EP1762303A1 - Procédé pour préparer des aubes de turbine en vue de leur revêtement par pulvérisation et support pour fixer de telles aubes - Google Patents

Procédé pour préparer des aubes de turbine en vue de leur revêtement par pulvérisation et support pour fixer de telles aubes Download PDF

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Publication number
EP1762303A1
EP1762303A1 EP05019698A EP05019698A EP1762303A1 EP 1762303 A1 EP1762303 A1 EP 1762303A1 EP 05019698 A EP05019698 A EP 05019698A EP 05019698 A EP05019698 A EP 05019698A EP 1762303 A1 EP1762303 A1 EP 1762303A1
Authority
EP
European Patent Office
Prior art keywords
holder
shielding
shield
blade
shielding 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.)
Granted
Application number
EP05019698A
Other languages
German (de)
English (en)
Other versions
EP1762303B1 (fr
Inventor
Thomas Beck
Francis-Jurjen Dr. Ladru
Benjamin Lippke
Marcus Mensing
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP05019698A priority Critical patent/EP1762303B1/fr
Priority to US11/518,554 priority patent/US7717058B2/en
Publication of EP1762303A1 publication Critical patent/EP1762303A1/fr
Application granted granted Critical
Publication of EP1762303B1 publication Critical patent/EP1762303B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/01—Selective coating, e.g. pattern coating, without pre-treatment of the material to be coated
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
    • B05B12/00—Arrangements for controlling delivery; Arrangements for controlling the spray area
    • B05B12/16—Arrangements for controlling delivery; Arrangements for controlling the spray area for controlling the spray area
    • B05B12/20—Masking elements, i.e. elements defining uncoated areas on an object to be coated

Definitions

  • the invention relates to a method for the preparation of turbine blades for the spray coating of their operating area of the flowing medium in the blade area in a spray coating apparatus in which the turbine blade is used with its blade root in a cavity of a holder such that it adjoins the adjoining the blade root Blade region protrudes from an opening of the cavity to form a gap between the opening edge and the turbine blade, and wherein the gap is bridged by a fixed to the holder shield.
  • the invention further relates to a holder for fixing a turbine blade in a spray coating apparatus, with at least one opening having cavity for receiving the turbine blade such that the turbine blade is inserted with a blade root in the cavity and with the adjoining the blade root, in Operation projects from the medium flowing through the blade area protruding from the opening of the cavity to form a gap between the opening edge and turbine blade, wherein in the region of the opening a shield for bridging the gap is provided.
  • Highly stressed workpieces such as turbine blades, for example turbines, in particular gas turbines, such as guide vanes and rotor blades, are coated to improve their temperature and / or abrasion resistance with suitable metals, metal alloys or ceramics.
  • the coating is done by means of a spray coating device in which the turbine blade is spray-coated.
  • spray coating methods are atmospheric plasma spraying (APS). and High Speed Oxygen Fuel Spraying (HVOF).
  • the holder has a cavity with an opening into which the turbine blade is used with its blade root, so that it protrudes with the blade portion to be coated from the opening of the cavity.
  • the cavity may additionally have a connection to a compressed air source from which compressed air can be injected into the cavity for cooling during the coating process.
  • the invention has for its object to provide a method of the type mentioned above and a suitable holder in such a way that the overspray of parts of the turbine blades is avoided, which should remain uncoated in accordance with specifications.
  • the object is achieved according to the invention in that a shielding layer made of a plastic that is resistant to spray coating is used for the shielding, the shielding layer being arranged such that it reaches to the boundary between blade root and shovel area.
  • the basic idea of the invention is therefore to provide a temperature-resistant plastic material between the turbine blade and the opening of the holder, in such a way that the part of the turbine blade which is not to be coated is completely covered, ie only the turbine surfaces remain free. In this way, an overspray of parts of the workpiece is avoided, which should remain layer-free, and it can on regrinding (overspray grinding) is dispensed with. Due to the use of the plastic material, there is no or at most limited adhesion of the material used for the spray coating, so that spalling of coating material when removing the turbine blade from the holder can be avoided.
  • the shielding is formed solely by the shielding layer, i. H. the use of shielding is omitted in this embodiment.
  • the shield is formed using at least one shielding plate on which the shielding layer is mounted on the workpiece side. In both cases, a flexible shielding tape can be used for the shielding layer.
  • the shielding band can be fastened to the shielding plate (s), preferably in such a way that the shielding band protrudes beyond the shielding plate (s), so that a step transition is also created to that extent.
  • the shielding layer is sprayed onto the shielding plate and then forms a coating.
  • the material for the shielding layer those which are heat-resistant so as to be resistant to spray coating should be used, and which are anti-adhesive, so that the coating material used in the spray-coating does not adhere to the shielding layer.
  • plastics such as PTFE. They avoid chipping during removal after the coating process. But other plastic materials are operational, provided they are similar or equal temperature resistant and anti-adhesive as PTFE.
  • the shielding layer is brought to bear against the turbine blade. This not only avoids overspray of non-coated areas, but also has an advantageous effect on the cooling of the turbine blade, since the injected cooling air is better used due to the sealing effect of the plastic material.
  • the shield should be placed so that it projects beyond the opening of the bracket.
  • the shield can be clamped to the bracket similar to the previously used Einsteckbleche.
  • a shielding layer made of a plastic which is resistant to spray coating is provided for the shield, the shielding layer being arranged such that it engages with the turbine blade inserted the boundary between blade root and blade area is sufficient.
  • the invention further provides a spray coating apparatus for spray coating workpieces, wherein the holder is formed as described above.
  • the holders 1 shown in FIGS. 1 to 3 each have a pot-like hollow body 2 which has an opening delimited at the top by an opening edge 3.
  • the hollow body 2 encloses a cavity 4, in which from above vertically a turbine blade 5 is inserted such that its blade root 6 is located substantially within the cavity 4 and there resting on a base 7, while the turbine blade 5 shown with its shortened During operation of the turbine provided therewith, the blade area 8, which is acted upon by the medium flowing through, extends outside the holder 1.
  • the arrow A indicates that the turbine blade 5 is cooled during the coating process with compressed air.
  • the holder 1 is intended to be used in a spray coating device, so that there the blade area 8 - this includes the top of the blade root 6 - is provided with a metal coating which is applied by plasma spraying. So that the coating remains limited to this and parts of the blade root 6 are not coated, the holders 1 have the blades 6 enclosing shields 9, 10, 11, which shield the part of the blade root 6 protruding from the hollow body 2 in such a way that the coating is applied the blade area 8 remains limited.
  • the shields 9, 10, 11 are formed differently.
  • the shielding 9 consists of shielding plates 12, 13 and a shielding band 14 fastened to the inside of the shielding plates 12, 13.
  • the shielding plates 12, 13 are clamped on the inside of the hollow body 2 by means of clamps 15, 16.
  • the shielding tape 14 protrudes upward beyond the shielding plates 12, 13 so far that it extends to the upper edge of the blade root 6 and abuts against its side faces. In this way, the distance between the blade root 6 and Bridged inside the hollow body 2. At the same time prevents parts of the blade root 6 are sprayed below the upper edge during coating.
  • the shielding 10 likewise has shielding plates 17, 18, which are provided on the inside with a shielding band 19.
  • the arrangement of the shielding band 19 is the same as in the exemplary embodiment according to FIG. 1. The only difference is that the shielding plates 17, 18 are extended so far upwards that their upper end sides lie flush with the upper end sides of the shielding band 19.
  • shielding plates are dispensed with.
  • the gap between the hollow body 2 and the turbine blade 5 is here bridged solely by a shielding 20, which rests in the lower region on the inside of the hollow body 2 and is clamped there by means of brackets 21, 22 and which rests in the upper region on the outside of the blade root 6.
  • the shielding tape 20 covers the blade root 6 up to its upper edge, so that it is ensured that only the blade area 8 are coated during the coating process.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Details Or Accessories Of Spraying Plant Or Apparatus (AREA)
EP05019698A 2005-09-09 2005-09-09 Procédé pour préparer des aubes de turbine en vue de leur revêtement par pulvérisation et support pour fixer de telles aubes Not-in-force EP1762303B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP05019698A EP1762303B1 (fr) 2005-09-09 2005-09-09 Procédé pour préparer des aubes de turbine en vue de leur revêtement par pulvérisation et support pour fixer de telles aubes
US11/518,554 US7717058B2 (en) 2005-09-09 2006-09-08 Method of preparing turbine blades for spray coating and mounting for fixing such a turbine blade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP05019698A EP1762303B1 (fr) 2005-09-09 2005-09-09 Procédé pour préparer des aubes de turbine en vue de leur revêtement par pulvérisation et support pour fixer de telles aubes

Publications (2)

Publication Number Publication Date
EP1762303A1 true EP1762303A1 (fr) 2007-03-14
EP1762303B1 EP1762303B1 (fr) 2012-10-17

Family

ID=35717712

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05019698A Not-in-force EP1762303B1 (fr) 2005-09-09 2005-09-09 Procédé pour préparer des aubes de turbine en vue de leur revêtement par pulvérisation et support pour fixer de telles aubes

Country Status (2)

Country Link
US (1) US7717058B2 (fr)
EP (1) EP1762303B1 (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1980366A1 (fr) * 2007-04-12 2008-10-15 Siemens Aktiengesellschaft Concept d'installation et de dispositif pour une installation de grenaillage destinée à la solidification de turbines de gaz de pieds d'aubes mobiles
EP2055800A1 (fr) * 2007-11-05 2009-05-06 Siemens Aktiengesellschaft Dispositif de support de composant destiné à l'utilisation dans une installation de revêtement et procédé de revêtement d'un composant
WO2009143817A1 (fr) * 2008-05-28 2009-12-03 Mtu Aero Engines Gmbh Cache et procédé de revêtement de composants
EP2181775A1 (fr) * 2008-11-04 2010-05-05 Siemens Aktiengesellschaft Fixation pour grands composants ayant une protection contre la projection
EP2309016A1 (fr) * 2009-10-06 2011-04-13 Siemens Aktiengesellschaft Procédé et agencement pour processus de revêtement à pulvérisation
CN106493642A (zh) * 2016-12-28 2017-03-15 无锡透平叶片有限公司 用于叶片叶根工作面喷丸和喷涂处理的支撑定位装置
EP2596871A3 (fr) * 2011-11-28 2017-07-05 United Technologies Corporation Régulation de température passive de revêtement de rotor HPC
WO2019057455A1 (fr) * 2017-09-20 2019-03-28 Siemens Aktiengesellschaft Orientation et fixation d'une pièce pour un usinage ultérieur au moyen d'un procédé de fabrication additive
DE102018217280A1 (de) * 2018-10-10 2020-04-16 Siemens Aktiengesellschaft Turbinenschaufelhalterung ohne Brückenbildung und Verfahren
EP3877094A4 (fr) * 2018-11-07 2022-08-24 Orizon Aerostuctures, LLC Systèmes, dispositifs et procédés à utiliser avec des pièces aérospatiales

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8967078B2 (en) * 2009-08-27 2015-03-03 United Technologies Corporation Abrasive finish mask and method of polishing a component
EP2359940A1 (fr) * 2010-02-12 2011-08-24 Siemens Aktiengesellschaft Dispositif et procédé de protection contre les excès de projection
FR2959528B1 (fr) * 2010-04-29 2012-06-08 Snecma Masque amovible pour une plate-forme d'aube ou de secteur de distributeur de turbomachine
DE102013224568A1 (de) * 2013-11-29 2015-06-03 Siemens Aktiengesellschaft Verfahren zur Erzeugung einer Fase, Bauteil mit Fase und Vorrichtung
DE102014204117A1 (de) 2014-03-06 2015-10-15 MTU Aero Engines AG Verfahren und Vorrichtung zum partiellen Abdecken eines Bauteilbereichs eines Bauteils
CN106756818B (zh) * 2016-11-30 2019-03-15 中航动力股份有限公司 一种用于涡轮导向叶片可变角度涂覆涂层的保护装置及方法

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4271005A (en) * 1979-12-03 1981-06-02 United Technologies Corporation Workpiece support apparatus for use with cathode sputtering devices
US5665217A (en) * 1993-10-15 1997-09-09 United Technologies Corporation Method for abrasive tipping of integrally bladed rotors
US6485655B1 (en) * 2001-08-02 2002-11-26 General Electric Company Method and apparatus for retaining an internal coating during article repair
EP1388592A1 (fr) * 2002-07-31 2004-02-11 METAPLAS IONON Oberflächenveredelungstechnik GmbH Procédé et installation d'isolement d'une zone superficielle d'une pièce
DE69815644T2 (de) 1997-12-19 2004-03-25 United Technologies Corp. (N.D.Ges.D. Staates Delaware), Hartford Schild und Verfahren zum Schützen der Oberfläche eines Werkstückes mit einem Flügelprofil
EP1537950A1 (fr) * 2003-12-04 2005-06-08 Snecma Moteurs Masque de protection pour le traitement de surface d'aubes de turbomachines

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5867762A (en) * 1994-05-26 1999-02-02 Rafferty; Kevin Masking tape
US6544460B2 (en) * 1998-11-20 2003-04-08 United Technologies Corporation Method and fixture for disposing filler material in an article
US6863927B2 (en) * 2002-09-27 2005-03-08 General Electric Aviation Service Operation Ptd. Ltd. Method for vapor phase aluminiding of a gas turbine blade partially masked with a masking enclosure

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4271005A (en) * 1979-12-03 1981-06-02 United Technologies Corporation Workpiece support apparatus for use with cathode sputtering devices
US5665217A (en) * 1993-10-15 1997-09-09 United Technologies Corporation Method for abrasive tipping of integrally bladed rotors
DE69815644T2 (de) 1997-12-19 2004-03-25 United Technologies Corp. (N.D.Ges.D. Staates Delaware), Hartford Schild und Verfahren zum Schützen der Oberfläche eines Werkstückes mit einem Flügelprofil
US6485655B1 (en) * 2001-08-02 2002-11-26 General Electric Company Method and apparatus for retaining an internal coating during article repair
EP1388592A1 (fr) * 2002-07-31 2004-02-11 METAPLAS IONON Oberflächenveredelungstechnik GmbH Procédé et installation d'isolement d'une zone superficielle d'une pièce
EP1537950A1 (fr) * 2003-12-04 2005-06-08 Snecma Moteurs Masque de protection pour le traitement de surface d'aubes de turbomachines

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1980366A1 (fr) * 2007-04-12 2008-10-15 Siemens Aktiengesellschaft Concept d'installation et de dispositif pour une installation de grenaillage destinée à la solidification de turbines de gaz de pieds d'aubes mobiles
EP2055800A1 (fr) * 2007-11-05 2009-05-06 Siemens Aktiengesellschaft Dispositif de support de composant destiné à l'utilisation dans une installation de revêtement et procédé de revêtement d'un composant
WO2009143817A1 (fr) * 2008-05-28 2009-12-03 Mtu Aero Engines Gmbh Cache et procédé de revêtement de composants
US9694568B2 (en) 2008-05-28 2017-07-04 MTU Aero Engines AG Method for coating components
EP2181775A1 (fr) * 2008-11-04 2010-05-05 Siemens Aktiengesellschaft Fixation pour grands composants ayant une protection contre la projection
CN102031476B (zh) * 2009-10-06 2015-08-19 西门子公司 用于喷涂工艺的方法及装置
CN102031476A (zh) * 2009-10-06 2011-04-27 西门子公司 用于喷涂工艺的方法及装置
EP2309016A1 (fr) * 2009-10-06 2011-04-13 Siemens Aktiengesellschaft Procédé et agencement pour processus de revêtement à pulvérisation
EP2596871A3 (fr) * 2011-11-28 2017-07-05 United Technologies Corporation Régulation de température passive de revêtement de rotor HPC
CN106493642A (zh) * 2016-12-28 2017-03-15 无锡透平叶片有限公司 用于叶片叶根工作面喷丸和喷涂处理的支撑定位装置
WO2019057455A1 (fr) * 2017-09-20 2019-03-28 Siemens Aktiengesellschaft Orientation et fixation d'une pièce pour un usinage ultérieur au moyen d'un procédé de fabrication additive
DE102018217280A1 (de) * 2018-10-10 2020-04-16 Siemens Aktiengesellschaft Turbinenschaufelhalterung ohne Brückenbildung und Verfahren
EP3877094A4 (fr) * 2018-11-07 2022-08-24 Orizon Aerostuctures, LLC Systèmes, dispositifs et procédés à utiliser avec des pièces aérospatiales
US11970290B2 (en) 2018-11-07 2024-04-30 Orizon Aerostructures, Llc Systems, devices, and methods for use with aerospace parts

Also Published As

Publication number Publication date
EP1762303B1 (fr) 2012-10-17
US7717058B2 (en) 2010-05-18
US20070110910A1 (en) 2007-05-17

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