is that the dimensions of the feed material must be substantially greater than the dimensions of the finally recrystallized material in order to impart the required high degree of deformation. This leads to less flexibility in the manufacturing process.
  • Another disadvantage is that the large amount of stored energy in the material caused by the high degree of deformation can lead to spontaneous grain growth in the material during recrystallization. This may make it more difficult to control grain size in the finally recrystallized material.
  • a non-sag microstructure can be obtained in a molybdenum-lanthana alloy using a degree of deformation of from about 7% to about 18%.
  • the degree of deformation refers to the percentage reduction in at least one dimension of the feed material, e.g., sheet thickness.
  • the degree of deformation is from about 12% to about 17%.
  • the alloy may be deformed directly from the as-sintered state to its finished form and then finally recrystallized or, preferably, the alloy can worked from the as-sintered state to a near-finished form, recrystallized, and then deformed to its finished form and finally recrystallized.
  • the recrystallization of the alloy in its near-finished form is conducted at a temperature of from about 1150°C to about 1400°C.
  • the final recrystallization is preferably conducted at about 1900°C.
  • the amount of lanthana in the alloy ranges from 0.4 wt.% to about 1.0 wt.%, more preferably, from about 0.6 wt.% to about 0.7 wt.%.
  • the grain size after final recrystallization is larger because the predominant mechanism occurring during the heat treatment is the annihilation of dislocations at the neighboring grain boundaries causing some grain boundaries to disappear. This is generally referred to as strain-induced grain boundary migration.
  • the grains tend to exhibit less elongation than grains resulting from methods which use high degrees of deformation.
  • the aspect ratio for the grains produced by the method of this invention is no more than 4:1.
  • the degree of reformation needed to produce the non-sag microstructure is about 18% or less, the feed material need not be much larger than the finished product and there is a greater potential to control grain size in the finished material because of the lower amount of stored energy in the material prior to final recrystallization.
  • the method of this invention is more flexible for manufacturers of refractory metal products.
  • Fig. 1A is a photomicrograph of the microstructure of the molybdenum-lanthana alloy of Example 1 after recrystallization and rolling to 0.15 cm thickness.
  • Fig. IB is a photomicrograph of non-sag microstructure of the molybdenum-lanthana alloy of Example 1 after final recrystallization .
  • Fig. 2A is a photomicrograph of the microstructure of the molybdenum-lanthana alloy of Example 2 after recrystallization and rolling to 0.10 cm thickness.
  • Fig. 2B is a photomicrograph of non-sag microstructure of the molybdenum-lanthana alloy of Example 2 after final recrystallization .
  • Pure molybdenum metal powder with grain size of 3.5 ⁇ m was mixed with 0.7 weight percent (wt.%) of La(0H) 3 powder having a grain size of 0.65 ⁇ m.
  • the mixture was isostatically pressed at 240 MPa to form a pressed slab with dimensions of 64 cm x 38 cm x 5 cm.
  • the slab was subsequently rolled at varying temperatures; starting at 980°C, followed by 785°C, and finally at ambient temperature to a thickness of 0.17 cm.
  • the sheet was then recrystallized at 1400°C and then rolled at ambient temperature to the thickness of 0.15 cm, (about 12% deformation) .
  • the microstructure of the recrystallized and rolled sheet is shown in Fig. 1A.
  • the rolled sheet was subjected to a final recrystallization anneal at 1900°C to produce the non-sag microstructure which is shown in Fig. IB.
  • Pure molybdenum metal powder with grain size of 3.5 ⁇ m was mixed with 0.7 wt.% La(0H) 3 powder with a grain size of 0.65 ⁇ m.
  • the mixture was isostatically pressed at 240 MPa to form a pressed slab with dimensions of 64 cm x 38 cm x 5 cm.
  • the slab was subsequently rolled at varying temperatures; starting at 980°C, followed by 785°C, and finally at ambient temperature to a thickness of 0.12 cm.
  • the sheet was then recrystallized at 1150°C. Subsequently it was rolled at ambient temperature to the thickness of 0.10 cm (about 17% deformation) .
  • the microstructure of the recrystallized and rolled sheet is shown in Fig. 2A.
  • the sheet material exhibited the non-sag microstructure shown in Fig. 2B.
  • the sag resistance of 0.5 in. x 5.6 in. samples of the non-sag molybdenum-lanthana sheet material from Examples 1 and 2 was measured according to the following procedure. The samples were supported at opposite ends and a 10 g weight placed on the sample at the center point between the supports. The distance between the supports was 4.2 inches. At the start of the test, the distance between the reference plate and the 0.15-cm-thick sample was 0.5 in. at the point directly below the 10-g load. The corresponding distance for the 0.10-cm-thick sample was 0.4375 in. at the start of the test. Sag was measured as the amount of deflection of the sample toward the reference plate after heating the sample at 1900°C for 1 hour.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Organic Chemistry (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Manufacturing & Machinery (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Powder Metallurgy (AREA)
  • Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
  • Polyurethanes Or Polyureas (AREA)

Abstract

A method for forming a molybdenum-lanthana alloy is described wherein a non-sag microstructure is achieved by mechanically working an as-sintered or recrystallized body to obtain a degree of deformation of from about 7% to about 18% and then subjecting the lightly worked body to a final recrystallization.

Description

Method of Forming Non-sag Molybdenum-Lanthana Alloys
TECHNICAL FIELD
This invention relates generally to methods for forming dispersion-strengthened alloys of molybdenum. More particularly, this invention relates to methods of forming molybdenum-lanthana alloys having non-sag microstructures .
BACKGROUND OF THE INVENTION
Molybdenum alloys which have been dispersion-strengthened with particles of lanthanum oxide (lanthana) , La203, are desirable for use in high temperature applications because of their high melting point and good mechanical properties at high temperatures, in particular, resistance to sag and creep. The alloys are formed by combining molybdenum powder with from about 0.1 to about 5 weight percent (wt.%) of lanthanum oxide powder or an equivalent amount of a lanthanum oxide precursor, such as La(0H)3 or La(N03) , which is then converted to the oxide by heating. The size of the lanthanum oxide particles dispersed in the molybdenum matrix is generally preferred to be less than about 1 μm, however, the particles may be as large 5-10 μ . After compacting and sintering, the sintered body is deformed by mechanical working, e.g., rolling, swaging, drawing, or hammering, and then is then recrystallized to generate the desired microstructure . For sag and creep resistance, the preferred microstructure consists of large, interlocking grains which are elongated in the direction of the applied mechanical work. The recrystallization behavior of the alloy is affected by the prior amount of deformation. When the undeformed or fully recrystallized alloy is being cold worked, the density of dislocations within the alloy increases. This occurs first at the grain boundaries and then progresses further into the bulk of the grains as the amount of cold work increases. Prior art methods have employed high degrees of deformation (>60%) in order to achieve hi'gh-temperature strength and creep-resistance.
Japanese Patent Publication 59-177345 (1984) describes a molybdenum-lanthana alloy for structural purposes. The alloy has a high secondary recrystallization temperature and high high-temperature strength. The alloy contains 1 to 5 wt.% lanthana (La203) particles having an average size of not more than 3 μm which are uniformly dispersed in molybdenum. For structural purposes, the material is preferably worked from the sinter by a working factor of at least 60% and then heated above the secondary recrystallization temperature.
U.S. Patent No. 4,950,327 to Eck et al . (1990) describes a high- temperature, creep-resistant molybdenum-lanthana alloy having a tiered structural arrangement. After sintering, the alloy is mechanically reformed in gradations of about 10% without heating the alloy above its recrystallization temperature. Once the degree of reforming is at least 85%, the alloy is finally subjected to a recrystallization anneal.
One disadvantage with the prior art methods is that the dimensions of the feed material must be substantially greater than the dimensions of the finally recrystallized material in order to impart the required high degree of deformation. This leads to less flexibility in the manufacturing process. Another disadvantage is that the large amount of stored energy in the material caused by the high degree of deformation can lead to spontaneous grain growth in the material during recrystallization. This may make it more difficult to control grain size in the finally recrystallized material.
SUMMARY OF THE INVENTION
It has been discovered that a non-sag microstructure can be obtained in a molybdenum-lanthana alloy using a degree of deformation of from about 7% to about 18%. As used herein, the degree of deformation refers to the percentage reduction in at least one dimension of the feed material, e.g., sheet thickness. Preferably, the degree of deformation is from about 12% to about 17%. The alloy may be deformed directly from the as-sintered state to its finished form and then finally recrystallized or, preferably, the alloy can worked from the as-sintered state to a near-finished form, recrystallized, and then deformed to its finished form and finally recrystallized. Preferably, the recrystallization of the alloy in its near-finished form is conducted at a temperature of from about 1150°C to about 1400°C. The final recrystallization is preferably conducted at about 1900°C. Preferably, the amount of lanthana in the alloy ranges from 0.4 wt.% to about 1.0 wt.%, more preferably, from about 0.6 wt.% to about 0.7 wt.%.
The grain size after final recrystallization is larger because the predominant mechanism occurring during the heat treatment is the annihilation of dislocations at the neighboring grain boundaries causing some grain boundaries to disappear. This is generally referred to as strain-induced grain boundary migration. After final recrystallization, the grains tend to exhibit less elongation than grains resulting from methods which use high degrees of deformation. Typically, the aspect ratio for the grains produced by the method of this invention is no more than 4:1. Also, since the degree of reformation needed to produce the non-sag microstructure is about 18% or less, the feed material need not be much larger than the finished product and there is a greater potential to control grain size in the finished material because of the lower amount of stored energy in the material prior to final recrystallization. Hence, the method of this invention is more flexible for manufacturers of refractory metal products.
BRIEF DESCRIPTION OF THE DRAWINGS
Fig. 1A is a photomicrograph of the microstructure of the molybdenum-lanthana alloy of Example 1 after recrystallization and rolling to 0.15 cm thickness.
Fig. IB is a photomicrograph of non-sag microstructure of the molybdenum-lanthana alloy of Example 1 after final recrystallization .
Fig. 2A is a photomicrograph of the microstructure of the molybdenum-lanthana alloy of Example 2 after recrystallization and rolling to 0.10 cm thickness.
Fig. 2B is a photomicrograph of non-sag microstructure of the molybdenum-lanthana alloy of Example 2 after final recrystallization .
DETAILED DESCRIPTION OF THE INVENTION
For a better understanding of the present invention, together with other and further objects, advantages and capabilities thereof, reference is made to the following disclosure and appended claims taken in conjunction with the above-described drawings .
EXAMPLE 1
Pure molybdenum metal powder with grain size of 3.5 μm was mixed with 0.7 weight percent (wt.%) of La(0H)3 powder having a grain size of 0.65 μm. The mixture was isostatically pressed at 240 MPa to form a pressed slab with dimensions of 64 cm x 38 cm x 5 cm. The slab was subsequently rolled at varying temperatures; starting at 980°C, followed by 785°C, and finally at ambient temperature to a thickness of 0.17 cm. The sheet was then recrystallized at 1400°C and then rolled at ambient temperature to the thickness of 0.15 cm, (about 12% deformation) . The microstructure of the recrystallized and rolled sheet is shown in Fig. 1A. The rolled sheet was subjected to a final recrystallization anneal at 1900°C to produce the non-sag microstructure which is shown in Fig. IB.
Example 2
Pure molybdenum metal powder with grain size of 3.5 μm was mixed with 0.7 wt.% La(0H)3 powder with a grain size of 0.65 μm. The mixture was isostatically pressed at 240 MPa to form a pressed slab with dimensions of 64 cm x 38 cm x 5 cm. The slab was subsequently rolled at varying temperatures; starting at 980°C, followed by 785°C, and finally at ambient temperature to a thickness of 0.12 cm. The sheet was then recrystallized at 1150°C. Subsequently it was rolled at ambient temperature to the thickness of 0.10 cm (about 17% deformation) . The microstructure of the recrystallized and rolled sheet is shown in Fig. 2A. Upon a final recrystallization anneal at 1900°C, the sheet material exhibited the non-sag microstructure shown in Fig. 2B.
The sag resistance of 0.5 in. x 5.6 in. samples of the non-sag molybdenum-lanthana sheet material from Examples 1 and 2 was measured according to the following procedure. The samples were supported at opposite ends and a 10 g weight placed on the sample at the center point between the supports. The distance between the supports was 4.2 inches. At the start of the test, the distance between the reference plate and the 0.15-cm-thick sample was 0.5 in. at the point directly below the 10-g load. The corresponding distance for the 0.10-cm-thick sample was 0.4375 in. at the start of the test. Sag was measured as the amount of deflection of the sample toward the reference plate after heating the sample at 1900°C for 1 hour. Six such heating cycles were carried out for each sample and the amount of deflection measured after each cycle. The cumulative amount of deflection is reported in the following table. The sag resistance of the materials was found to be equivalent to commercially available non-sag molybdenum-lanthana sheet material .
Table
While there has been shown and described what are at the present considered the preferred embodiments of the invention, it will be obvious to those skilled in the art that various changes and modifications may be made therein without departing from the scope of the invention as defined by the appended claims.

Claims

I claim:
1. A method for forming a non-sag molybdenum-lanthana alloy comprising:
(a) forming a sintered body of a molybdenum-lanthana alloy wherein the alloy contains from about 0.1 weight percent to about 5 weight percent lanthana;
(b) mechanically working the sintered body to a near- finished form;
(c) recrystallizing the sintered body in its near-finished form;
(d) mechanically deforming the sintered body to a finished form wherein the degree of deformation is from about 7% to about 18%; and
(e) subjecting the sintered body in its finished form to a final recrystallization annealing.
2. The method of claim 1 wherein the degree of deformation is from about 12% to about 17%.
3. The method of claim 1 wherein the final recrystallization annealing is performed at about 1900°C.
4. The method of claim 1 wherein the sintered body in its near-finished form is recrystallized at a temperature from about 1150°C to about 1400°C.
5. The method of claim 1 wherein the molybdenum-lanthana alloy contains from about 0.4 weight percent to about 1.0 weight percent lanthana.
6. The method of claim 1 wherein the sintered body is subjected to one or more heat treatments during the mechanical working in step (b) .
7. The method of claim 3 wherein the molybdenum-lanthana alloy contains from about 0.6 weight percent to about 0.7 weight percent lanthana.
8. A method for forming a non-sag molybdenum-lanthana alloy comprising:
(a) forming a sintered body of a molybdenum-lanthana alloy wherein the alloy contains from about 0.4 weight percent to about 1.0 weight percent lanthana;
(b) mechanically working the sintered body to a near- finished form;
(c) recrystallizing the sintered body in its near-finished form at a temperature from about 1150 °C to about 1400°C;
(d) mechanically deforming the sintered body to a finished form wherein the degree of deformation is from about 7% to about 18%; and
(e) subjecting the sintered body in its finished form to a final recrystallization annealing at a temperature of about 1900°C.
9. The method of claim 8 wherein the degree of deformation is from about 12% to about 17%.
10. The method of claim 8 wherein the molybdenum-lanthana alloy contains from about 0.6 weight percent to about 0.7 weight percent lanthana.
11. A method for forming a non-sag molybdenum-lanthana alloy comprising :
(a) forming a sintered body of a molybdenum-lanthana alloy wherein the alloy contains from about 0.1 weight percent to about 5 weight percent lanthana;
(b) mechanically deforming the sintered body to a finished form wherein the degree of deformation is from about 7% to about 18%; and
(c) subjecting the sintered body in its finished form to a final recrystallization annealing.
12. The method of claim 11 wherein the degree of deformation is from about 12% to about 17%.
13. The method of claim 11 wherein the final recrystallization annealing is performed at about 1900°C.
1 . The method of claim 11 wherein the molybdenum-lanthana alloy contains from about 0.4 weight percent to about 1.0 weight percent lanthana.
15. The method of claim 11 wherein the molybdenum-lanthana alloy contains from about 0.6 weight percent to about 0.7 weight percent lanthana.
16. The method of claim 13 wherein the degree of deformation is from about 12% to about 17%.
17. The method of claim 16 wherein the molybdenum-lanthana alloy contains from about 0.6 weight percent to about 0.7 weight percent lanthana.
EP03794565A 2002-09-04 2003-09-04 Method of forming sag-resistant molybdenum-lanthana alloys Expired - Lifetime EP1546422B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US40808702P 2002-09-04 2002-09-04
US408087P 2002-09-04
PCT/US2003/027439 WO2004022801A1 (en) 2002-09-04 2003-09-04 Method of forming non-sag molybdenum-lanthana alloys

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EP1546422A1 EP1546422A1 (en) 2005-06-29
EP1546422A4 true EP1546422A4 (en) 2006-04-05
EP1546422B1 EP1546422B1 (en) 2007-02-21

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US (1) US20060073063A1 (en)
EP (1) EP1546422B1 (en)
AT (1) ATE354683T1 (en)
AU (1) AU2003263051A1 (en)
DE (1) DE60312012T2 (en)
WO (1) WO2004022801A1 (en)

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CA2522844A1 (en) * 2003-04-23 2004-11-04 H.C. Starck Inc. Molybdenum alloy x-ray targets having uniform grain structure
US20110100356A1 (en) * 2009-10-13 2011-05-05 Wayne Thomas Bliesner Reversible hydride thermal energy storage cell optimized for solar applications
CN102626845B (en) * 2012-03-27 2015-06-03 苏州先端稀有金属有限公司 Molybdenum lanthanum alloy tray processing method
KR102722614B1 (en) * 2016-08-05 2024-10-28 삼성디스플레이 주식회사 Linear evaporation source and deposition apparatus including the same

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WO2004022801A1 (en) 2004-03-18
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US20060073063A1 (en) 2006-04-06
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