EP1991380A1 - Procédé de fabrication d'un segment d'étanchéité et segment d'étanchéité à utiliser dans des composants de turbine et de compresseur - Google Patents

Procédé de fabrication d'un segment d'étanchéité et segment d'étanchéité à utiliser dans des composants de turbine et de compresseur

Info

Publication number
EP1991380A1
EP1991380A1 EP07721961A EP07721961A EP1991380A1 EP 1991380 A1 EP1991380 A1 EP 1991380A1 EP 07721961 A EP07721961 A EP 07721961A EP 07721961 A EP07721961 A EP 07721961A EP 1991380 A1 EP1991380 A1 EP 1991380A1
Authority
EP
European Patent Office
Prior art keywords
mixture
sealing segment
molded body
powder
metal
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Withdrawn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
EP07721961A
Other languages
German (de)
English (en)
Inventor
Reinhold Meier
Claus Müller
Franz Prieschl
Siegfried Sikorski
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.)
MTU Aero Engines AG
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 EP1991380A1 publication Critical patent/EP1991380A1/fr
Withdrawn legal-status Critical Current

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
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/009—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine components other than turbine blades
    • 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
    • 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
    • B22F7/062—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 involving the connection or repairing of preformed parts
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/626—Preparing or treating the powders individually or as batches ; preparing or treating macroscopic reinforcing agents for ceramic products, e.g. fibres; mechanical aspects section B
    • C04B35/63—Preparing or treating the powders individually or as batches ; preparing or treating macroscopic reinforcing agents for ceramic products, e.g. fibres; mechanical aspects section B using additives specially adapted for forming the products, e.g.. binder binders
    • C04B35/638—Removal thereof
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B37/00—Joining burned ceramic articles with other burned ceramic articles or other articles by heating
    • C04B37/02—Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles
    • C04B37/021—Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles in a direct manner, e.g. direct copper bonding [DCB]
    • 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
    • B22F2998/10—Processes characterised by the sequence of their steps
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B28—WORKING CEMENT, CLAY, OR STONE
    • B28B—SHAPING CLAY OR OTHER CERAMIC COMPOSITIONS; SHAPING SLAG; SHAPING MIXTURES CONTAINING CEMENTITIOUS MATERIAL, e.g. PLASTER
    • B28B1/00—Producing shaped prefabricated articles from the material
    • B28B1/002—Producing shaped prefabricated articles from the material assembled from preformed elements
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B28—WORKING CEMENT, CLAY, OR STONE
    • B28B—SHAPING CLAY OR OTHER CERAMIC COMPOSITIONS; SHAPING SLAG; SHAPING MIXTURES CONTAINING CEMENTITIOUS MATERIAL, e.g. PLASTER
    • B28B1/00—Producing shaped prefabricated articles from the material
    • B28B1/24—Producing shaped prefabricated articles from the material by injection moulding
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/60—Aspects relating to the preparation, properties or mechanical treatment of green bodies or pre-forms
    • C04B2235/602—Making the green bodies or pre-forms by moulding
    • C04B2235/6027—Slip casting
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/34—Oxidic
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/34—Oxidic
    • C04B2237/341—Silica or silicates
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/36—Non-oxidic
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/36—Non-oxidic
    • C04B2237/361—Boron nitride
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/36—Non-oxidic
    • C04B2237/363—Carbon
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/40—Metallic
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00018—Manufacturing combustion chamber liners or subparts

Definitions

  • the present invention relates to a method for producing a sealing segment for use in compressor and turbine components by means of powder injection molding and a sealing segment for use in compressor and turbine components consisting of at least a first molded body as the base member and at least one second molded body with a compared to the first molded body higher abrasion than rubbing on.
  • Such sealing segments are used in particular in so-called gap holding systems in the compressor and turbine components for use.
  • such sealing segments or sealing systems have the task to keep a sealing gap of rotating blading to a housing as well as the gap of a standing blading to the rotating rotor hub minimal and thus to guarantee a stable performance with high efficiency.
  • the rotating components of the turbine sealing fins which run in a known manner against honeycomb seals.
  • honeycomb seal is disclosed by WO 2004/061340 Al. This known honeycomb seal consists of a single molded body produced by powder metallurgical injection molding.
  • Said enema process can easily lead to overheating in the sealing fins, if the contact with the honeycomb material takes too long or the resulting resistance in abrading the honeycomb is too high. Damage to the sealing fins can therefore not be ruled out in known sealing segments or corresponding inlet linings.
  • a process according to the invention for producing a sealing segment for use in compressor and turbine components by means of powder injection molding comprises the following process steps according to the invention: a) preparation of a first homogeneous mixture of a metal powder or a mixture of metal powders or a ceramic powder or a mixture of ceramic powders and at least one binder; b) producing a first molded article by injection molding of the first mixture; c) Preparation of a second homogeneous mixture of a metal powder or a mixture of metal powders or a ceramic powder or a mixture of ceramic powders and at least one binder, wherein the second mixture is selected such that it compared to the first mixture for a subsequent common sinter - process has a higher abrasion; d) producing a second shaped body as a rubbing layer by means of injection molding of the second mixture; and e) connecting the first and second shaped bodies to produce the sealing segment.
  • the use of the powder injection molding process ensures a cost-effective and also individual production of the required sealing segments.
  • all sprayable and sinterable metals, metal alloys and ceramics can be used. It is also conceivable to mix the metal or ceramic powders.
  • the sinterable ceramics may include, for example, nitride, oxide and silicate ceramics and carbides.
  • Decisive in the production of the sealing system according to the invention is that the abradable coating consists from the second molded body has a higher abrasion than serving as a base and / or fastener for the sealing segment first molded body. According to the invention it is therefore possible to meet a wide variety of material requirements for such a sealing segment in compressor and turbine components.
  • properties of the second shaped body concerning the abrasion behavior such as the emergence of only low frictional energies and resistances, the good chip formation and removability of the abrasion, or also the prevention of an inflammation of the abrasion when rubbing, individually on the tapping components the turbine, such as sealing fins, are tuned.
  • the stress of the sealing fins is significantly reduced by the rubbing, whereby the corresponding sealing gap can be reduced in an advantageous manner.
  • honeycomb seals or honeycomb inlet coverings with conventional geometry have to be produced; it is also possible to develop aerodynamically more effective and production-technically more cost-effective geometries.
  • honeycomb shape completely eliminated and correspondingly flat layers are produced cost-saving.
  • even the first mold element, which serves as a base or fastener of the sealing segment to vote on the appropriate technical and material engineering conditions. This concerns in particular the temperature and erosion resistance.
  • the bonding of the first and second shaped bodies can take place immediately after their production and before a joint delivery process of the shaped bodies.
  • the joining of the first and second shaped bodies takes place after a separate delivery process and before a subsequent common sintering process of the shaped bodies.
  • the joining of the first and second shaped bodies can be carried out after a separate debinding and sintering process of the molded articles. body takes place. In the latter case, both mechanical and chemical bonding processes are possible.
  • the higher abrasion of the second shaped body is achieved by reducing the proportion of metal powder or ceramic powder in the second mixture.
  • the metal powder or ceramic powder content in the second mixture is only about 15-30% by volume. This results in sintering a porous structure by reduced grain contacts.
  • the higher abrasion of the second molded body is achieved by the use of metal and ceramic powders with reduced sintering activity.
  • metal powder with low purity class, d. H. For example, higher C and O content can be used.
  • deaerated air instead of inertgasverdüstem metal powder leads to a higher C and O occupancy of the surfaces and thus to a reduced sintering activity.
  • inexpensive metal or ceramic powders can be used, it is achieved a homogeneous porosity distribution and a reduction of the demixing effects. Again, no changes to the process parameters are necessary.
  • the higher abrasion of the second shaped body is achieved by admixing binder polymers which do not completely decompose during delivery and / or sintering to form the second mixture.
  • the binder polymers can be selected from the group of phenolic resins or novolac.
  • the addition of binder polymers results in a reduction of the sintering activity, resulting in carbon residues in the grain gussets of the metal or ceramic powder particles in the sintered product, see above that good abrasion properties can be achieved.
  • the higher abrasion of the second molded body is achieved by admixing fillers to the second mixture.
  • the fillers of easily cleavable inert materials such as graphite, bentonite or hexagonal boron nitride and / or materials which decompose at least partially during debindering and / or sintering and contribute to the formation of pores in the second molded body, may arise.
  • an evaporation takes place during sintering, whereby it comes to pore formation in the stripping layer and the second molded body.
  • the fillers do not decompose and in the sintered product, d. H.
  • the stripping layer or the second shaped body remain in the grain gussets of the metal or ceramic powder particles. This results overall in a very easily cleavable or abradable Abstreif für.
  • the formation of pores in the subsequent use of the sealing segment by superficial oxidation for example, in the choice of graphite as a filler.
  • An inventive sealing segment for use in compressor and turbine components consists of at least one first molded body as the base element and / or fastening element and at least one second molded body having a higher abrasion than the squealer layer compared to the first molded body, wherein the first and the second molded body are each by means of powder injection molding is made. Due to the at least two-layer design of the sealing segment according to the invention, it is possible to on the one hand the base and / or fastener, namely the first molded body, as well as the stripping, namely the second molded body, both in their geometries as well as the material compositions to meet the technical and material requirements.
  • the sealing segment may be, for example, an inlet lining for sealing a radial gap between a rotating blade and a housing of a gas turbine. Furthermore, it is possible that the sealing segment is honeycomb-shaped.
  • the sealing segment according to the invention is produced by a method as has been described in detail above.
  • the sealing segment of the invention consists of a plurality of molded articles, wherein at least two molded bodies are produced by means of powder injection molding.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Manufacturing & Machinery (AREA)
  • Ceramic Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Structural Engineering (AREA)
  • Organic Chemistry (AREA)
  • Composite Materials (AREA)
  • Inorganic Chemistry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Powder Metallurgy (AREA)
  • Sealing Devices (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)

Abstract

La présente invention concerne un procédé de fabrication d'un segment d'étanchéité prévu pour être utilisé dans des composants de turbine et de compresseur par moulage par injection de poudres. Ce procédé consiste a) à produire un premier mélange homogène constitué d'une poudre métallique ou un mélange de poudres métalliques ou d'une poudre céramique ou bien un mélange de poudres céramiques et d'au moins un liant, b) à produire un premier corps moulé par moulage par injection du premier mélange, c) à produire un second mélange homogène constitué d'une poudre métallique ou un mélange de poudres métalliques ou d'une poudre céramique ou bien un mélange de poudres céramiques et d'au moins un liant, ce second mélange étant sélectionné de sorte qu'il présente une plus faible résistance à l'abrasion que le premier mélange après un processus de frittage commun suivant, d) à produire un second corps moulé comme couche abradable par moulage par injection du second mélange et e) à lier les premier et second corps moulés pour former le segment d'étanchéité. Cette invention concerne également un segment d'étanchéité prévu pour être utilisé dans des composants de turbine et de compresseur, lequel segment est constitué d'au moins un premier corps moulé comme élément de base et d'au moins un second corps moulé, présentant une résistance à l'abrasion plus faible que le premier corps moulé, comme couche abradable, les premier et second corps moulés étant chacun fabriqués par moulage par injection de poudre.
EP07721961A 2006-03-03 2007-02-27 Procédé de fabrication d'un segment d'étanchéité et segment d'étanchéité à utiliser dans des composants de turbine et de compresseur Withdrawn EP1991380A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006009860A DE102006009860A1 (de) 2006-03-03 2006-03-03 Verfahren zur Herstellung eines Dichtsegments und Dichtsegment zur Verwendung in Verdichter- und Turbinenkomponenten
PCT/DE2007/000360 WO2007098739A1 (fr) 2006-03-03 2007-02-27 Procédé de fabrication d'un segment d'étanchéité et segment d'étanchéité à utiliser dans des composants de turbine et de compresseur

Publications (1)

Publication Number Publication Date
EP1991380A1 true EP1991380A1 (fr) 2008-11-19

Family

ID=38226598

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07721961A Withdrawn EP1991380A1 (fr) 2006-03-03 2007-02-27 Procédé de fabrication d'un segment d'étanchéité et segment d'étanchéité à utiliser dans des composants de turbine et de compresseur

Country Status (5)

Country Link
US (1) US20090041607A1 (fr)
EP (1) EP1991380A1 (fr)
CA (1) CA2643568A1 (fr)
DE (1) DE102006009860A1 (fr)
WO (1) WO2007098739A1 (fr)

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DE102008019331A1 (de) * 2008-04-16 2009-10-22 Rolls-Royce Deutschland Ltd & Co Kg Einlaufdichtung für den Kompressor eines Gasturbinentriebwerks
US10226818B2 (en) 2009-03-20 2019-03-12 Pratt & Whitney Canada Corp. Process for joining powder injection molded parts
CA2797746C (fr) * 2009-04-29 2021-12-07 Maetta Sciences Inc. Procede de co-traitement de composants dans un procede de moulage par injection de metal, et composants produits par celui-ci
DE102009055914A1 (de) * 2009-11-27 2011-06-09 Rolls-Royce Deutschland Ltd & Co Kg Dichtringe für eine Labyrinthdichtung
US9903275B2 (en) 2014-02-27 2018-02-27 Pratt & Whitney Canada Corp. Aircraft components with porous portion and methods of making
US9970318B2 (en) * 2014-06-25 2018-05-15 Pratt & Whitney Canada Corp. Shroud segment and method of manufacturing
US9517507B2 (en) 2014-07-17 2016-12-13 Pratt & Whitney Canada Corp. Method of shaping green part and manufacturing method using same
US20160263656A1 (en) 2015-03-12 2016-09-15 Pratt & Whitney Canada Corp. Method of forming a component from a green part
CN104841940A (zh) * 2015-04-01 2015-08-19 宝得粉末注射成形（常熟）有限公司 小型涡轮发动机叶片的制备方法

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US6969231B2 (en) * 2002-12-31 2005-11-29 General Electric Company Rotary machine sealing assembly
DE10331397A1 (de) * 2003-07-11 2005-01-27 Mtu Aero Engines Gmbh Verfahren zur Herstellung von Bauteilen einer Gasturbine sowie entsprechendes Bauteil
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See references of WO2007098739A1 *

Also Published As

Publication number Publication date
DE102006009860A1 (de) 2007-09-06
CA2643568A1 (fr) 2007-09-07
US20090041607A1 (en) 2009-02-12
WO2007098739A1 (fr) 2007-09-07

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