US3888663A - Metal powder sintering process - Google Patents
Metal powder sintering process Download PDFInfo
- Publication number
- US3888663A US3888663A US301433A US30143372A US3888663A US 3888663 A US3888663 A US 3888663A US 301433 A US301433 A US 301433A US 30143372 A US30143372 A US 30143372A US 3888663 A US3888663 A US 3888663A
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- United States
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- powder
- mass
- sintering
- microns
- sintered
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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- 239000000843 powder Substances 0.000 title claims abstract description 74
- 238000000034 method Methods 0.000 title claims abstract description 49
- 238000005245 sintering Methods 0.000 title claims abstract description 47
- 230000008569 process Effects 0.000 title claims abstract description 41
- 229910052751 metal Inorganic materials 0.000 title description 12
- 239000002184 metal Substances 0.000 title description 12
- 229910000601 superalloy Inorganic materials 0.000 claims abstract description 33
- 239000002245 particle Substances 0.000 claims abstract description 28
- 230000000704 physical effect Effects 0.000 claims abstract description 20
- 239000011230 binding agent Substances 0.000 claims abstract description 14
- 238000003825 pressing Methods 0.000 claims abstract description 5
- 150000001247 metal acetylides Chemical class 0.000 claims description 33
- 239000000203 mixture Substances 0.000 claims description 18
- 230000009466 transformation Effects 0.000 claims description 17
- 238000006243 chemical reaction Methods 0.000 claims description 16
- 230000000694 effects Effects 0.000 claims description 16
- 238000010438 heat treatment Methods 0.000 claims description 15
- 238000009792 diffusion process Methods 0.000 claims description 10
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 6
- 239000001301 oxygen Substances 0.000 claims description 6
- 229910052760 oxygen Inorganic materials 0.000 claims description 6
- 239000000126 substance Substances 0.000 claims description 6
- 230000015572 biosynthetic process Effects 0.000 claims description 4
- 230000009467 reduction Effects 0.000 claims description 3
- 238000005728 strengthening Methods 0.000 abstract description 6
- 238000005242 forging Methods 0.000 abstract description 4
- 238000010310 metallurgical process Methods 0.000 abstract description 2
- 229910045601 alloy Inorganic materials 0.000 description 20
- 239000000956 alloy Substances 0.000 description 20
- 210000003739 neck Anatomy 0.000 description 12
- 239000011159 matrix material Substances 0.000 description 10
- 230000008901 benefit Effects 0.000 description 8
- 238000002844 melting Methods 0.000 description 6
- 230000008018 melting Effects 0.000 description 6
- 239000000470 constituent Substances 0.000 description 5
- 239000007789 gas Substances 0.000 description 5
- 230000006872 improvement Effects 0.000 description 5
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 4
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 4
- 238000005275 alloying Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 238000000889 atomisation Methods 0.000 description 3
- 238000005266 casting Methods 0.000 description 3
- 239000011651 chromium Substances 0.000 description 3
- 238000005056 compaction Methods 0.000 description 3
- 230000000052 comparative effect Effects 0.000 description 3
- 238000000280 densification Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 239000012188 paraffin wax Substances 0.000 description 3
- 239000011148 porous material Substances 0.000 description 3
- 239000004484 Briquette Substances 0.000 description 2
- 229910052786 argon Inorganic materials 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000007731 hot pressing Methods 0.000 description 2
- 239000011261 inert gas Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 230000005012 migration Effects 0.000 description 2
- 238000013508 migration Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 229910052759 nickel Inorganic materials 0.000 description 2
- 230000003647 oxidation Effects 0.000 description 2
- 238000007254 oxidation reaction Methods 0.000 description 2
- 238000012856 packing Methods 0.000 description 2
- 238000007493 shaping process Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 239000010936 titanium Substances 0.000 description 2
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 description 1
- 239000004925 Acrylic resin Substances 0.000 description 1
- 229920000178 Acrylic resin Polymers 0.000 description 1
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 1
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 1
- 229910003294 NiMo Inorganic materials 0.000 description 1
- 239000004372 Polyvinyl alcohol Substances 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 241001420369 Thosea Species 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 238000005219 brazing Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 229910052804 chromium Inorganic materials 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 238000007872 degassing Methods 0.000 description 1
- 230000002939 deleterious effect Effects 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 238000011049 filling Methods 0.000 description 1
- 238000013467 fragmentation Methods 0.000 description 1
- 238000006062 fragmentation reaction Methods 0.000 description 1
- 238000009689 gas atomisation Methods 0.000 description 1
- 239000001307 helium Substances 0.000 description 1
- 229910052734 helium Inorganic materials 0.000 description 1
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 150000002500 ions Chemical class 0.000 description 1
- QSHDDOUJBYECFT-UHFFFAOYSA-N mercury Chemical compound [Hg] QSHDDOUJBYECFT-UHFFFAOYSA-N 0.000 description 1
- 229910052753 mercury Inorganic materials 0.000 description 1
- 229910001092 metal group alloy Inorganic materials 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 229910052750 molybdenum Inorganic materials 0.000 description 1
- 239000011733 molybdenum Substances 0.000 description 1
- 229910001120 nichrome Inorganic materials 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 229920001568 phenolic resin Polymers 0.000 description 1
- 229920002451 polyvinyl alcohol Polymers 0.000 description 1
- 229920000915 polyvinyl chloride Polymers 0.000 description 1
- 239000004800 polyvinyl chloride Substances 0.000 description 1
- 230000002028 premature Effects 0.000 description 1
- 238000010926 purge Methods 0.000 description 1
- 230000003252 repetitive effect Effects 0.000 description 1
- 238000005204 segregation Methods 0.000 description 1
- 238000004513 sizing Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000002904 solvent Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 230000008961 swelling Effects 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
Images
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/04—Making non-ferrous alloys by powder metallurgy
- C22C1/0433—Nickel- or cobalt-based alloys
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
Definitions
- Billets and components produced employing the aforementioned powder metallurgical techniques are further characterized as possessing a wrought grain structure and having excellent high temperature physical properties.
- Unfortunately, such densitied billets of superalloy powders, as well as shaped components thereof, are comparatively expensive due to the large number of steps involved, as well as the care and trained personnel required, in addition to relatively expensive equipment employed.
- the present process further enables the fabrication of sintered parts which closely approxmate the final shape and dimensions of the finished component, thereby eliminating or minimizing final finishing operations. Further improvements in the physical properties of the final components can be achieved by effecting a further compaction of the sintered mass as well as a heat treatment thereof in order to achieve optimum properties consistent with the intended end use of the component.
- a process which comprises the steps of providing a mass of a superalloy powder of the general type characterized as being of a nickel base and as normally having carbide and gamma-prime strengthening.
- the mass of powder is formed into a three-dimensional shape of a desired configuration, whereafter the shaped mass is heated in an atmosphere approaching a substantially perfect vacuum to a first or transformation temperature at which the chemical equilibrium is conducive toward, and preferably, which optimizes a conversion of primary metal carbides to secondary or complex carbides.
- the mass is maintained at the first temperature for a period of time sufficient to effect an appreciable conversion of the primary carbides to the secondary or complex carbides accompanied by a migration of carbides from the surface to the interior of the powder particles and an initiation of the diffusion bonding of the powder particles to each other at their points of contact.
- the mass while still in an evacuated atmosphere, is heated to a second or sintering temperature which is above the carbide transformation temperature and may range up to a level at which incipient melting of the superalloy powder particles occurs.
- the mass is maintained at the second temperature for a period of time sufficient to form an integral porous sintered preform in which the powder particles are securely bonded to each other by necks which bridge or interconnect adjoining powder particles at their initial points of contact.
- the resultant sintered mass is further densified to effect a reduction in the porosity thereof and is subjected to a heat treatment, whereby a further enhancement and optimization in the physical properties thereof are achieved.
- the powder particles are distributed over the range of l75 microns to 10 microns, providing for a greater degree of packing of the loose powder, achieving thereby a sintered preform of lower porosity. It is a characteristic of superalloy powders that the particles are generally spherical in configuration when such powders are formed by microcasting techniques, including gas atomization, airless spraying and centrifugal techniques for effecting a fragmentation of a molten mass of the alloy. Typical of a gas microcasting technique is that described in US. Pat. No. 3,253,783, which is assigned to the same assignee as the present invention and wherein a nozzle arrangement is disclosed for effecting an atomization of a molten mass of the metal into particles of controlled size.
- the superalloy compositions generally contain a large variety of alloying constituents, many of which have an affinity for oxygen at temperatures corresponding to those at which the alloys are heated to effect an atomization thereof. While oxygen contents in the metal powder of up to about 300 parts per million (ppm) do not have any appreciable adverse effect on the high temperature mechanical properties of the resultant sintered components, it is usually preferred that such powders have oxygen contents of less than about 100 ppm.
- metal powders containing oxygen contents of less than about 100 ppm can readily be achieved by employing an inert gas, such as argon or helium, for example, to effect an atomization of the molten mass, as well as in providing an inert atmosphere in the chamber in which the molten particles are cooled and collected.
- an inert gas such as argon or helium
- a powder of the prescribed composition and average particle size range is shaped into a desired three-dimensional configuration, whereafter it is subjected to a controlled two-stage sintering operation under a vacuum atmosphere.
- the sintering of the powder to form a preform can be achieved by placing the powder in a mold cavity of the desired configuration or, alternatively, mixing the powder with a volatile binder and cold-pressing the powder in a die cavity of the desired configuration to form a three-dimensional briquette possessing sufficient green strength to retain its shape during the sintering step.
- the mold When employing a mold, it is usually preferred to subject the mold to sonic or supersonic vibratory frequencies to effect optimum packing thereof to a density usually ranging from about 60% up to about 70% of a theoretical 100% density.
- a density usually ranging from about 60% up to about 70% of a theoretical 100% density.
- the cold compaction of the metallic powder-binder mixture produces a green briquette of a density similarly ranging from about 60% to about 70% of 100% theoretical density.
- any one of a variety of well known organic binder materials can be employed in amounts usually ranging from about 2% up to about 5% of the powder-binder mixture provided that the binder is sufficiently volatile so as to substantially completely decompose without leaving any detrimental residue during the sintering operation.
- Binders suitable for this purpose include acrylic resins, paraffin wax, phenol formaldehyde resin, polyvinylchloride, polyvinyl alcohol, and the like, of which paraffin wax constitutes a preferred material when employed in amounts of from about 1% to about 3% based on the total binder-powder blend.
- the green cold-pressed briquettes are prepared in accordance with known techniques wherein a uniform mixture of the powder and particulated organic binder or a solution of the binder in a volatile solvent is placed in a die cavity of the desired configuration and the resultant powder mixture is cold compacted at unit pressures of about 30,000 psi up to about 100,000 psi or even higher, depending upon equipment limitations.
- the refractory mold filled with the superalloy powder or the cold-pressed green briquettes in accordance with the process sequence illustrated in the drawing is thereafter placed in a furnace chamber capable of being evacuated to produce a substantially complete vacuum under which the powder is heated to a first transformation temperature and thereafter to a second sintering temperature in a manner and for the purposes as hereinafter described.
- the refractory mold filled with metal powder or green briquettes is progressively heated to a first temperature which may more aptly be described as a carbide transformation temperature and at which the chemical equilibrium favors a conversion of primary carbides to complex carbides in accordance with the following equation:
- M comprises a metal such as titanium, chromium, molybdenum, etc., depending upon the specific alloy employed forming a carbide;
- MC comprises a primary carbide such as (Ti 0.6; Cr 0.2; Mo 0.2)C; and
- M C comprises a secondary or complex carbide.
- the carbide transformation temperature for superalloys of the type to which the present invention is applicable is within a relatively narrow band located somewhere between about l600 up to about 2000F.
- the specific transformation temperature to which the powder is heated during the first stage sintering operation will vary depending upon the chemistry of the alloy and is selected so as to optimize the conversion of primary carbides to complex carbides plus gamma-prime such that at the conclusion of the first stage sintering step, the secondary or complex carbides are in abundance, while the primary carbides are present in substantially small quantities.
- the duration of the first stage sintering step will vary depending upon the specific alloy composition employed and is controlled so as to effect an appreciable transformation of primary to secondary carbides and a migration of the carbides from the surfaces of the powder particles to their interiors.
- an initial diffusion bonding or sintering of the particles at their points of Contact also occurs during the first sintering stage forming a so-called neck," which progressively grows, particularly during the second sintering stage, forming an integrallybonded three-dimensional matrix of increased density.
- the presintered matrix is heated to a second or sintering tem perature which is conventionally selected as one slightly below or at about the incipient melting temperature of the alloy to promote a more rapid atomic diffusion and neck growth in order to complete the sintering step.
- a second or sintering tem perature which is conventionally selected as one slightly below or at about the incipient melting temperature of the alloy to promote a more rapid atomic diffusion and neck growth in order to complete the sintering step.
- temperatures at or slightly above the transformation temperature employed in the first sintering stage can be used in the second sintering stage, the rate of diffusion and neck growth is generally too slow from a commercial standpoint, and it is for this reason that temperatures at or about the incipient melting point of the alloy are used.
- the incipient melting point for most superalloys generally ranges from about 2l00F up to about 2350F, at which optimum atomic mobility is achieved to promote the diffusion reaction and neck growth.
- the second stage sintering step is carried out for a period of time to achieve maximum densification and pore shrinkage of the powdered mass.
- time periods of from about 1 hour up to about hours when heated to a temperature slightly below or at the incipient melting point of the alloy are satisfactory for achieving optimum mechanical properties of the resultant sintered matrix.
- the resultant sintered mass depending upon the specific powder particles employed and the duration of the sec- 0nd stage sintering operation, will have porosities usually ranging from about 20% to about 10% by volume.
- the conversion of primary carbides to complex carbides and gammaprime results in a bonding neck formation during the first sintering stage which is substantially clean and devoid of brittle carbide phases and the rapid neck growth during the final sintering stage prevents any appreciable reconversion of complex carbides to primary carbides.
- the resultant sintered matrix is, accordingly, possessed of unexpectedly high mechanical properties. It will be understood, however, that the foregoing theory does not comprise any part of the present invention and is merely offered as a possible explanation of the unexpected results obtained.
- the sintered matrix is removed from the furnace and conventionally is of a density ranging from about to about of theoretical density.
- the sintered porous preform can be further compacted or densified such as by cold or hot coining and cold or hot pressing to provide for a more accurate sizing and shaping of the preform and to effect a further densification thereof from about 90% up to about theoretical density.
- the sintered preform can be subjected to cold or hot forging in which a comparatively high deformation thereof is effected, producing forged components or parts of a desired shape and of densities approaching 100% theoretical density.
- the sintered preform with or without further densification is also preferably subjected to a heat treatment to optimize and further enhance the physical properties thereof consistent with the intended end use of the component.
- Typical heat treatments include a heating of the sintered preform to a temperature above the gamma-prime solvus to effect dissolving of the gammaprime whereafter the preform is quenched.
- the resultant structure having a very fine-sized and uniform gamma-prime can thereafter be aged to grow the gamma-prirne phase to a size and morphology consistent with the properties desired at the ultimate operating temperatures.
- any conventional heat treatment cycle can be employed to achieve a desired modification of the properties of the preform consistent with its intended end use.
- EXAMPLE 1 A quantity of a superalloy powder having a composition corresponding to the alloy lN-lOO as set forth in Table l and of an average particle size of 75 microns was mixed with 2% by weight of paraffin wax as a binder and placed in a steel die cavity shaped as a dogbone tensile specimen and compacted under a pressure of 60,000 psi. The green compact was thereafter removed from the die and placed in a vacuum furnace at 1800F for a period of 15 hours at a vacuum of about 1 micron. At the completion of the first stage sintering operation, the furnace was increased in temperature to 2250F and the pre-sintered matrix was sintered for an additional 24 hour period, after which it was removed.
- EXAMPLE 2 A quantity of superalloy powder identical to that employed in Example 1 is placed in a refractory mold cavity and sintered in a vacuum of one micron at 1800 for a period of 15 hours followed by a second phase sintering step at 2250F for 24 hours.
- the resultant sintered preform is removed from the mold cavity and has a density of about 80% of 100% theoretical density.
- the preform after a correction of cross sectional area to compensate for density variations, has physical properties comparable to those obtained on Sample A of Example 1.
- a process for making sintered articles which comprises the steps of providing a mass of nickel-base superalloy powder having an oxygen content of less than about 300 ppm and of the type characterized as normally having carbide and gamma-prime strengthening, forming said mass of powder into a three-dimensional shape of the desired configuration, heating the shaped said mass of powder in the substantial absence of a surrounding atmosphere to a first sintering and transformation temperature ranging from about 1600 to about 2000F at which the chemical equilibrium is conducive for effecting a conversion of primary carbides to complex carbides, maintaining said mass at said first sintering temperature for a period of time to effect an appreciable conversion of said primary carbides to said complex carbides under the prevailing equilibrium conditions and to initiate a diffusion bonding and neck formation between the powder particles at their points of contact, heating said mass of powder to a second sintering temperature above said first temperature up to the incipient melting point of said powder particles for a period of time sufficient to effect growth of said neck and the formation of an integral porous sintered preform, and
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Powder Metallurgy (AREA)
Abstract
Description
Claims (11)
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US301433A US3888663A (en) | 1972-10-27 | 1972-10-27 | Metal powder sintering process |
DE2351846A DE2351846C2 (en) | 1972-10-27 | 1973-10-16 | Process for the production of sintered bodies from superalloy powder on a nickel base |
FR7338113A FR2204474B1 (en) | 1972-10-27 | 1973-10-25 | |
JP48120344A JPS5226483B2 (en) | 1972-10-27 | 1973-10-25 | |
GB5004473A GB1414233A (en) | 1972-10-27 | 1973-10-26 | Sintering metal powders |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US301433A US3888663A (en) | 1972-10-27 | 1972-10-27 | Metal powder sintering process |
Publications (1)
Publication Number | Publication Date |
---|---|
US3888663A true US3888663A (en) | 1975-06-10 |
Family
ID=23163336
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US301433A Expired - Lifetime US3888663A (en) | 1972-10-27 | 1972-10-27 | Metal powder sintering process |
Country Status (5)
Country | Link |
---|---|
US (1) | US3888663A (en) |
JP (1) | JPS5226483B2 (en) |
DE (1) | DE2351846C2 (en) |
FR (1) | FR2204474B1 (en) |
GB (1) | GB1414233A (en) |
Cited By (29)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4063939A (en) * | 1975-06-27 | 1977-12-20 | Special Metals Corporation | Composite turbine wheel and process for making same |
US4483820A (en) * | 1980-02-06 | 1984-11-20 | Sintermetallwerk Krebsoge Gmbh | Method of making sintered powder metallurgical bodies |
US4713215A (en) * | 1986-05-16 | 1987-12-15 | L'air Liquide | Process for sintering powdered material in a continuous furnace |
US4859164A (en) * | 1986-12-06 | 1989-08-22 | Nippon Piston Ring Co., Ltd. | Ferrous sintered alloy vane and rotary compressor |
US5009704A (en) * | 1989-06-28 | 1991-04-23 | Allied-Signal Inc. | Processing nickel-base superalloy powders for improved thermomechanical working |
US5075053A (en) * | 1988-08-04 | 1991-12-24 | Gte Valenite Corporation | Method of making cutting insert |
US5174952A (en) * | 1989-09-13 | 1992-12-29 | Asea Brown Boveri Ltd. | Process for the powder-metallurgical production of a workpiece |
EP0676483A1 (en) * | 1994-04-06 | 1995-10-11 | Special Metals Corporation | High strain rate deformation of nickel-base superalloy compact |
US5472662A (en) * | 1991-11-27 | 1995-12-05 | Asmo Co., Ltd. | Method for manufacturing a stator for an ultrasonic motor |
US20040151611A1 (en) * | 2003-01-30 | 2004-08-05 | Kline Kerry J. | Method for producing powder metal tooling, mold cavity member |
US20040234407A1 (en) * | 2003-03-27 | 2004-11-25 | Hoganas Ab | Powder metal composition and method for producing components thereof |
US20050064221A1 (en) * | 2001-05-14 | 2005-03-24 | Lu Jyh-Woei J. | Sintering process and tools for use in metal injection molding of large parts |
US20050238526A1 (en) * | 2003-11-20 | 2005-10-27 | Gerald Schall | Heat resistant super alloy and its use |
US20060191396A1 (en) * | 2002-07-29 | 2006-08-31 | L.S. Starrett Company | Cutting tool with grooved cutting edge |
US20060198751A1 (en) * | 2003-03-27 | 2006-09-07 | Hoganas Ab, | Co-based water-atomised powder composition for die compaction |
US20060208105A1 (en) * | 2005-03-17 | 2006-09-21 | Pratt & Whitney Canada Corp. | Modular fuel nozzle and method of making |
US20080115358A1 (en) * | 2006-11-21 | 2008-05-22 | Honeywell International, Inc. | Superalloy rotor component and method of fabrication |
US20080277454A1 (en) * | 2002-07-29 | 2008-11-13 | William Engineering Llc | Composite metal article and method of making |
US20090000303A1 (en) * | 2007-06-29 | 2009-01-01 | Patel Bhawan B | Combustor heat shield with integrated louver and method of manufacturing the same |
US20090020587A1 (en) * | 2007-02-08 | 2009-01-22 | Toyota Jidosha Kabushiki Kaisha | Bonding Method |
US20090026027A1 (en) * | 2007-07-23 | 2009-01-29 | Gerald Martino | Brake rotors for vehicles |
US20090026026A1 (en) * | 2007-07-23 | 2009-01-29 | Gerald Martino | Vehicular brake rotors |
US7543383B2 (en) | 2007-07-24 | 2009-06-09 | Pratt & Whitney Canada Corp. | Method for manufacturing of fuel nozzle floating collar |
US20100178194A1 (en) * | 2009-01-12 | 2010-07-15 | Accellent, Inc. | Powder extrusion of shaped sections |
US20110123386A1 (en) * | 2009-11-26 | 2011-05-26 | Rolls-Royce Plc | Method of manufacturing a multiple composition component |
US20110142709A1 (en) * | 2009-12-16 | 2011-06-16 | Rolls-Royce Plc | Method of manufacturing a component |
WO2011136810A1 (en) * | 2010-04-30 | 2011-11-03 | Accellent, Inc. | Pressure forming of metal and ceramic powders |
US9101984B2 (en) | 2011-11-16 | 2015-08-11 | Summit Materials, Llc | High hardness, corrosion resistant PM Nitinol implements and components |
US20170074116A1 (en) * | 2014-07-17 | 2017-03-16 | United Technologies Corporation | Method of creating heat transfer features in high temperature alloys |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS57123902A (en) * | 1981-01-21 | 1982-08-02 | Uitetsuku Keiman Patentsu Ltd | Manufacture of bakes granular structure and crush compress formation |
JP3421758B2 (en) * | 1993-09-27 | 2003-06-30 | 株式会社日立製作所 | Oxide dispersion strengthened alloy and high temperature equipment composed of the alloy |
JP2004536967A (en) * | 2001-05-14 | 2004-12-09 | ハネウェル・インターナショナル・インコーポレーテッド | Sintering methods and tools used for metal injection molding of large parts |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2823988A (en) * | 1955-09-15 | 1958-02-18 | Sintercast Corp America | Composite matter |
US3655458A (en) * | 1970-07-10 | 1972-04-11 | Federal Mogul Corp | Process for making nickel-based superalloys |
-
1972
- 1972-10-27 US US301433A patent/US3888663A/en not_active Expired - Lifetime
-
1973
- 1973-10-16 DE DE2351846A patent/DE2351846C2/en not_active Expired
- 1973-10-25 JP JP48120344A patent/JPS5226483B2/ja not_active Expired
- 1973-10-25 FR FR7338113A patent/FR2204474B1/fr not_active Expired
- 1973-10-26 GB GB5004473A patent/GB1414233A/en not_active Expired
Patent Citations (2)
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Cited By (48)
Publication number | Priority date | Publication date | Assignee | Title |
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US4063939A (en) * | 1975-06-27 | 1977-12-20 | Special Metals Corporation | Composite turbine wheel and process for making same |
US4483820A (en) * | 1980-02-06 | 1984-11-20 | Sintermetallwerk Krebsoge Gmbh | Method of making sintered powder metallurgical bodies |
US4713215A (en) * | 1986-05-16 | 1987-12-15 | L'air Liquide | Process for sintering powdered material in a continuous furnace |
US4859164A (en) * | 1986-12-06 | 1989-08-22 | Nippon Piston Ring Co., Ltd. | Ferrous sintered alloy vane and rotary compressor |
US4976916A (en) * | 1986-12-06 | 1990-12-11 | Nippon Piston Ring Co., Ltd. | Method for producing ferrous sintered alloy product |
US5075053A (en) * | 1988-08-04 | 1991-12-24 | Gte Valenite Corporation | Method of making cutting insert |
US5009704A (en) * | 1989-06-28 | 1991-04-23 | Allied-Signal Inc. | Processing nickel-base superalloy powders for improved thermomechanical working |
US5174952A (en) * | 1989-09-13 | 1992-12-29 | Asea Brown Boveri Ltd. | Process for the powder-metallurgical production of a workpiece |
US5472662A (en) * | 1991-11-27 | 1995-12-05 | Asmo Co., Ltd. | Method for manufacturing a stator for an ultrasonic motor |
EP0676483A1 (en) * | 1994-04-06 | 1995-10-11 | Special Metals Corporation | High strain rate deformation of nickel-base superalloy compact |
US20050064221A1 (en) * | 2001-05-14 | 2005-03-24 | Lu Jyh-Woei J. | Sintering process and tools for use in metal injection molding of large parts |
US7635405B2 (en) | 2001-05-14 | 2009-12-22 | Honeywell International Inc. | Sintering process and tools for use in metal injection molding of large parts |
US20060191396A1 (en) * | 2002-07-29 | 2006-08-31 | L.S. Starrett Company | Cutting tool with grooved cutting edge |
US7451678B2 (en) * | 2002-07-29 | 2008-11-18 | The L.S. Starrett Company | Cutting tool with grooved cutting edge |
US20080277454A1 (en) * | 2002-07-29 | 2008-11-13 | William Engineering Llc | Composite metal article and method of making |
US20080280157A1 (en) * | 2002-07-29 | 2008-11-13 | William Engineering Llc | Composite metal article and method of making |
US20040151611A1 (en) * | 2003-01-30 | 2004-08-05 | Kline Kerry J. | Method for producing powder metal tooling, mold cavity member |
US20040234407A1 (en) * | 2003-03-27 | 2004-11-25 | Hoganas Ab | Powder metal composition and method for producing components thereof |
US20060198751A1 (en) * | 2003-03-27 | 2006-09-07 | Hoganas Ab, | Co-based water-atomised powder composition for die compaction |
US7300488B2 (en) | 2003-03-27 | 2007-11-27 | Höganäs Ab | Powder metal composition and method for producing components thereof |
US9051844B2 (en) | 2003-11-20 | 2015-06-09 | Borgwarner Inc. | Heat resistant super alloy and its use |
US20050238526A1 (en) * | 2003-11-20 | 2005-10-27 | Gerald Schall | Heat resistant super alloy and its use |
US20080271822A1 (en) * | 2003-11-20 | 2008-11-06 | Borg Warner Inc. | Heat resistant super alloy and its use |
US7237730B2 (en) | 2005-03-17 | 2007-07-03 | Pratt & Whitney Canada Corp. | Modular fuel nozzle and method of making |
US20060208105A1 (en) * | 2005-03-17 | 2006-09-21 | Pratt & Whitney Canada Corp. | Modular fuel nozzle and method of making |
US20080115358A1 (en) * | 2006-11-21 | 2008-05-22 | Honeywell International, Inc. | Superalloy rotor component and method of fabrication |
US9114488B2 (en) | 2006-11-21 | 2015-08-25 | Honeywell International Inc. | Superalloy rotor component and method of fabrication |
US20090020587A1 (en) * | 2007-02-08 | 2009-01-22 | Toyota Jidosha Kabushiki Kaisha | Bonding Method |
US7770781B2 (en) * | 2007-02-08 | 2010-08-10 | Toyota Jidosha Kabushiki Kaisha | Bonding method |
US20090000303A1 (en) * | 2007-06-29 | 2009-01-01 | Patel Bhawan B | Combustor heat shield with integrated louver and method of manufacturing the same |
US8316541B2 (en) | 2007-06-29 | 2012-11-27 | Pratt & Whitney Canada Corp. | Combustor heat shield with integrated louver and method of manufacturing the same |
US8904800B2 (en) | 2007-06-29 | 2014-12-09 | Pratt & Whitney Canada Corp. | Combustor heat shield with integrated louver and method of manufacturing the same |
US7806243B2 (en) * | 2007-07-23 | 2010-10-05 | Gerald Martino | Vehicular brake rotors |
US20100314208A1 (en) * | 2007-07-23 | 2010-12-16 | Gerald Martino | Vehicular brake rotors |
US20090026027A1 (en) * | 2007-07-23 | 2009-01-29 | Gerald Martino | Brake rotors for vehicles |
US20090026026A1 (en) * | 2007-07-23 | 2009-01-29 | Gerald Martino | Vehicular brake rotors |
US8028812B2 (en) * | 2007-07-23 | 2011-10-04 | Gerald Martino | Brake rotors for vehicles |
US7543383B2 (en) | 2007-07-24 | 2009-06-09 | Pratt & Whitney Canada Corp. | Method for manufacturing of fuel nozzle floating collar |
US20100178194A1 (en) * | 2009-01-12 | 2010-07-15 | Accellent, Inc. | Powder extrusion of shaped sections |
US20110123386A1 (en) * | 2009-11-26 | 2011-05-26 | Rolls-Royce Plc | Method of manufacturing a multiple composition component |
US8703045B2 (en) | 2009-11-26 | 2014-04-22 | Rolls-Royce Plc | Method of manufacturing a multiple composition component |
EP2327493A1 (en) * | 2009-11-26 | 2011-06-01 | Rolls-Royce plc | Method of manufacturing a multiple composition component |
US8758676B2 (en) * | 2009-12-16 | 2014-06-24 | Rolls-Royce Plc | Method of manufacturing a component |
US20110142709A1 (en) * | 2009-12-16 | 2011-06-16 | Rolls-Royce Plc | Method of manufacturing a component |
WO2011136810A1 (en) * | 2010-04-30 | 2011-11-03 | Accellent, Inc. | Pressure forming of metal and ceramic powders |
US9789543B2 (en) | 2010-04-30 | 2017-10-17 | Accellent Inc. | Pressure forming of metal and ceramic powders |
US9101984B2 (en) | 2011-11-16 | 2015-08-11 | Summit Materials, Llc | High hardness, corrosion resistant PM Nitinol implements and components |
US20170074116A1 (en) * | 2014-07-17 | 2017-03-16 | United Technologies Corporation | Method of creating heat transfer features in high temperature alloys |
Also Published As
Publication number | Publication date |
---|---|
JPS5226483B2 (en) | 1977-07-14 |
JPS49133210A (en) | 1974-12-20 |
FR2204474B1 (en) | 1980-04-25 |
FR2204474A1 (en) | 1974-05-24 |
DE2351846C2 (en) | 1982-12-30 |
GB1414233A (en) | 1975-11-19 |
DE2351846A1 (en) | 1974-05-02 |
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