US3888663A - Metal powder sintering process - Google Patents

Metal powder sintering process Download PDF

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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
Prior art keywords
powder
mass
sintering
microns
sintered
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Expired - Lifetime
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US301433A
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English (en)
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Steven H Reichman
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.)
ALLEGHENY INTERNATIONAL ACCEPTANCE Corp
TABERT Inc
Federal Mogul LLC
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Federal Mogul LLC
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Priority to US301433A priority Critical patent/US3888663A/en
Priority to DE2351846A priority patent/DE2351846C2/de
Priority to FR7338113A priority patent/FR2204474B1/fr
Priority to JP48120344A priority patent/JPS5226483B2/ja
Priority to GB5004473A priority patent/GB1414233A/en
Application granted granted Critical
Publication of US3888663A publication Critical patent/US3888663A/en
Assigned to AL-INDUSTRIAL PRODUCTS, INC. reassignment AL-INDUSTRIAL PRODUCTS, INC. SECURITY INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SPECIAL METALS CORPORATION A DE CORP
Assigned to CITICORP INDUSTRIAL CREDIT, INC., BOND COURT BLDG., STE. 615, 1300 E. 9TH ST., CLEVELAND, OH. 44114 reassignment CITICORP INDUSTRIAL CREDIT, INC., BOND COURT BLDG., STE. 615, 1300 E. 9TH ST., CLEVELAND, OH. 44114 SECURITY INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SPECIAL METALS CORPORATION
Assigned to ALLEGHENY INTERNATIONAL ACCEPTANCE CORPORATION reassignment ALLEGHENY INTERNATIONAL ACCEPTANCE CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: AL- INDUSTRIAL PRODUCTS INC.
Assigned to TABERT INC reassignment TABERT INC CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). EFFECTIVE AUG. 22, 1985 Assignors: CIP INC
Assigned to HELLER FINANCIAL, INC. reassignment HELLER FINANCIAL, INC. SECURITY INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SPECIAL METALS CORPORATION
Assigned to SPECIAL METALS CORPORATION reassignment SPECIAL METALS CORPORATION RELEASED BY SECURED PARTY (SEE DOCUMENT FOR DETAILS). Assignors: CITICORP INDUSTRIAL CREDIT, INC.
Assigned to SPECIAL METALS CORPORATION reassignment SPECIAL METALS CORPORATION RELEASED BY SECURED PARTY (SEE DOCUMENT FOR DETAILS). Assignors: AL-INDUSTRIAL PRODUCTS, INC., A CORP. OF PA, ALLEGHENY INTERNATIONAL, INC., A CORP. OF PA
Assigned to SPECIAL METALS CORPORATION reassignment SPECIAL METALS CORPORATION RELEASED BY SECURED PARTY (SEE DOCUMENT FOR DETAILS). Assignors: HELLER FINANCIAL, INC.
Anticipated expiration legal-status Critical
Assigned to CREDIT LYONNAIS NEW YORK BRANCH reassignment CREDIT LYONNAIS NEW YORK BRANCH SECURITY INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SPECIAL METALS CORPORATION
Expired - Lifetime legal-status Critical Current

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    • 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)
US301433A 1972-10-27 1972-10-27 Metal powder sintering process Expired - Lifetime US3888663A (en)

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 (de) 1972-10-27 1973-10-16 Verfahren zur Herstellung von Sinterkörpern aus Superlegierungspulver auf Nickel-Basis
FR7338113A FR2204474B1 (cs) 1972-10-27 1973-10-25
JP48120344A JPS5226483B2 (cs) 1972-10-27 1973-10-25
GB5004473A GB1414233A (en) 1972-10-27 1973-10-26 Sintering metal powders

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US301433A US3888663A (en) 1972-10-27 1972-10-27 Metal powder sintering process

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US3888663A true US3888663A (en) 1975-06-10

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JP (1) JPS5226483B2 (cs)
DE (1) DE2351846C2 (cs)
FR (1) FR2204474B1 (cs)
GB (1) GB1414233A (cs)

Cited By (29)

* Cited by examiner, † Cited by third party
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)

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JPS57123902A (en) * 1981-01-21 1982-08-02 Uitetsuku Keiman Patentsu Ltd Manufacture of bakes granular structure and crush compress formation
JP3421758B2 (ja) * 1993-09-27 2003-06-30 株式会社日立製作所 酸化物分散強化型合金及び該合金から構成される高温機器
JP2004536967A (ja) * 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 大きな部品の金属射出成形に使用する焼結方法および工具

Citations (2)

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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

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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

Cited By (48)

* Cited by examiner, † Cited by third party
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
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
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GB1414233A (en) 1975-11-19
DE2351846A1 (de) 1974-05-02
JPS5226483B2 (cs) 1977-07-14
DE2351846C2 (de) 1982-12-30
JPS49133210A (cs) 1974-12-20
FR2204474B1 (cs) 1980-04-25
FR2204474A1 (cs) 1974-05-24

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