EP0446673A1 - Procédé de préparation d'un article fritté avec une couche externe compacte et une surface lisse - Google Patents

Procédé de préparation d'un article fritté avec une couche externe compacte et une surface lisse Download PDF

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Publication number
EP0446673A1
EP0446673A1 EP91102429A EP91102429A EP0446673A1 EP 0446673 A1 EP0446673 A1 EP 0446673A1 EP 91102429 A EP91102429 A EP 91102429A EP 91102429 A EP91102429 A EP 91102429A EP 0446673 A1 EP0446673 A1 EP 0446673A1
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EP
European Patent Office
Prior art keywords
powder
grained
fine
edge zone
mold
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.)
Withdrawn
Application number
EP91102429A
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German (de)
English (en)
Inventor
Reinhard Fried
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.)
ABB Asea Brown Boveri Ltd
ABB AB
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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Filing date
Publication date
Application filed by ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0446673A1 publication Critical patent/EP0446673A1/fr
Withdrawn legal-status Critical Current

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    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/10—Sintering only
    • B22F3/11—Making porous workpieces or articles
    • B22F3/1103—Making porous workpieces or articles with particular physical characteristics
    • B22F3/1109—Inhomogenous pore distribution
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/12—Both compacting and sintering
    • B22F3/1208—Containers or coating used therefor
    • B22F3/1258—Container manufacturing
    • B22F3/1266—Container manufacturing by coating or sealing the surface of the preformed article, e.g. by melting
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • 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
    • B22F2999/00—Aspects linked to processes or compositions used in powder metallurgy

Definitions

  • the invention relates to the further development, perfection and simplification of powder metallurgical manufacturing methods for the production of workpieces with comparatively complicated shapes, where the problems of shrinkage during sintering and the achievement of a high surface quality play an important role.
  • the area of application is above all the area of components of turbine construction, with graduated layers of different material composition and / or different density or porosity being the focus.
  • the invention relates to a method for producing a sintered body with an edge zone with targeted surface properties.
  • the invention has for its object to provide a method for producing a sintered body with an edge zone with targeted surface properties, which is inexpensive.
  • the method should make it possible to produce a comparatively complicated shaped workpiece of any cross-section and unlimited wall thickness based on metal or ceramic powders.
  • the process is intended to provide a reproducible finished product that no longer has to be processed, or at most only slightly. Bubbles and unwanted harmful residues should be avoided during powder processing.
  • the process is intended to ensure the greatest possible freedom of movement and universality.
  • This object is achieved in that in the process mentioned at the beginning on the inner surface of the hollow negative mold which determines the shape of the sintered body, first by applying fine-grained powder, the mean grain size of which is at most 60% of the mean grain size of the powder used to build up the sintered body, in the region a fine-grained surface skin is formed in the edge zone and then the mold for forming a coarse-grained core is filled with said powder and the green compact thus formed, with or without a mold, is subjected to a sintering process.
  • FIG. 1 shows a perspective illustration of a component to be produced by powder metallurgy.
  • it is a component in the form of a rotating body (e.g. shaft with toothed disks).
  • 2 shows an elevation / section through a ceramic mold for the powder-metallurgical production of a component.
  • the shape corresponds to that of component 1 in FIG. 1.
  • 2 represents the porous ceramic shape, the cavity 3 of which, taking into account the shrinkage, is a similar image of the component.
  • Fig. 3 is a cross section through a sintered body after sintering at a temperature of 1000 ° C.
  • 4 represents the fine-grained edge zone, 5 the coarse-grain core.
  • a section of the edge part is shown enlarged.
  • the grains are white, the pores are black.
  • 6 is the grain of the edge zone (94% density) after sintering at 1000 ° C.
  • 7 represents the corresponding pore space of the edge zone (6%).
  • 8 is the grain of the core (90% density) after sintering at 1000 ° C.
  • 9 is the corresponding pore space of the core (10%).
  • Fig. 4 shows a cross section through a sintered body after sintering at 1200 ° C. 4 is again the fine-grained edge zone, 5 the coarse-grained core.
  • the enlarged section of the right half of the figure shows the grain 10 of the edge zone (99% density) after sintering at 1200 ° C and the corresponding pore volume 11 of the edge zone (1%) and the grain 12 of the core (94% density) as well as the corresponding pore volume 13 of the core (6%).
  • FIG. 5 shows a cross section through a sintered body after sintering at 1350 ° C.
  • the fine-grained edge zone 4 and the coarse-grained core 5 are shown enlarged in the right half of the picture.
  • 14 is the grain of the edge zone (100% density) after sintering at 1350 ° C, with no more pore space.
  • 15 represents the grain of the core (95% density), 16 the corresponding pore volume (5%).
  • FIG. 6 schematically shows an elevation of a turbine blade.
  • the blade is drawn in such a way that its foot section 17 (“fir tree foot”) is at the top, its leaf section 18 with the bore 19 for the damper wire is at the bottom.
  • foot section 17 (“fir tree foot”) is at the top
  • leaf section 18 with the bore 19 for the damper wire is at the bottom.
  • the blade can have any other shape.
  • 7 relates to an elevation / section through a ceramic mold for the powder-metallurgical production of a turbine blade.
  • 2 is the porous ceramic shape
  • 3 represents the cavity, which is a true-to-scale replica of the workpiece to be manufactured (taking the shrinkage dimension into account).
  • the space intended for the leaf section is at the bottom, that for the foot section with the inlet funnel in the upper part of Form 2.
  • FIG. 8 shows an elevation / section through a ceramic mold with a filling device for a powder suspension for the blade section of a turbine blade (phase I).
  • 2 is a porous ceramic shape (see Fig. 7).
  • 20 represents a storage container for the powder suspension in a slurry.
  • 21 is the feed pipe for the powder suspension, which is located at the lower end of the storage container 20 after the funnel-shaped lower part 22.
  • 23 represents a low-viscosity suspension of powder for the fine-grained edge zone in the leaf section (casing).
  • 24 is the said powder filling in suspension for the fine-grain edge zone (Anti-erosion layer for the leaf section) after filling in the ceramic mold 2.
  • FIG. 9 shows an elevation / section through a ceramic mold with a suction device for a powder suspension for the blade section of a turbine blade (phase II).
  • the reference numerals 2 and 3 correspond exactly to those of Fig. 8.
  • 23 is the low-viscosity suspension.
  • 25 shows the suction pipe for the powder suspension. In the left half of the picture, the edge section is shown enlarged.
  • 26 is the inner mold wall
  • 27 is the thin layer of the powder suspension (anti-erosion layer) adhering to the inner mold wall 26.
  • 10 shows an elevation / section through a ceramic mold with a filling device for a powder suspension for the entire turbine blade (phase III).
  • 2 is the porous ceramic mold
  • 20 the storage container for a powder suspension in slurry solution
  • 27 the thin layer of the first powder suspension (anti-erosion layer) already adhering to the inner wall of the mold.
  • 28 is a thin suspension of powder (second mixture) for the fine-grained edge zone in the entire blade (shell).
  • 29 is the corresponding powder filling in suspension for the fine-grained edge zone (gas-tight layer for the entire blade) after filling in the ceramic mold 2.
  • FIG. 11 shows an elevation / section through a ceramic mold with a suction device for a powder suspension for the entire turbine blade (phase IV). 2 and 3 correspond to the reference numerals in FIG. 8. 25 is a suction pipe for the powder suspension 28 according to FIG. 10. In the left half of the figure, the edge section is shown enlarged. 26 represents the inner mold wall, 27 the thin layer of the first powder suspension (antierosison layer) adhering to the inner mold wall 26 and 30 the one on the latter Mold inner wall 26 adhering thin layer of the second powder suspension (gas-tight layer).
  • FIG. 12 shows an elevation / section through a ceramic mold with a filling device for powder for the coarse-grained core of a turbine blade (phase V).
  • the reference numerals 2 and 20 correspond exactly to those in FIG. 8.
  • 31 is a powder for the coarse-grained core of the turbine blade, 32 the corresponding dry powder bed.
  • 26 is the inner mold wall, 27 the thin layer of the first powder suspension (anti-erosion layer) adhering to the inner wall 26, 30 the thin layer of the second powder suspension (gastight layer) adhering to the latter and 32 the dry powder filling of the coarse-grained core.
  • 13 relates to a section (schematic metallographic cut) through the structure of a multilayer sintered, hot-isostatically pressed body.
  • 33 represents the densely sintered, hot-isostatically pressed anti-erosion layer with 100% density of the fine-grained edge zone (outer skin).
  • 34 is the densely sintered, hot-isostatically pressed gas-tight layer with 100% density of the fine-grained edge zone.
  • 35 is the sintered, hot-isostatically pressed coarse-grained core of the workpiece.
  • FIG. 14 shows an elevation / section through a ceramic mold for the powder-metallurgical production of a turbine blade using different carrier liquids and dry powder.
  • 2 is the porous ceramic shape, 3 the cavity.
  • the arrow 36 (with wavy lines) indicates the supply of sticky viscous liquid.
  • the arrow 37 (with dots) means the supply of powder adhering to the mold inner wall.
  • 15 shows a schematic elevation / section through part of a ceramic mold for the powder-metallurgical production of a turbine blade using carrier fluids and dry powder alternately (sequence of the production phases).
  • 2 shows the porous ceramic shape (detail).
  • the vertical downward arrows represent the alternating supply of viscous liquids (wavy lines) and powders of different particle sizes (dots).
  • 38 means a moderately viscous liquid adhering to the inner wall of the mold.
  • 39 is a first fine-grain powder adhering to the moderately viscous liquid 38.
  • 40 in turn is a highly viscous liquid that adheres to the fine-grained layer. This is followed at 41 by a medium-fine powder that sticks to the highly viscous liquid.
  • the coarse-grained powder 42 for the core follows. All powder fillings are carried out with dry powders.
  • 16 shows an elevation / section through a highly porous powder-metallurgically manufactured turbine blade for internal cooling.
  • 43 is a porous, high-damping turbine blade for internal cooling consisting of a blade and a base.
  • 44 represents the supply of the gaseous cooling medium through channels created in the powder body.
  • the arrows 45 indicate the removal of the gaseous cooling medium from the surface of the airfoil.
  • 46 is the fine-grained, highly porous outer skin of the peripheral zone
  • 47 is the medium-fine-grained, highly porous intermediate layer of the peripheral zone.
  • 48 shows the coarse-grained, highly porous core. In the left half of the picture, the layer sequence is shown in a larger magnification. It goes without saying that all layers must be open-pored to enable the cooling medium to pass through.
  • 17 shows a longitudinal section through a hetrogenic bending beam produced by powder metallurgy.
  • 49 is a heterogeneous component (bending beam) as an example of the lightweight construction.
  • 50 is the dense fine-grained edge zone that forms the smooth outer skin, 51 represents the highly porous coarse-grained core as a stiffening structure.
  • 52 is the large pore volume in between.
  • the vertical load is indicated by the symbol P, the reaction forces by the symbol P 2nd indicated.
  • ⁇ shows the course of the main stress in the section of the greatest bending moment.
  • 18 relates to an elevation / section through a ceramic mold and a component which is reinforced by powder metallurgy and is reinforced with embedded fibers.
  • 1 represents the component in the form of a rotating body.
  • 2 is the porous ceramic shape.
  • 53 means the fine-grained shell (edge zone), 54 the embedded reinforcing fibers made of ceramic or metal following the contour.
  • 55 represents the coarse-grained core zone that determines the general shape and primarily absorbs compressive forces.
  • test specimens were cut out of the various cross sections of the components and both the mechanical properties and the structure, in particular the course of the density, were examined using metallographic sections. It was found that at 1000 ° C according to a). sintered components in their peripheral zone were not sufficiently dense to be hot-isostatically compressed using a capsule-free process. The edge zone of the at 1200 ° C according to b). and at 1350 ° C according to c). sintered components was sufficiently tight for the subsequent hot isostatic pressing without using a separate additional capsule. The coherent shell formed by the edge zone thus replaced the metal capsule otherwise required in conventional hot isostatic pressing. The workpieces sintered at at least 1200 ° C showed a glossy smooth surface and a roughness of less than 4 ⁇ m, so that additional mechanical processing of the shaft parts of the components could be dispensed with (see FIGS. 4 and 5).
  • FIGS. 3, 4 and 5 The results of the different process variants are shown in FIGS. 3, 4 and 5.
  • the workpieces according to b). and c). were non-porous and showed a dense structure.
  • a suspension 28 was filled from the powder of the material with the designation B 1914 (nickel-based alloy corresponding to G-Ni 110 from INCO) to the funnel edge of the cavity of the ceramic mold 2.
  • B 1914 nickel-based alloy corresponding to G-Ni 110 from INCO
  • the fine fraction below 50 ⁇ m (proportion approx. 12%) was sieved out from a powder with a particle diameter of 5 to 500 ⁇ m.
  • the moist powder layer (powder suspension 30) which remained after the excess suspension had been suctioned off had an average thickness of 1.5 mm.
  • the remaining coarser fraction of the powder 31 of the nickel-based alloy B 1914 was filled into the ceramic mold 2 in the dry state as the core material and pre-compacted by shaking.
  • the workpiece prepared in this way was first dried at 200 ° C, brought to a temperature of 800 ° C under a pre-vacuum corresponding to a residual pressure of 10 ⁇ 5 bar for a period of 3 h and pre-sintered at this temperature under an argon atmosphere under reduced pressure.
  • the furnace was then brought to a temperature of 1280 ° C. over a period of 2 1/2 hours and sintered at this temperature for 4 hours.
  • the workpiece was then cooled to room temperature over a period of 3 hours.
  • the component was then hot-isostatically pressed at a temperature of 1100 ° C. under a pressure of 1800 bar for 3 h.
  • the metallographic examination revealed a perfect, firmly adhering metallurgical bond between the anti-erosion protective layer, the fine-grained edge zone and the core material. All structural zones were completely dense (see Fig. 13). As a result, the mechanical properties such as fatigue strength and creep resistance were excellent. The corrosion resistance was also excellent.
  • Example 3 a porous, highly damping turbine blade 49 for internal cooling (feed 44, discharge 45 of the cooling medium) of the same final dimensions was produced from the titanium alloy Ti6Al4V. But the goal was different. Instead of obtaining a completely sealed component in the end, hot isostatic pressing for the purpose of post-compression and pore closing was deliberately omitted. This fact was taken into account when dimensioning the ceramic mold 2, since only the reduction of the workpiece due to the usual shrinkage had to be taken into account. Two powder mixtures were assumed: fine-grained from 5 to 70 ⁇ (powder 39); coarse-grained from 50 to 500 ⁇ .
  • the fine fraction of 50 to 200 ⁇ m was used to build up the second layer of the edge zone (Puvler 4) sieved, so that a coarse fraction (powder 42) of 200 to 500 microns remained for the highly porous core 48. Care was taken to ensure that the front of the blade root had no fine and medium-grained edge zone.
  • Example 3 The procedure was exactly the same as in Example 3.
  • the sintering process was carried out under an argon atmosphere at a temperature of 1150 ° C. for 6 hours.
  • the density of the coarse-grained core 48 was on average 70%, that of the fine and medium-grained edge zone (outer skin 46 and intermediate layer 47) 75%.
  • the open pore volume available for the passage of the gaseous cooling medium was therefore 30 or 25%.
  • the mechanical-dynamic investigation showed that the blade had excellent damping properties in the temperature range mentioned. This was a further advantage in addition to the excellent internal cooling of the blade, which only caused small temperature gradients.
  • a rotating body consisting of a shaft and 2 disks similar to FIG. 1 was produced as a component made of silicon carbide with SiC fiber reinforcement from powders.
  • the component 1 (rotating body) had a unit weight of approx. 1 kg.
  • the discs had a diameter of 80 mm and a width of 20 mm.
  • the diameter of the shaft was 20 mm.
  • the solvent of the binder was driven off by drying at 60 ° C / 1 h. This process step was repeated 2 more times until a surface layer of approximately 0.8 mm thickness had been achieved. Now an intermediate layer with a thicker one Carrier solution of a different composition and a coarser powder applied.
  • the carrier solution had the following composition: Binder: "Mowid 4/88" (polyvinyl alcohol) 2 g to 10 ml deionized water Liquefier: tetramethylammonium hydroxide 5 ml to 100 ml finished solution.
  • a first fiber layer (reinforcing fibers 54) of SiC fibers was inserted and moistened with ethyl alcohol. Thereupon, medium-fine SiC powder with a particle size of 10 to 100 ⁇ m was filled in and the whole was dried at 60 ° C./1 h. Then followed a second layer of SiC fibers (reinforcing fibers 54) according to the analogous method, which was moistened again and covered with a medium-fine SiC powder layer (fine-grained casing 53). After drying again, the coarse fraction of the SiC powder forming the coarse-grained core zone 55 was filled dry into the remaining cavity and pre-compacted by vibration.
  • the whole was dried under vacuum and the binder decomposed (350 ° C / 2 h).
  • the mixture was then heated to a temperature of 1500 ° C. at a rate of 10 ° C. per minute and this temperature was maintained for 2 hours.
  • the temperature was raised to 1650 ° C. in the course of 1 h and kept at this value for 2 h.
  • Form 2 was then removed and the workpiece was heated to 2000 ° C. and held for 6 hours. At this temperature, core zone 55 also sintered together to a density of over 90%.
  • the edge zone reached a density of 100%. Without additional encapsulation, the workpiece was then hot-isostatically pressed at a temperature of 1800 ° C. and a pressure of 2000 bar for 4 hours under an argon atmosphere. The investigation after cooling also showed a core density of over 99% of the theoretical value.
  • the process for producing a sintered body with an edge zone 4 with targeted surface properties is carried out by first applying fine-grain powder on the inner surface of the hollow negative mold 2 which determines the shape of the sintered body, the mean grain size of which is at most 60% of the mean grain size of the material used to build up the Sintered powder used is in the range of Edge zone 4 forms a fine-grained surface skin and then the mold 2 is filled with said powder to form a coarse-grained core 5 and the green compact thus formed, with or without mold 2, is subjected to a sintering process. In this way, either a fine-grained, dense edge zone 4 with a smooth surface or a fine-grained, porous edge zone 4 with fine, continuous open pores is produced in the surface.
  • a fine-grained, dense edge zone (4; 50) of high strength and a coarse-grained, highly porous core 5 are also produced as a stiffening framework.
  • the fine-grained surface skin is formed by slurrying fine-grained powder in a liquid to form a suspension 23, pouring it into the hollow mold 2 and pivoting it on the inside surface for the purpose of adhering the powder particles, and removing the excess slurry (23; 24) of the fine-grained powder the form 2 emptied or suctioned and the latter is dried for the purpose of solidifying the fine-grained surface skin.
  • the inner surface of the hollow negative mold 2 is moistened with a well-wetting liquid 36, the powder is poured into the mold and the excess is emptied again, whereupon the smaller fractions of the powder adhering to the inner surface of the mold 2 associated fine-grained powder particles are dried for solidification.
  • the process of applying the fine-grained powder to build up the fine-grained surface skin is preferably repeated several times, with several layers of the edge zone 4 being built up.
  • coarser coarser powders are successively used in accordance with a special embodiment of the method for applying the various layers of the edge zone 4, and in this way a grain size structure that increases continuously after the core 5 is created.
  • materials of different compositions are used to build up the multilayer edge zone 4 of the sintered body for the individual layers.
  • the fine-grained surface skin is first densely sintered to form a hollow body, the latter is filled with powder, and the whole is further treated by final sintering and / or hot isostatic pressing with or without encapsulation to form the final body.

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  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Materials Engineering (AREA)
  • Powder Metallurgy (AREA)
  • Producing Shaped Articles From Materials (AREA)
EP91102429A 1990-03-14 1991-02-20 Procédé de préparation d'un article fritté avec une couche externe compacte et une surface lisse Withdrawn EP0446673A1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
CH81690 1990-03-14
CH816/90 1990-03-14
CH2453/90 1990-07-24
CH245390 1990-07-24

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EP0446673A1 true EP0446673A1 (fr) 1991-09-18

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4338457A1 (de) * 1993-11-11 1995-05-18 Mtu Muenchen Gmbh Bauteil aus Metall oder Keramik mit dichter Außenschale und porösem Kern und Herstellungsverfahren
WO1995024286A1 (fr) * 1994-03-10 1995-09-14 Man B & W Diesel A/S Procede de fabrication d'un ajutage pour clapet d'admission de carburant et cet ajutage
EP0909869A3 (fr) * 1997-10-14 1999-04-28 Camco International Inc. Surchouche en métal dur pour des trépans de forages
EP2910324A3 (fr) * 2014-02-25 2016-03-09 General Electric Company Procédé de fabrication d'un objet tridimensionel à l'aide de poudres
CN119489186A (zh) * 2024-11-25 2025-02-21 昆明理工大学 一种表层致密内部多孔的医用钛合金制备方法

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2464517A (en) * 1943-05-13 1949-03-15 Callite Tungsten Corp Method of making porous metallic bodies
DE2015450A1 (de) * 1969-04-02 1970-10-08 Davy and United Engineering Company Ltd., Sheffield, Yorkshire (Großbritannien) Verfahren zum Herstellen eines zusammengesetzten, weitgehend zylindrischen Körpers
WO1981003634A1 (fr) * 1980-06-11 1981-12-24 Uddeholms Ab Procede de fabrication de pieces metalliques comprimees et frittees
US4830822A (en) * 1985-08-26 1989-05-16 Gte Products Corporation Variable density article and method for producing same
EP0354376A1 (fr) * 1988-07-14 1990-02-14 Nkk Corporation Procédé de fabrication d'articles frittés ayant une densité élevée

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2464517A (en) * 1943-05-13 1949-03-15 Callite Tungsten Corp Method of making porous metallic bodies
DE2015450A1 (de) * 1969-04-02 1970-10-08 Davy and United Engineering Company Ltd., Sheffield, Yorkshire (Großbritannien) Verfahren zum Herstellen eines zusammengesetzten, weitgehend zylindrischen Körpers
WO1981003634A1 (fr) * 1980-06-11 1981-12-24 Uddeholms Ab Procede de fabrication de pieces metalliques comprimees et frittees
US4830822A (en) * 1985-08-26 1989-05-16 Gte Products Corporation Variable density article and method for producing same
EP0354376A1 (fr) * 1988-07-14 1990-02-14 Nkk Corporation Procédé de fabrication d'articles frittés ayant une densité élevée

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4338457A1 (de) * 1993-11-11 1995-05-18 Mtu Muenchen Gmbh Bauteil aus Metall oder Keramik mit dichter Außenschale und porösem Kern und Herstellungsverfahren
FR2712218A1 (fr) * 1993-11-11 1995-05-19 Mtu Muenchen Gmbh Pièce en métal ou en céramique à coque extérieure dense et à âme poreuse, ainsi que son procédé de fabrication.
DE4338457C2 (de) * 1993-11-11 1998-09-03 Mtu Muenchen Gmbh Bauteil aus Metall oder Keramik mit dichter Außenschale und porösem Kern und Herstellungsverfahren
WO1995024286A1 (fr) * 1994-03-10 1995-09-14 Man B & W Diesel A/S Procede de fabrication d'un ajutage pour clapet d'admission de carburant et cet ajutage
RU2124417C1 (ru) * 1994-03-10 1999-01-10 Ман Б Энд В Диесель А/С Сопло клапана для впуска топлива и способ его изготовления
EP0909869A3 (fr) * 1997-10-14 1999-04-28 Camco International Inc. Surchouche en métal dur pour des trépans de forages
EP2910324A3 (fr) * 2014-02-25 2016-03-09 General Electric Company Procédé de fabrication d'un objet tridimensionel à l'aide de poudres
US10780501B2 (en) 2014-02-25 2020-09-22 General Electric Company Method for manufacturing objects using powder products
US11426792B2 (en) 2014-02-25 2022-08-30 General Electric Company Method for manufacturing objects using powder products
CN119489186A (zh) * 2024-11-25 2025-02-21 昆明理工大学 一种表层致密内部多孔的医用钛合金制备方法

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