WO2012051978A2 - Pièce et procédé pour concevoir, réparer et/ou construire une pièce de ce type - Google Patents

Pièce et procédé pour concevoir, réparer et/ou construire une pièce de ce type Download PDF

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Publication number
WO2012051978A2
WO2012051978A2 PCT/DE2011/001727 DE2011001727W WO2012051978A2 WO 2012051978 A2 WO2012051978 A2 WO 2012051978A2 DE 2011001727 W DE2011001727 W DE 2011001727W WO 2012051978 A2 WO2012051978 A2 WO 2012051978A2
Authority
WO
WIPO (PCT)
Prior art keywords
component
blade element
cold gas
kinetic
layer
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.)
Ceased
Application number
PCT/DE2011/001727
Other languages
German (de)
English (en)
Other versions
WO2012051978A3 (fr
Inventor
Manuel Hertter
Andreas Jakimov
Mihaela-Sorina Seitz
Marcin Olbrich
Erwin Bayer
Jürgen Kraus
Bertram Kopperger
Klaus Broichhausen
Hans Banhirl
Wolfgang Werner
Eberhard Knodel
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 WO2012051978A2 publication Critical patent/WO2012051978A2/fr
Publication of WO2012051978A3 publication Critical patent/WO2012051978A3/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P6/00—Restoring or reconditioning objects
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C24/00—Coating starting from inorganic powder
    • C23C24/02—Coating starting from inorganic powder by application of pressure only
    • C23C24/04—Impact or kinetic deposition of particles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/005—Repairing methods or devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to a component and a method for forming, repairing and / or constructing such a component, in particular a blade element of a gas turbine, e.g. a gas turbine of an aircraft engine , compaction by means of kinetic cold gas.
  • a component in particular a blade element of a gas turbine, e.g. a gas turbine of an aircraft engine , compaction by means of kinetic cold gas.
  • blades such as blades of aircraft engines, such as turbine blades or compressor blades
  • manufacture of blades is relatively expensive. Therefore, such blades are usually repaired in the event of damage or wear, if possible.
  • a damaged or worn blade is not necessarily always replaced with a new, but only in the event that the blade is no longer usable or no longer repairable.
  • the repair of blades is done so far usually by means of the so-called "patching" or by build-up welding.
  • a portion of the blade, which has a damaged portion is removed from the blade by a cut.
  • this relates to a portion of the blade tip includes, as often occur in the blade tip damage or wear.
  • this can also be done by means of standardized spare parts.
  • the severed damaged segment is replaced by a correspondingly identical intact segment or supplemented by welding.
  • a new segment is usually made separately and possibly formed with an oversize and joined to the rest of the bucket. In particular, in cases in which the new segment has an excess, then a processing takes place, by means of which the desired shape is generated.
  • WO 2008/003295 A2 discloses a method for repairing and / or replacing individual elements of a component of a gas turbine.
  • a replacement element is connected to a component by means of inductive low-frequency or high-frequency pressure welding.
  • the invention now has the object of providing a simple possibility of repairing elements, in particular blade elements of gas turbines, for example of gas turbines of aircraft engines, etc.
  • a method for forming, repairing and / or assembling or replacing a gas turbine component, as well as a corresponding device. More specifically, a method is provided for forming, repairing, and / or assembling or replacing a component, in particular a vane element, eg, a turbine or a compressor, a gas turbine casing element or a gas turbine disk element, the method comprising the steps:
  • the method has the advantage that a fine-grained forging structure can be achieved by the kinetic cold gas compacting. Furthermore, kinetic cold gas compacting provides minimally invasive and individual repair of damaged or worn areas of gas turbine components, such as gas turbine components. Shovel elements, possible. This means that only the damaged areas can be removed and the missing material can be individually supplemented by cold gas spraying.
  • the damaged and / or worn portion of the component is first removed, and then the remote portion is sprayed layer-by-layer on the component and the removed portion is filled by kinetic cold gas compaction.
  • the filled area can be formed with an oversize and later be reworked accordingly, so that it has a nominal dimension.
  • the damaged and / or wear-prone area of the component is first removed and then inserted into the remote area of the component a corresponding part and connected by means of kinetic Kaltgaskompaktieren with the component. This has the advantage that a larger area which has previously been removed from the component can be easily replaced or refilled.
  • one or more layers which are applied to the component by the kinetic cold gas compacting are subsequently processed or reworked, for example by means of milling and / or an electrochemical method.
  • This has the advantage that the predetermined contour can be formed, wherein the contour, for example, can have a more uniform structure, in that sprayed-on layers are reworked.
  • the adhesion conditions for the next layer can be further improved, for example by deliberately thawing the surface of the component.
  • the separating surfaces or separating edges, on which the damaged or wear-prone area of the component has been removed are activated, in particular by plasma cleaning or by mechanical blasting, such as, for example, particle blasting.
  • plasma cleaning or by mechanical blasting such as, for example, particle blasting.
  • FIG. 1 shows a perspective view of a component to be repaired, here blade element
  • FIG. 2 is a flow diagram of the repair of a component, here blade element, according to the invention.
  • the invention will be described in more detail below with reference to a blade element as an example of a gas turbine component.
  • a blade element any other element of a gas turbine can be provided as a gas turbine component, for example a gas turbine housing element, a gas turbine disk element, etc., to name only two further examples of gas turbine components.
  • FIG. 1 shows a greatly simplified view of a blade element 10 as a gas turbine component which is repaired in accordance with the method according to the invention and is provided, for example, as a component 22 as an BLIS blade element on a disk.
  • the invention is not limited to the specific illustration of the blade element 10 in FIG.
  • the greatly simplified representation of the blade element 10 serves as a gas turbine component only for explaining the invention.
  • the blade element 10 for example in the region of the blade tip 12, has a region 14 with damage.
  • a damaged component eg a blade element 10, for example a so-called BLISK (bladed disc) blade element or a bling ring blade element, is thereby repaired by the blade element 10 or gas turbine component or its Blade profile or gas turbine component profile by means of kinetic Kaltgaskompaktiern (K3) is at least partially built or supplemented.
  • K3 kinetic Kaltgaskompaktiern
  • the region 14 is first removed or cut out, which has damage and / or corresponding wear.
  • the removed or to be removed area 16 which contains the damaged area is indicated in FIG. 1 with a dashed line. This line indicates the separation edge or separation region 22 at which the region is cut out or severed.
  • the contour of the area to be removed 16 can be varied as desired and is not limited to the contour shown in FIG.
  • areas damaged or affected by wear can be removed at various locations, or individual areas can be combined to form a region 16 to be removed and severed from the blade element 10 in one piece, if damaged areas or areas subject to wear, e.g. lie close to each other.
  • the missing region 16 is supplemented or fully filled again by means of kinetic cold-gas compacting, as will be described below with reference to FIG. 2.
  • the separating edge or the separating region 22 can initially optionally be additionally activated after the separation of the region 16 to be separated, for example by blasting or plasma cleaning, before the kinetic cold gas compacting takes place.
  • FIG. 2 now shows a flowchart of the repair of a gas turbine component, eg here a blade element, according to the invention, wherein a blade element can be repaired, as shown in FIG.
  • the damaged area of the gas turbine component in this case the blade element, is first removed in FIG. 1 in a first step S1.
  • the separation area where the damaged area has been removed can optionally be additionally activated.
  • the activation of the separation surface can be effected for example by means of radiation or a plasma cleaning or by means of another suitable method or combination of methods.
  • the missing material in the cut-out region of the blade element to be repaired is supplemented by kinetic cold gas compacting (K3), for example with an oversize or, in an alternative embodiment, a blade element part is inserted into this region in a step S3 * and then connected via kinetic cold gas compacting with the remaining blade element in a step S3 **.
  • K3 kinetic cold gas compacting
  • material particles or powder of metal or a metal alloy are sprayed, in layers or in zones in the remote area of the blade element, in order to form the blade element, e.g. build up layer by layer in this area or to connect an inserted blade element part with the blade element.
  • the layers can each be constructed from the same material particles or material powders or combination of material particles or material powders or layers of different material particles or material powders or material particle combinations or material powder combinations can be combined.
  • the layers can be applied or provided in such a way that a smooth transition between the layers is given or the layers are separated from one another.
  • the powder of metal or a metal alloy has ceramic particles or ceramic powder, polymer powder or particles of another non-conductive material in an alternative embodiment.
  • the powder or powder mixture is applied via a spray nozzle, in particular a Laval nozzle, on the blade element.
  • An injection material jet is achieved by an expansion of a carrier gas and by the supply of the powder mixture.
  • the carrier gas can be preheated to a predetermined process temperature.
  • the heating of the carrier gas, for example air, nitrogen, helium and / or water vapor, etc., before coating serves primarily to increase the outflow velocity in the spray nozzle and to improve the forging properties of the powder particles.
  • the blade element Due to the kinetic Kaitgaskompakt Schlieren no melt for the blade element is necessary, but it can be mixed together different materials or material powder, with a wide range of material combinations or Werkstoffmi loops can be achieved.
  • the blade element can be produced with regions having different properties, for example the blade element can be formed with an armor of the leading edge or an erosion protection, as well as with an armor of the fin region and / or an armor of so-called Z-notches, etc
  • short fiber reinforcements can be used in the construction of blade elements.
  • At least one or even each layer may additionally be processed prior to the spraying of the next layer in order, for example, to produce the desired geometry of the blade element and / or to provide the best possible adhesion conditions for the next spray layer through a specifically structured surface, for example by a Thawing or ablation of the uppermost particle layer.
  • the processing of the respective layer may, for example, be at least partially machined, e.g. by milling, and / or by means of an electrochemical process.
  • a gas turbine component in this case a blade element or airfoil
  • a gas turbine component in this case a blade element or airfoil
  • one or more bumps or projections in the base body eg a disk base body in a BLISK ("bladed disc") blade element or a ring base body in the case of a BLING (bladed ring) blade element, can optionally additionally be formed. milled, for example, on which or which then the measuring shovel element splints is sprayed on.
  • each layer may additionally be processed prior to the spraying of the next layer in order, for example, to produce the desired geometry of the blade element and / or to achieve the best possible adhesion conditions for a next spray layer through a specifically structured surface create. Likewise, however, only at the end of the spraying of all
  • Layers are produced by an electrochemical process and / or by a milling process, the final contour of the blade element. This applies accordingly if, as described above, only a cut-out region of a blade element is supplemented. Again, the blade element can be obtained only at the end by an electrochemical process or by milling its final contour.
  • the blade element can be sprayed on, for example, with a slurry by kinetic cold gas compacting.
  • a subsequent milling or lowering, for example, an annular space of a B LI SK blade element with the thinning of the blade element can be connected to a predetermined nominal size.
  • the method is also suitable for supplementing components so as to be able to strongly rejuvenate the blanks z. B. housings.
  • the invention is not limited to milling or an electrochemical method for machining a blade element. In principle, any other method or combination of methods suitable for appropriately machining the vane element may be used. with the desired contour and / or to achieve optimal adhesion conditions by creating a specifically structured surface.
  • the supplementing of the cut-out damaged and / or worn area of the blade element by means of kinetic cold gas compacting has the advantage that in the kinetic cold gas-compacted layer or layers no melt structure is formed or exists but a fine-grained forging structure. Furthermore, kinetic cold gas compaction allows minimally invasive and individual repair of damaged or worn areas. In addition, the erfindugnssiee method allows a generative structure of forging blades, for example, for BLISK. In addition, the choice of materials more strongly to the needs or purpose of the respective blade element be adapted, for example, because different powder compositions can be forged together.
  • the respective blade element can be subjected to further processing steps following the kinetic cold gas compacting.
  • the blade element may be subjected to a heat treatment, etc.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un procédé pour concevoir, réparer et/ou construire une pièce, en particulier un élément d'aube de turbine à gaz. Ce procédé comprend les étapes consistant à préparer une pièce et à construire au moins une partie de la pièce par compactage cinétique à froid.
PCT/DE2011/001727 2010-10-13 2011-09-12 Pièce et procédé pour concevoir, réparer et/ou construire une pièce de ce type Ceased WO2012051978A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102010048336.2 2010-10-13
DE102010048336A DE102010048336A1 (de) 2010-10-13 2010-10-13 Bauteil und Verfahren zum Ausbilden, Reparieren und/oder Aufbauen eines derartigen Bauteils

Publications (2)

Publication Number Publication Date
WO2012051978A2 true WO2012051978A2 (fr) 2012-04-26
WO2012051978A3 WO2012051978A3 (fr) 2012-06-28

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2011/001727 Ceased WO2012051978A2 (fr) 2010-10-13 2011-09-12 Pièce et procédé pour concevoir, réparer et/ou construire une pièce de ce type

Country Status (2)

Country Link
DE (1) DE102010048336A1 (fr)
WO (1) WO2012051978A2 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015203234B4 (de) * 2015-02-24 2018-04-26 MTU Aero Engines AG Verfahren zur Herstellung eines Bauteils, nämlich einens Gehäuses einer Gasturbine und das entsprechende Bauteil
DE102015207017B4 (de) * 2015-04-17 2017-04-27 Hermle Maschinenbau Gmbh Verfahren zur Herstellung von gedeckelten Laufrädern
US20170114466A1 (en) * 2015-10-21 2017-04-27 General Electric Company Article, turbine component and airfoil treatment methods
DE102024204578A1 (de) 2024-05-17 2025-11-20 Siemens Energy Global GmbH & Co. KG Verfahren zur Reparatur von Gasturbinenkomponenten

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008003295A2 (fr) 2006-07-07 2008-01-10 Mtu Aero Engines Gmbh Procédé de réparation et/ou de remplacement d'éléments individuels d'une pièce d'une turbine à gaz

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DE59607692D1 (de) * 1995-12-08 2001-10-18 Siemens Ag Verfahren zur rissbeseitigung bei einem metallischen bauteil, insbesondere einer turbinenschaufel, sowie turbinenschaufel
US6491208B2 (en) * 2000-12-05 2002-12-10 Siemens Westinghouse Power Corporation Cold spray repair process
US6905728B1 (en) * 2004-03-22 2005-06-14 Honeywell International, Inc. Cold gas-dynamic spray repair on gas turbine engine components
US20060045785A1 (en) * 2004-08-30 2006-03-02 Yiping Hu Method for repairing titanium alloy components
DE102006009751A1 (de) * 2006-03-02 2007-09-06 Praxair Surface Technologies Gmbh Verfahren zur Reparatur und Wiederherstellung von dynamisch beanspruchten Komponenten aus Aluminiumlegierungen für luftfahrtechnische Anwendungen
EP1867749A1 (fr) * 2006-06-12 2007-12-19 Siemens Aktiengesellschaft Procédé de revêtement d'un matériau à une pièce
EP1903127A1 (fr) * 2006-09-21 2008-03-26 Siemens Aktiengesellschaft Procédé de fabrication des composants par pulvérisation de gaz à froid et composant de turbine
DE102007046386B3 (de) * 2007-09-21 2008-10-02 Siemens Ag Verfahren zur Reparatur eines Bauteils durch Beschichten
DE102007056451A1 (de) * 2007-11-23 2009-05-28 Mtu Aero Engines Gmbh Verfahren zur Reparatur eines Gasturbinenbauteils
US20090249603A1 (en) * 2008-04-08 2009-10-08 Chris Vargas Cold deposition repair of casting porosity
DE102008052030B4 (de) * 2008-10-16 2011-06-16 Mtu Aero Engines Gmbh Verfahren zum Verbinden wenigstens einer Turbinenschaufel mit einer Turbinenscheibe oder einem Turbinenring

Patent Citations (1)

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Publication number Priority date Publication date Assignee Title
WO2008003295A2 (fr) 2006-07-07 2008-01-10 Mtu Aero Engines Gmbh Procédé de réparation et/ou de remplacement d'éléments individuels d'une pièce d'une turbine à gaz

Also Published As

Publication number Publication date
DE102010048336A1 (de) 2012-04-19
WO2012051978A3 (fr) 2012-06-28

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