WO2005009654A2 - Procede de production de composants d'une turbine a gaz - Google Patents

Procede de production de composants d'une turbine a gaz Download PDF

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Publication number
WO2005009654A2
WO2005009654A2 PCT/DE2004/001468 DE2004001468W WO2005009654A2 WO 2005009654 A2 WO2005009654 A2 WO 2005009654A2 DE 2004001468 W DE2004001468 W DE 2004001468W WO 2005009654 A2 WO2005009654 A2 WO 2005009654A2
Authority
WO
WIPO (PCT)
Prior art keywords
powder
shaped body
gas turbine
sintering
during sintering
Prior art date
Application number
PCT/DE2004/001468
Other languages
German (de)
English (en)
Other versions
WO2005009654A3 (fr
Inventor
Josef Kranzeder
Max Kraus
Claus Müller
Erich Steinhardt
Original Assignee
Mtu Aero Engines Gmbh
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Mtu Aero Engines Gmbh filed Critical Mtu Aero Engines Gmbh
Publication of WO2005009654A2 publication Critical patent/WO2005009654A2/fr
Publication of WO2005009654A3 publication Critical patent/WO2005009654A3/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/22—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces for producing castings from a slip
    • B22F3/225—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces for producing castings from a slip by injection molding
    • 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
    • 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
    • B22F2003/1042—Sintering only with support for articles to be sintered
    • 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 a method for producing components of a gas turbine according to the preamble of patent claim 1.
  • the most important materials used today for aircraft engines or other gas turbines are titanium alloys, nickel alloys (also known as super alloys) and high-strength steels.
  • the high-strength steels are used for shaft parts, gear parts, compressor housings and turbine housings. Titanium alloys are typical materials for compressor parts. Nickel alloys are suitable for the hot parts of the aircraft engine.
  • Powder-metallurgical injection molding has proven itself in the manufacture or manufacture of precision components from metallic or ceramic powders. Powder-metallurgical injection molding is related to plastic injection molding and is also known as metal mold injection or metal injection molding (MIM). Powder-metallurgical injection molding can be used to manufacture components that achieve almost the full density and approx. 95% of the static strength of forged parts. The reduced dynamic strength compared to forged parts can be compensated for by suitable material selection.
  • MIM metal mold injection or metal injection molding
  • a powder preferably a metal powder, hard metal powder or ceramic powder, with a binding agent medium and possibly a plasticizer is mixed to a homogeneous mass.
  • Shaped bodies are produced from this homogeneous mass by injection molding.
  • the injection molded moldings already have the geometric shape of the component to be produced, but their volume is increased by the volume of the binder and plasticizer added.
  • the binder and plasticizer are removed from the injection molded body in a debinding process. Subsequently, the molded body is compacted into the finished component during sintering.
  • the volume of the molded body decreases, whereby it is crucial that the dimensions of the molded part have to shrink uniformly in all three spatial directions.
  • the linear shrinkage in volume is between 10% and 20%, depending on the binder and plasticizer content.
  • a sintering temperature is selected during sintering which is approximately in the vicinity of the melting temperature of the metal.
  • the metal accordingly softens and the molded body can deform accordingly.
  • the shaped body In the case of sintering, the shaped body must be supported, the support having to support the shaped body during sintering and, at the same time, should ensure good mobility of the shaped body during sintering. This is particularly problematic when complex, three-dimensional components, such as components of gas turbines, are to be produced by powder metallurgy injection molding.
  • the present invention is based on the problem of proposing a novel method for producing components of a gas turbine. This problem is solved in that the method mentioned at the outset is further developed by the features of the characterizing part of patent claim 1.
  • the or each shaped body is stored in a powdery material during sintering.
  • the storage of the shaped body in the powdery material according to the invention achieves, on the one hand, that complex three-dimensional components or shaped bodies can be well supported for the sintering process and thus can be stored well.
  • the storage in the powdery material ensures sufficient freedom of movement of the shaped body or component during sintering. By eliminating rigid bearings, the component can move evenly in all three spatial directions during sintering. Unwanted geometric deformations as well as the formation of cracks or other defects on the component to be manufactured can be minimized.
  • the or each shaped body is preferably floatingly stored in a powdery material.
  • the or each shaped body is preferably stored in a bed of powder material, the density of the powder material roughly corresponding to the density of the or each shaped body.
  • the method according to the invention is used in particular for the manufacture of blades or blade parts, in particular guide blades or guide blade parts, of an aircraft engine, these blades or blade parts consisting of a nickel-based alloy or also a titanium-based alloy.
  • the or each corresponding shaped body is stored in a ceramic powder, the ceramic powder preferably having an approximately round particle shape and an average grain size of 0.05 mm to 2 mm.
  • Fig. 1 a block diagram to illustrate the individual process steps in powder metallurgical injection molding.
  • the present invention relates to the production of components of a gas turbine, in particular an aircraft engine, by powder metallurgical injection molding.
  • Powder metallurgical injection molding is also known as metal injection molding (MIM).
  • a metal powder, hard metal powder or ceramic powder is provided in a first step 10.
  • a binder and optionally a plasticizer are provided in a second step 11.
  • the metal powder provided in process step 10 and the binder and plasticizer provided in process step 11 are mixed in process step 12 so that a homogeneous mass is formed.
  • the volume proportion of the metal powder in the homogeneous mass is preferably between 50% and 70%.
  • the proportion of binder and plasticizer in the homogeneous mass therefore fluctuates approximately between 30% and 50%.
  • This homogeneous mass of metal powder, binder and plasticizer is further processed in the sense of step 13 by injection molding. Moldings are manufactured during injection molding. These moldings already have all the typical features of the components to be produced. In particular, the shaped bodies have the geometric shape of the component to be manufactured. However, they have a volume increased by the amount of the detergent and the amount of plasticizer.
  • Process step 14 the binder and the plasticizer are expelled from the moldings.
  • Process step 14 can also be referred to as the final binding process. Binding agents and plasticizers can be driven out in different ways. This is usually done by fractional, thermal decomposition or evaporation. Another possibility is to suck out the thermally liquefied binding and Plasticizers by capillary forces, by sublimation or by solvents.
  • the shaped bodies are sintered in the sense of step 15.
  • the shaped bodies are compressed into the components with the final geometric properties. Accordingly, during the sintering, the shaped bodies become smaller, the dimensions of the shaped bodies having to shrink uniformly in all three spatial directions.
  • the linear shrinkage is between 10% and 20% depending on the binder content and plasticizer content.
  • the sintering can be carried out under various protective gases or under vacuum.
  • step 16 the finished component is present, which is represented by step 16 in FIG. 1.
  • the component can still be subjected to a finishing process in the sense of step 17.
  • the finishing process is optional.
  • a ready-to-install component can already be present immediately after sintering.
  • the shaped body is stored in a bed of powder material.
  • the grain size, particle shape and composition of the powder material is optimized with regard to sufficient support and sufficient freedom of movement of the shaped body.
  • the powder material is selected such that the powder material does not react with the material of the molded body. gier that in particular the powder material is not wetted by the metal of the molded body and in particular does not dissolve in the metal.
  • the powder material for storing the shaped body during sintering is preferably selected such that an expansion coefficient of the powder material forming the powder bed essentially corresponds to the expansion coefficient of the shaped body, that is to say the expansion coefficient of the metal. Ceramic powder or powder made of intermetallic compounds is used in particular as the powder material for forming the powdery bed.
  • the or each molded body is floatingly stored in a powdery bed during sintering.
  • the or each shaped body is stored in a bed of powder material, the density of the powder material roughly corresponding to the density of the shaped body.
  • the density of the powder material is preferably in a range of ⁇ 30% of the density of the shaped body.
  • the method according to the invention is particularly suitable for the production of components for gas turbines, in particular for aircraft engines.
  • the production of guide blades or guide blade parts or guide blade segments and rotor blades or rotor blade parts or rotor blade segments of an aircraft engine is preferred.
  • Sealing segments, adjusting levers or securing parts for gas turbines can also be produced in the sense of the method according to the invention.
  • Such guide vanes or moving blades consist of a nickel alloy or nickel-based alloy or titanium alloy or titanium-based alloy.
  • a ceramic powder with an average grain size of 0.05 mm to 2 mm and a round particle shape is then preferably used as the material for forming the powder bed.
  • BN, SiC, Si3N4, Al203, Zr02, borides or suicides are particularly suitable as powder material for providing the powder bed when the shaped bodies are sintered It is therefore within the meaning of the present invention in the manufacture of components with the aid of powder metallurgical injection molding during the sintering of the shaped bodies to store them in a powdery material, namely a powder bed.
  • a powdery material namely a powder bed.
  • This enables complex components to be manufactured with the desired dimensional accuracy. Unwanted, geometric deformations are avoided, so that post-processing can be reduced. This reduces the number of manufacturing steps and thus results in lower manufacturing costs.
  • the powdery material that is used to store the shaped bodies during sintering is inexpensive and can be used several times. This is also advantageous for cost reasons.

Landscapes

  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Mechanical Engineering (AREA)
  • Powder Metallurgy (AREA)

Abstract

L'invention concerne un procédé de production de composants d'une turbine à gaz, en particulier d'un moteur d'avion, par un moulage par injection tel que mis en oeuvre dans la métallurgie des poudres. Dans un tel procédé de moulage par injection, une poudre métallique est d'abord mélangée avec un liant pour former une matière homogène qui est ensuite moulée par injection pour former au moins un corps moulé. Le ou chaque corps moulé est alors soumis à un procédé de retrait du liant. Enfin, le ou chaque corps moulé est compacté par frittage pour former au moins un composant présentant les caractéristiques géométriques souhaitées. Selon l'invention, le ou chaque corps moulé est, lors du frittage, déposé dans une matière pulvérulente.
PCT/DE2004/001468 2003-07-19 2004-07-08 Procede de production de composants d'une turbine a gaz WO2005009654A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10332882.3 2003-07-19
DE10332882A DE10332882A1 (de) 2003-07-19 2003-07-19 Verfahren zur Herstellung von Bauteilen einer Gasturbine

Publications (2)

Publication Number Publication Date
WO2005009654A2 true WO2005009654A2 (fr) 2005-02-03
WO2005009654A3 WO2005009654A3 (fr) 2005-06-16

Family

ID=33560219

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2004/001468 WO2005009654A2 (fr) 2003-07-19 2004-07-08 Procede de production de composants d'une turbine a gaz

Country Status (2)

Country Link
DE (1) DE10332882A1 (fr)
WO (1) WO2005009654A2 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2020240535A1 (fr) * 2019-05-30 2020-12-03 Stratasys Ltd. Procédé de conservation de forme d'un objet pendant le frittage

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3608095A1 (de) * 1985-03-15 1986-10-16 MTU Motoren- und Turbinen-Union München GmbH, 80995 München Verfahren zum herstellen von sinterformteilen
DE3527367A1 (de) * 1985-07-31 1987-02-12 Mtu Muenchen Gmbh Auf pulvermetallurgischem wege hergestellte bauteile
US4783297A (en) * 1983-05-13 1988-11-08 Ngk Insulators, Ltd. Method of producing ceramic parts
EP0633440A1 (fr) * 1993-07-02 1995-01-11 Abb Research Ltd. Procédé pour la préparation d'un support de frittage

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS61195902A (ja) * 1985-02-25 1986-08-30 Matsushita Electric Works Ltd 希土類磁石の焼結方法
JPH0820804A (ja) * 1994-07-08 1996-01-23 Sumitomo Electric Ind Ltd 焼結部品の製造方法
JPH0892606A (ja) * 1994-09-28 1996-04-09 Olympus Optical Co Ltd 金属粉末焼結体の製造方法
JPH09256003A (ja) * 1996-03-22 1997-09-30 Olympus Optical Co Ltd 金属粉末射出成形方法

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4783297A (en) * 1983-05-13 1988-11-08 Ngk Insulators, Ltd. Method of producing ceramic parts
DE3608095A1 (de) * 1985-03-15 1986-10-16 MTU Motoren- und Turbinen-Union München GmbH, 80995 München Verfahren zum herstellen von sinterformteilen
DE3527367A1 (de) * 1985-07-31 1987-02-12 Mtu Muenchen Gmbh Auf pulvermetallurgischem wege hergestellte bauteile
EP0633440A1 (fr) * 1993-07-02 1995-01-11 Abb Research Ltd. Procédé pour la préparation d'un support de frittage

Non-Patent Citations (4)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN Bd. 011, Nr. 025 (M-556), 23. Januar 1987 (1987-01-23) -& JP 61 195902 A (MATSUSHITA ELECTRIC WORKS LTD), 30. August 1986 (1986-08-30) *
PATENT ABSTRACTS OF JAPAN Bd. 1996, Nr. 05, 31. Mai 1996 (1996-05-31) -& JP 08 020804 A (SUMITOMO ELECTRIC IND LTD), 23. Januar 1996 (1996-01-23) *
PATENT ABSTRACTS OF JAPAN Bd. 1996, Nr. 08, 30. August 1996 (1996-08-30) -& JP 08 092606 A (OLYMPUS OPTICAL CO LTD), 9. April 1996 (1996-04-09) *
PATENT ABSTRACTS OF JAPAN Bd. 1998, Nr. 01, 30. Januar 1998 (1998-01-30) -& JP 09 256003 A (OLYMPUS OPTICAL CO LTD), 30. September 1997 (1997-09-30) *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2020240535A1 (fr) * 2019-05-30 2020-12-03 Stratasys Ltd. Procédé de conservation de forme d'un objet pendant le frittage
US11969794B2 (en) 2019-05-30 2024-04-30 Stratasys Ltd. Method for preserving shape of an object during sintering

Also Published As

Publication number Publication date
DE10332882A1 (de) 2005-02-03
WO2005009654A3 (fr) 2005-06-16

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