EP0072175A1 - Method of producing a monolithic alloy component preform - Google Patents
Method of producing a monolithic alloy component preform Download PDFInfo
- Publication number
- EP0072175A1 EP0072175A1 EP82304080A EP82304080A EP0072175A1 EP 0072175 A1 EP0072175 A1 EP 0072175A1 EP 82304080 A EP82304080 A EP 82304080A EP 82304080 A EP82304080 A EP 82304080A EP 0072175 A1 EP0072175 A1 EP 0072175A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- alloy
- alloys
- interface
- confining means
- powdered
- 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
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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
- B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
- B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
Definitions
- This invention relates to a method of producing a monolithic alloy component preform.
- the different alloys and properties thereof are utilized in a single component by bringing the alloys together in powder form prior to powder consolidation.
- Such consolidation may be hot isostatic pressing (HIP), consolidation at atomspheric pressure (CAP) etc.
- a method of producing a monolithic powdered alloy component preform from at least two different powdered alloys comprises the steps of placing the powders adjacent each other and consolidating the alloys, and causing a controlled mixing or diffusion of the powdered alloy particles or elements therein in an interface zone prior to or during the consolidation step or possible further metallurgical treatment.
- the invention also comprise a method of producing a multi-alloy component preform by powder metallurgy comprising the steps of introducing the powdered alloys into an outer mold or can having an inner shape corresponding to the outer shape of the desired preform, substantially confining the main bulk of each powdered alloy to a predetermined portion of the preform by providing a confining means substantially separating two different alloys and defining an interface therebetween and subsequently substantially removing said confining means, consolidating said powdered alloys into a preform, and causing a controlled mixing or diffusion of the powdered alloy particles or elements therein in an interface zone prior to or during the consolidation step or possible further metallurgical treatment, thus producing an interface alloy.
- a radial flow turbine wheel preform 10 is shown to consist of an inner hub portion of alloy B and an outer blade portion of alloy A bonded together into a monolithic component at an interface or rather an interface zone 11.
- Fig. 3 the method of producing such a preform in the form of a cylindrical disc having concentric alloy portion is diagramatically illustrated.
- the preform is initially shaped by means of an outer mold or can 12 which the powdered alloys fill.
- the outer can 12 is positioned in an enclosure 13 placed under vacuum or filled with inert gas to prevent oxidation of the powder particles as well known in the art.
- a confining means in the form of a basket 14 is positioned concentrically within the outer can 12. The two concentric compartments on either side of the basket 14 are filled with the two alloys as indicated.
- the interface-forming basket 14 may have a grid or screen structure, or it can be made from a perforated sheet, as a zig-zag wall with or without perforations, as a smooth wall etc.
- the purpose of the basket is one or more of the following:
- the controlled mixing of the powdered alloy particles to provide the interface zone can be obtained by allowing a controlled flow of one powder into the other through the basket 14, when in form of a grid, a screen or the like.
- the filling operation may be controlled so that the rising powder level in one compartment precedes that in the other by a fixed or variable height ( h) so that a powder flow from one to the other compartment can take place above the level in the other compartment with the only restriction being offered by the grid itself.
- h the specific gravity of the two powders as well as other factors which will influence the behaviour of the flow of powder into the other compartment will have to be taken into account.
- the height h and/or the restriction offered by the grid can be controlled to vary the amount of mixing of one alloy into the other and/or the thickness of the resulting interface zone. Variation of the latter can be used to compensate for interface zone slimming during subsequent forging of the preform.
- the controlled transfer of portions of one powdered alloy into the adjacent layer of the other powdered alloy can also be achieved in other ways, for instance by rotating the inner basket 14 or even rotating the basket as well as the outer can 12 using the centrifugal force to provide said controlled transfer. Shaking would be a further alternative. Instead of transferring powder particles, merely one or more elements of one alloy may be transferred across the interface to form an interface zone, and this may be accomplished by diffusion when the basket 14 has been removed prior to or during the consolidation step or possible further metallurgical treatment.
- a zig-zag type basket as shown in Fig. 4 would provide a considerable interface zone by diffusion alone.
- the basket 14 may be removed by decomposing or melting the material in the basket whereupon the molten or decomposed material is extracted and/or evaporated.
- the material may also be incorporated in one or both of the alloys A or B or in the interface alloy.
- Both the basket 14 and the outer can 12 may have different shapes in order to give the best final outer shape and interface configuration as illustrated in Fig. 5 for the basket 14.
- the powder preform After the powder preform has been consolidated, for example by hot isostatic pressing, it may be subjected to superplastic or hot die forging in which the material will flow into its near net shape. The turbine wheel blank would then be ready for heat treatment and final machining. Hot isostatic pressing may be used to shape the preform to final near net shape instead of merely for consolidation purposes.
- the method described will provide a sound monolithic structure without the many uncertain aspects connected with diffusion bonding of solid parts.
- the interface alloy will provide a compliance zone between the two alloys which for example could have a coefficient of expansion between those of the alloys A and B after the powder preform has been consolidated.
- a pressing and/or forging operation can follow which will give final dimensions prior to machining, as shown as an example in Fig. 6, in which the interface is indicated at 11 before forging and at 15 after forging.
- the outer contour of the preform is indicated at 16 and that of the final turbine wheel at 17.
- the line 16' indicates the contour between the blade and the hub portion of the turbine wheel.
- Trial and error methods will have to be used to determine the interface configuration 11 in the preform 10 which will result in the desired interface configuration 15 in the final component.
- the interface alloy now has properties which lies between those of A and B. Thus, there is no sharp "bonding line" between the two alloys.
- a preform according to the invention can consist of more than two alloys and more than one basket 14.
- a basket can be pre-loaded with powder prior to inserting the basket into the outer can. This is illustrated in Fig. 7, in which a basket 14' preloaded with powdered alloy B and a basket 14" preloaded with powdered alloy C may be placed into the outer can 12, whereupon a powdered alloy A may be introduced to fill the remaining space between the two baskets.
- the baskets would have an internal air tight seal 18 of a material which would easily be decomposed and may be extracted or absorbed into the powder on either side of the basket when exposed to the operation temperature of the consolidation process or to other influences.
- material C could be an alloy which is resistant to corrosion and abrasion at high temperature, whereas the requirement for high ultimate tensile strength is less than for the alloys A and B.
- the alloy B would be the alloy of the highest tensile strength.
- the properties of alloy A would fall between those of alloys B and C.
- the method of the invention has the potential of giving turbines the ability to operate at very high temperatures and tip-speeds without incurring risk of failure by inadequate and unreliable bonding.
- the method offers numerous interface geometry choices for the optimization of the structural properties of the finished turbines.
- alloy should be taken to refer to any solid, structural composition composed of two or more chemical elements of which at least one is a metal, providing this composition lends itself to powder metallurgy processing methods including consolidation steps.
- alloy not only mixtures of elemental metals, but also compositions such as metal carbides and ceramic materials are comprised by the term "alloy" as used in the present Specification.
Abstract
Description
- This invention relates to a method of producing a monolithic alloy component preform.
- In highly loaded structures and components, such as gas turbine rotors, the range of properties required very often extend beyond that which is available from a single alloy. As a result of this, various schemes have been proposed and/or tried wherein one component or part is composed of two portions welded, brazed or diffusion bonded together. Generally, however, such methods do not provide the desired bond quality and also often cause a reduction in properties on or near the interface between the two portions.
- According to the present invention the different alloys and properties thereof are utilized in a single component by bringing the alloys together in powder form prior to powder consolidation. Such consolidation may be hot isostatic pressing (HIP), consolidation at atomspheric pressure (CAP) etc.
- According to one aspect of the invention, a method of producing a monolithic powdered alloy component preform from at least two different powdered alloys comprises the steps of placing the powders adjacent each other and consolidating the alloys, and causing a controlled mixing or diffusion of the powdered alloy particles or elements therein in an interface zone prior to or during the consolidation step or possible further metallurgical treatment.
- The invention also comprise a method of producing a multi-alloy component preform by powder metallurgy comprising the steps of introducing the powdered alloys into an outer mold or can having an inner shape corresponding to the outer shape of the desired preform, substantially confining the main bulk of each powdered alloy to a predetermined portion of the preform by providing a confining means substantially separating two different alloys and defining an interface therebetween and subsequently substantially removing said confining means, consolidating said powdered alloys into a preform, and causing a controlled mixing or diffusion of the powdered alloy particles or elements therein in an interface zone prior to or during the consolidation step or possible further metallurgical treatment, thus producing an interface alloy.
- The invention will now be described in more detail solely by way of example, with reference to the accompanying drawings, in which
- Fig. 1 is a fragmentary, axial, cross-sectional view of a radial flow turbine wheel preform,
- Fig. 2 is a cross-sectional view of the preform illustrated in Fig. 1 along the line II-II thereof,
- Fig. 3 is a diagrammatic vertical cross-sectional view of an apparatus for introducing the powdered alloys into the outer mold or can in the production of a disc-shaped preform having concentric alloy portions,
- Fig. 4 is a fragmentary cross-sectional view of a mold with an enclosure means or basket defining a zig-zag-shaped interface,
- Fig. 5 is an axial cross-sectional view of a mold with a non-cylindrical basket,
- Fig. 6 is a diagrammatic illustration of the typical changes in the outer shape and the interface when producing a final turbine wheel from a preform of the type illustrated in Fig. 1, and
- Fig. 7 is a diagrammatical cross-sectional view of a component preform comprising three different powdered alloys.
- In Figs. 1 and a radial flow
turbine wheel preform 10 is shown to consist of an inner hub portion of alloy B and an outer blade portion of alloy A bonded together into a monolithic component at an interface or rather an interface zone 11. - In Fig. 3 the method of producing such a preform in the form of a cylindrical disc having concentric alloy portion is diagramatically illustrated. The preform is initially shaped by means of an outer mold or can 12 which the powdered alloys fill. The
outer can 12 is positioned in anenclosure 13 placed under vacuum or filled with inert gas to prevent oxidation of the powder particles as well known in the art. To substantially separate the two powders, a confining means in the form of abasket 14 is positioned concentrically within theouter can 12. The two concentric compartments on either side of thebasket 14 are filled with the two alloys as indicated. The interface-formingbasket 14 may have a grid or screen structure, or it can be made from a perforated sheet, as a zig-zag wall with or without perforations, as a smooth wall etc. The purpose of the basket is one or more of the following: - 1) To separate the main bulk of the two alloys.
- 2) To define the "macro"-geometry of the alloy interface.
- 3) To allow a controlled mixing of some of the powdered alloy particles in an interface zone on either side of the interface-forming basket to provide an interface zone consisting of an interface alloy compatible with both alloy A and alloy B. Alternatively, such an interface zone may be formed by diffusion of elements of one alloy into the other.
- 4) To provide a source of alloying elements needed
- a) for the interface alloy as such or
- b) to supply one or more alloying elements to either of the alloys A or B to compensate for depletion of elements caused by diffusion from alloy A to alloy B or vice versa.
- The controlled mixing of the powdered alloy particles to provide the interface zone can be obtained by allowing a controlled flow of one powder into the other through the
basket 14, when in form of a grid, a screen or the like. For that purpose the filling operation may be controlled so that the rising powder level in one compartment precedes that in the other by a fixed or variable height ( h) so that a powder flow from one to the other compartment can take place above the level in the other compartment with the only restriction being offered by the grid itself. In determining h the specific gravity of the two powders as well as other factors which will influence the behaviour of the flow of powder into the other compartment will have to be taken into account. The height h and/or the restriction offered by the grid can be controlled to vary the amount of mixing of one alloy into the other and/or the thickness of the resulting interface zone. Variation of the latter can be used to compensate for interface zone slimming during subsequent forging of the preform. The controlled transfer of portions of one powdered alloy into the adjacent layer of the other powdered alloy can also be achieved in other ways, for instance by rotating theinner basket 14 or even rotating the basket as well as the outer can 12 using the centrifugal force to provide said controlled transfer. Shaking would be a further alternative. Instead of transferring powder particles, merely one or more elements of one alloy may be transferred across the interface to form an interface zone, and this may be accomplished by diffusion when thebasket 14 has been removed prior to or during the consolidation step or possible further metallurgical treatment. - A zig-zag type basket as shown in Fig. 4 would provide a considerable interface zone by diffusion alone.
- The
basket 14 may be removed by decomposing or melting the material in the basket whereupon the molten or decomposed material is extracted and/or evaporated. However, as mentioned above, the material may also be incorporated in one or both of the alloys A or B or in the interface alloy. - Both the
basket 14 and theouter can 12 may have different shapes in order to give the best final outer shape and interface configuration as illustrated in Fig. 5 for thebasket 14. - After the powder preform has been consolidated, for example by hot isostatic pressing, it may be subjected to superplastic or hot die forging in which the material will flow into its near net shape. The turbine wheel blank would then be ready for heat treatment and final machining. Hot isostatic pressing may be used to shape the preform to final near net shape instead of merely for consolidation purposes.
- The method described will provide a sound monolithic structure without the many uncertain aspects connected with diffusion bonding of solid parts. Also, the interface alloy will provide a compliance zone between the two alloys which for example could have a coefficient of expansion between those of the alloys A and B after the powder preform has been consolidated. A pressing and/or forging operation can follow which will give final dimensions prior to machining, as shown as an example in Fig. 6, in which the interface is indicated at 11 before forging and at 15 after forging. The outer contour of the preform is indicated at 16 and that of the final turbine wheel at 17. The line 16' indicates the contour between the blade and the hub portion of the turbine wheel. Trial and error methods will have to be used to determine the interface configuration 11 in the
preform 10 which will result in the desiredinterface configuration 15 in the final component. The interface alloy now has properties which lies between those of A and B. Thus, there is no sharp "bonding line" between the two alloys. - A preform according to the invention can consist of more than two alloys and more than one
basket 14. Also, a basket can be pre-loaded with powder prior to inserting the basket into the outer can. This is illustrated in Fig. 7, in which a basket 14' preloaded with powdered alloy B and abasket 14" preloaded with powdered alloy C may be placed into theouter can 12, whereupon a powdered alloy A may be introduced to fill the remaining space between the two baskets. In this instance, the baskets would have an internal airtight seal 18 of a material which would easily be decomposed and may be extracted or absorbed into the powder on either side of the basket when exposed to the operation temperature of the consolidation process or to other influences. - In the example in Fig. 7 material C could be an alloy which is resistant to corrosion and abrasion at high temperature, whereas the requirement for high ultimate tensile strength is less than for the alloys A and B. The alloy B would be the alloy of the highest tensile strength. The properties of alloy A would fall between those of alloys B and C.
- The method of the invention has the potential of giving turbines the ability to operate at very high temperatures and tip-speeds without incurring risk of failure by inadequate and unreliable bonding. The method offers numerous interface geometry choices for the optimization of the structural properties of the finished turbines.
- In the specification the term "alloy" should be taken to refer to any solid, structural composition composed of two or more chemical elements of which at least one is a metal, providing this composition lends itself to powder metallurgy processing methods including consolidation steps. Thus, not only mixtures of elemental metals, but also compositions such as metal carbides and ceramic materials are comprised by the term "alloy" as used in the present Specification.
Claims (8)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
NO812680 | 1981-08-07 | ||
NO812680A NO150668C (en) | 1981-08-07 | 1981-08-07 | PROCEDURE FOR THE PREPARATION OF A MONOLITIC MACHINE PART WITH PARTS OF DIFFERENT ALLOY COMPOSITION BY POWDER METAL SURGERY |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0072175A1 true EP0072175A1 (en) | 1983-02-16 |
EP0072175B1 EP0072175B1 (en) | 1986-01-08 |
Family
ID=19886182
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP82304080A Expired EP0072175B1 (en) | 1981-08-07 | 1982-08-02 | Method of producing a monolithic alloy component preform |
Country Status (4)
Country | Link |
---|---|
EP (1) | EP0072175B1 (en) |
JP (1) | JPS5842703A (en) |
DE (1) | DE3268398D1 (en) |
NO (1) | NO150668C (en) |
Cited By (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0202735A2 (en) * | 1985-04-23 | 1986-11-26 | Cameron Iron Works, Inc. | Process for making a composite powder metallurgical billet |
EP0278682A2 (en) * | 1987-02-06 | 1988-08-17 | The Timken Company | Powder metal composite and method of its manufacture |
WO1990014185A1 (en) * | 1989-05-25 | 1990-11-29 | Gkn Technology Limited | Connecting rod |
WO1995019861A1 (en) * | 1994-01-19 | 1995-07-27 | Söderfors Powder Aktiebolag | Method relating to the manufacturing of a composite metal product |
WO1996020058A1 (en) * | 1994-12-23 | 1996-07-04 | Kennametal Inc. | Composite cermet articles and method of making |
US5623723A (en) * | 1995-08-11 | 1997-04-22 | Greenfield; Mark S. | Hard composite and method of making the same |
EP0983813A2 (en) * | 1998-09-03 | 2000-03-08 | Ykk Corporation | Process for producing shaped article |
US6183687B1 (en) | 1995-08-11 | 2001-02-06 | Kennametal Inc. | Hard composite and method of making the same |
CN1091014C (en) * | 1994-12-23 | 2002-09-18 | 钴碳化钨硬质合金公司 | Composite cermet articles and method of making |
US6908688B1 (en) | 2000-08-04 | 2005-06-21 | Kennametal Inc. | Graded composite hardmetals |
EP1724438A2 (en) * | 2005-05-17 | 2006-11-22 | The General Electric Company | Method for making a compositionally graded gas turbine disk |
EP2327493A1 (en) * | 2009-11-26 | 2011-06-01 | Rolls-Royce plc | Method of manufacturing a multiple composition component |
WO2015128597A1 (en) * | 2014-02-28 | 2015-09-03 | Castings Technology International Limited | Forming a composite component |
WO2015169746A1 (en) * | 2014-05-05 | 2015-11-12 | Gkn Sinter Metals Engineering Gmbh | Hydrogen-storage-element production device together with method therefor and hydrogen storage element |
EP2844410A4 (en) * | 2012-05-01 | 2016-04-27 | United Technologies Corp | Metal powder casting |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN115070043A (en) * | 2021-03-10 | 2022-09-20 | 中国航发商用航空发动机有限责任公司 | GH4065A and GH4169 same-material and different-material multistage rotor assembly and preparation method thereof |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB530639A (en) * | 1938-06-16 | 1940-12-17 | Meutsch Voigtlaender & Co | Process for the production of articles provided with coatings or insets of hard metal |
US3510935A (en) * | 1966-01-03 | 1970-05-12 | Duerrwaechter E Dr Doduco | Process of manufacturing rod-shaped multilayer semifinished material |
US3862286A (en) * | 1972-10-10 | 1975-01-21 | Aluminum Co Of America | Method of fabricating compacted powdered metal extrusion billets |
-
1981
- 1981-08-07 NO NO812680A patent/NO150668C/en unknown
-
1982
- 1982-08-02 EP EP82304080A patent/EP0072175B1/en not_active Expired
- 1982-08-02 DE DE8282304080T patent/DE3268398D1/en not_active Expired
- 1982-08-05 JP JP57136796A patent/JPS5842703A/en active Pending
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB530639A (en) * | 1938-06-16 | 1940-12-17 | Meutsch Voigtlaender & Co | Process for the production of articles provided with coatings or insets of hard metal |
US3510935A (en) * | 1966-01-03 | 1970-05-12 | Duerrwaechter E Dr Doduco | Process of manufacturing rod-shaped multilayer semifinished material |
US3862286A (en) * | 1972-10-10 | 1975-01-21 | Aluminum Co Of America | Method of fabricating compacted powdered metal extrusion billets |
Cited By (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0202735A3 (en) * | 1985-04-23 | 1987-09-16 | Cameron Iron Works, Inc. | Process for making a composite powder metallurgical billet |
EP0202735A2 (en) * | 1985-04-23 | 1986-11-26 | Cameron Iron Works, Inc. | Process for making a composite powder metallurgical billet |
EP0278682A2 (en) * | 1987-02-06 | 1988-08-17 | The Timken Company | Powder metal composite and method of its manufacture |
EP0278682A3 (en) * | 1987-02-06 | 1990-01-24 | The Timken Company | Powder metal composite and method of its manufacture |
WO1990014185A1 (en) * | 1989-05-25 | 1990-11-29 | Gkn Technology Limited | Connecting rod |
GB2233000A (en) * | 1989-05-25 | 1991-01-02 | Gkn Technology Ltd | Connecting rod |
US5815790A (en) * | 1994-01-19 | 1998-09-29 | Soderfors Powder Aktiebolag | Method relating to the manufacturing of a composite metal product |
WO1995019861A1 (en) * | 1994-01-19 | 1995-07-27 | Söderfors Powder Aktiebolag | Method relating to the manufacturing of a composite metal product |
CN1068266C (en) * | 1994-01-19 | 2001-07-11 | 索德弗粉末有限公司 | Method relating to manufacturing of composite metal product |
US5792403A (en) * | 1994-12-23 | 1998-08-11 | Kennametal Inc. | Method of molding green bodies |
US5762843A (en) * | 1994-12-23 | 1998-06-09 | Kennametal Inc. | Method of making composite cermet articles |
US5789686A (en) * | 1994-12-23 | 1998-08-04 | Kennametal Inc. | Composite cermet articles and method of making |
CN1091014C (en) * | 1994-12-23 | 2002-09-18 | 钴碳化钨硬质合金公司 | Composite cermet articles and method of making |
US5686119A (en) * | 1994-12-23 | 1997-11-11 | Kennametal Inc. | Composite cermet articles and method of making |
WO1996020058A1 (en) * | 1994-12-23 | 1996-07-04 | Kennametal Inc. | Composite cermet articles and method of making |
US5623723A (en) * | 1995-08-11 | 1997-04-22 | Greenfield; Mark S. | Hard composite and method of making the same |
US6183687B1 (en) | 1995-08-11 | 2001-02-06 | Kennametal Inc. | Hard composite and method of making the same |
EP0983813A2 (en) * | 1998-09-03 | 2000-03-08 | Ykk Corporation | Process for producing shaped article |
EP0983813A3 (en) * | 1998-09-03 | 2002-12-04 | Ykk Corporation | Process for producing shaped article |
US6908688B1 (en) | 2000-08-04 | 2005-06-21 | Kennametal Inc. | Graded composite hardmetals |
EP1724438A2 (en) * | 2005-05-17 | 2006-11-22 | The General Electric Company | Method for making a compositionally graded gas turbine disk |
EP1724438A3 (en) * | 2005-05-17 | 2012-09-19 | General Electric Company | Method for making a compositionally graded gas turbine disk |
EP2327493A1 (en) * | 2009-11-26 | 2011-06-01 | Rolls-Royce plc | Method of manufacturing a multiple composition component |
EP2844410A4 (en) * | 2012-05-01 | 2016-04-27 | United Technologies Corp | Metal powder casting |
US9475118B2 (en) | 2012-05-01 | 2016-10-25 | United Technologies Corporation | Metal powder casting |
WO2015128597A1 (en) * | 2014-02-28 | 2015-09-03 | Castings Technology International Limited | Forming a composite component |
CN106163698A (en) * | 2014-02-28 | 2016-11-23 | 卡斯丁技术国际有限公司 | Form composite component |
WO2015169746A1 (en) * | 2014-05-05 | 2015-11-12 | Gkn Sinter Metals Engineering Gmbh | Hydrogen-storage-element production device together with method therefor and hydrogen storage element |
Also Published As
Publication number | Publication date |
---|---|
DE3268398D1 (en) | 1986-02-20 |
NO150668B (en) | 1984-08-20 |
NO150668C (en) | 1984-11-28 |
EP0072175B1 (en) | 1986-01-08 |
NO812680L (en) | 1983-02-08 |
JPS5842703A (en) | 1983-03-12 |
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