EP1233081A1 - Procédé et dispositif pour le revêtement par plasma d'une aube de turbine - Google Patents

Procédé et dispositif pour le revêtement par plasma d'une aube de turbine Download PDF

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Publication number
EP1233081A1
EP1233081A1 EP01103457A EP01103457A EP1233081A1 EP 1233081 A1 EP1233081 A1 EP 1233081A1 EP 01103457 A EP01103457 A EP 01103457A EP 01103457 A EP01103457 A EP 01103457A EP 1233081 A1 EP1233081 A1 EP 1233081A1
Authority
EP
European Patent Office
Prior art keywords
axis
blade
turbine blade
coating
plasma
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Withdrawn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
EP01103457A
Other languages
German (de)
English (en)
Inventor
Claus Dr. Heuser
Gerhard Dr. Johner
Helge Reymann
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.)
Coatec & Co KG GmbH
Siemens AG
Siemens Corp
Original Assignee
Coatec & Co KG GmbH
Siemens AG
Siemens Corp
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 Coatec & Co KG GmbH, Siemens AG, Siemens Corp filed Critical Coatec & Co KG GmbH
Priority to EP01103457A priority Critical patent/EP1233081A1/fr
Priority to US10/467,939 priority patent/US20040146657A1/en
Priority to DE50204081T priority patent/DE50204081D1/de
Priority to JP2002570793A priority patent/JP2004526056A/ja
Priority to EP02722074A priority patent/EP1360342B1/fr
Priority to CA002438156A priority patent/CA2438156A1/fr
Priority to PCT/EP2002/001515 priority patent/WO2002070772A1/fr
Priority to CNA2005100729046A priority patent/CN1699615A/zh
Priority to CNB028049861A priority patent/CN1237197C/zh
Publication of EP1233081A1 publication Critical patent/EP1233081A1/fr
Withdrawn legal-status Critical Current

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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
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/134—Plasma spraying

Definitions

  • the invention relates to a method for plasma coating a turbine blade directed along a blade axis by means of thermal plasma spraying.
  • the invention relates also a coating device for implementation of the procedure.
  • a coating process for plasma coating a turbine blade emerges from EP 1 033 417 A1.
  • One of the possible coatings to be applied to the turbine blade consists of an MCrAlX alloy, M for one or more elements comprising iron, cobalt or nickel, Cr for chrome, Al for aluminum and X for one or more elements the group comprising yttrium, rhenium and the elements of rare earths.
  • This metallic layer is achieved by thermal spraying using the VPS (Vacuum Plasma Spraying) or LPPS (Low Pressure Plasma Spraying) applied the turbine blade.
  • the gas turbine blade exists in particular from a nickel or iron or cobalt-based superalloy.
  • the MCrAlX alloy serves in particular a corrosion and oxidation prevention.
  • the application One layer usually includes heat treatment on.
  • a process time of about 30 minutes during the post heat treatment the gas turbine blade has a process time of about Has 120 minutes.
  • the plasma coating is done with a plasma gun or a plasma torch. Such a Plasma torch is also often used before the coating process used to heat the component to be coated.
  • the Turbine blade to be coated is usually on one Turntable arranged while the plasma torch is on a multi-axis robot is arranged. During the coating the turbine blade is at a coating temperature kept from about 1100 ° K to 1200 ° K.
  • the object of the invention is to provide a method for Plasma coating of a turbine blade, in particular an improved quality of by thermal plasma spraying applied coating results.
  • Another task the invention is the specification of a coating device to carry out this procedure.
  • the object is directed to a method solved by specifying a process for plasma coating a turbine blade directed along a blade axis, with the at least three plasma torches for thermal Plasma spraying can be used simultaneously.
  • the invention is based on the knowledge that in the conventional Certain use of a single plasma torch Loss of quality for the coating of the turbine blade consequences.
  • it occurs on certain critical areas like the transition area between the airfoil and adjacent blade platforms to an undesirably high Layer thickness because the coating of the platform on the one hand and the leaf on the other hand in the border area to one after conventional coating method inevitable overlap and thus lead to an increased layer thickness.
  • Such pore formation leads to one increased corrosion of the coating actually protective base material.
  • the invention in a coating with only one Burner an unfavorable temperature control for the to be coated Component, since with only one burner only one insufficiently uniform heating of the component is possible.
  • the task directed at a coating device becomes solved according to the invention by specifying a coating device for coating a turbine blade by means of a Method according to one of the possibilities described above.
  • Figure 1 shows a coating device 1.
  • the coating device 1 has a coating chamber 3. With the pre-chamber 5 of the coating chamber 3 is vacuum-tight connected. In the coating chamber 3 is one along Blade axis 9 arranged turbine blade 11 arranged. The turbine blade 11 is on one in the coating chamber 3 arranged blade manipulator 13 arranged. Via an expansion chamber connected to the coating chamber 3 15 also carries a burner manipulator 17 into the coating chamber 3. A first plasma torch 19 and a second plasma torch 21 are on a torch carrier 25 arranged. A third plasma torch 23 is on the torch manipulator 17 arranged. The three plasma torches 19, 21, 23 are decoupled from each other and thus controllable independently of each other and agile.
  • Farther can be one of the particularly large turbine blades Plasma torch 19, 21, 23 for heating the turbine blade 11 are used, which means a targeted heat input exactly is achieved where it is needed, which in turn changes results in a qualitative improvement for the layer.
  • particularly large turbine blades for example on the order of a length of 1 m, a coating possible with sufficiently high quality the use of at least three plasma torches 19, 21, 23.
  • the use of the three plasma torches 19, 21, 23 also to an overall more constant layer thickness distribution on the turbine blade 11.
  • FIG. 2 shows a particularly simple construction type of installation of the three plasma torches 19, 21, 23.
  • the turbine blade 11 is therefore a gas turbine blade made of a nickel or cobalt base superalloy base 30. It has an airfoil 33 to which it is attached Blade tip a tip platform 31 and blade foot side a foot platform 35 borders. Between platforms 31, 35, The airfoil 33 has rounded regions 37, in which it especially to the overspray when using only one Plasma torches can come as described above.
  • the turbine blade 11 is attached to the blade manipulator 13 in such a way that they are in a direction of rotation by means of the blade manipulator 13 43 is rotatable about the blade axis 9.
  • a first plasma torch 19 sprays along a first spray direction 67 onto the turbine blade 11.
  • the first plasma torch 19 is about a first axis of rotation 66 rotatable in the direction of rotation 65.
  • a second Plasma torch 21 sprays along a second spray direction 63 on the turbine blade 11.
  • the second plasma torch 21 is along a second axis of rotation 62 in a direction of rotation 61 rotatable.
  • the first plasma torch 19 is along a direction parallel to the blade axis 9 in the foot area the turbine blade 11 arranged while the second Plasma torch 21 along this direction at the height of the Blade tip of the turbine blade 11 is arranged.
  • the first spray direction 67 forms with the second spray direction 63 an angle ⁇ that is greater than 90 °. In this configuration the first plasma torch 19 is used for a coating the tip platform 31, while the second plasma torch 21 serves to coat the foot platform 35.
  • a third is arranged on the side of the turbine blade 11 Plasma torch 23.
  • This third plasma torch 23 injects along a third spray direction 53 onto the turbine blade 11.
  • the third plasma torch 23 is along one Rotation axis 56 rotatable about the direction of rotation 55.
  • the turbine blade 11 Before coating the turbine blade 11 with a a coating material 81, preferably a MCrAlX oxidation-corrosion protection layer, the turbine blade 11 is heated. This happens in particularly evenly by all three plasma torches 19, 21, 23 at the same time. After reaching the desired temperature the coating material is applied, as described, the first plasma torch 19 and the second Plasma torches 21 serve to coat the platforms 31, 35, while a coating over the third plasma torch 23 of the airfoil 33 is made.
  • a coating material 81 preferably a MCrAlX oxidation-corrosion protection layer
  • FIG. 3 shows a modification of the coating device 1 from Figure 2, this modification the third plasma torch 23 concerns. This is now also in one direction 51 movable perpendicular to the plane E through the blade axis 9 and the third spray direction 53 is fixed. Furthermore, the third plasma torch 23 is also at a distance to the turbine blade 11 along a mobility the third spray direction 53 movably arranged. While the axis of rotation 56 of the third plasma torch 23 according to FIG Arrangement in Figure 2 aligned parallel to the blade axis 9 was, it is now along the spray direction 53 and thus directed perpendicular to the blade axis 9. The axis of rotation 56 lies in level E. As already in FIG.
  • FIG. 4 shows a common mobility of the first plasma torch 19 and the second plasma torch 21 by means of a drive unit 71, the one Carrier 72 for the first and second plasma torches 19, 21 in parallel moved to the blade axis 9.
  • a chain 73 moved parallel to the blade axis 9.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP01103457A 2001-02-14 2001-02-14 Procédé et dispositif pour le revêtement par plasma d'une aube de turbine Withdrawn EP1233081A1 (fr)

Priority Applications (9)

Application Number Priority Date Filing Date Title
EP01103457A EP1233081A1 (fr) 2001-02-14 2001-02-14 Procédé et dispositif pour le revêtement par plasma d'une aube de turbine
US10/467,939 US20040146657A1 (en) 2001-02-14 2002-02-13 Method for plasma coating a turbine blade and coating device
DE50204081T DE50204081D1 (de) 2001-02-14 2002-02-13 Verfahren zur plasmabeschichtung einer turbinenschaufel und beschichtungsvorrichtung
JP2002570793A JP2004526056A (ja) 2001-02-14 2002-02-13 タービン翼のプラズマ被覆法
EP02722074A EP1360342B1 (fr) 2001-02-14 2002-02-13 Procede et dispositif pour revetir de plasma une aube de turbine
CA002438156A CA2438156A1 (fr) 2001-02-14 2002-02-13 Procede et dispositif pour revetir de plasma une aube de turbine
PCT/EP2002/001515 WO2002070772A1 (fr) 2001-02-14 2002-02-13 Procede et dispositif pour revetir de plasma une aube de turbine
CNA2005100729046A CN1699615A (zh) 2001-02-14 2002-02-13 用于对透平叶片进行等离子喷镀的方法和喷镀装置
CNB028049861A CN1237197C (zh) 2001-02-14 2002-02-13 用于对透平叶片进行等离子喷镀的方法和喷镀装置

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP01103457A EP1233081A1 (fr) 2001-02-14 2001-02-14 Procédé et dispositif pour le revêtement par plasma d'une aube de turbine

Publications (1)

Publication Number Publication Date
EP1233081A1 true EP1233081A1 (fr) 2002-08-21

Family

ID=8176493

Family Applications (2)

Application Number Title Priority Date Filing Date
EP01103457A Withdrawn EP1233081A1 (fr) 2001-02-14 2001-02-14 Procédé et dispositif pour le revêtement par plasma d'une aube de turbine
EP02722074A Expired - Lifetime EP1360342B1 (fr) 2001-02-14 2002-02-13 Procede et dispositif pour revetir de plasma une aube de turbine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP02722074A Expired - Lifetime EP1360342B1 (fr) 2001-02-14 2002-02-13 Procede et dispositif pour revetir de plasma une aube de turbine

Country Status (7)

Country Link
US (1) US20040146657A1 (fr)
EP (2) EP1233081A1 (fr)
JP (1) JP2004526056A (fr)
CN (2) CN1237197C (fr)
CA (1) CA2438156A1 (fr)
DE (1) DE50204081D1 (fr)
WO (1) WO2002070772A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009144109A1 (fr) * 2008-05-29 2009-12-03 Siemens Aktiengesellschaft Procédé de projection à la flamme supersonique
EP2145974A1 (fr) * 2008-07-16 2010-01-20 Siemens Aktiengesellschaft Procédé destiné à l'injection de flammes à vitesse élevée
EP2444590A1 (fr) * 2010-10-19 2012-04-25 Siemens Aktiengesellschaft Procédé de revêtement de trous de refroidissement

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2520705C (fr) * 2004-11-02 2012-12-18 Sulzer Metco Ag Appareil de projection a chaud et egalement processus de projection a chaud
EP1816229B1 (fr) * 2006-01-31 2010-03-24 Siemens Aktiengesellschaft Dispositif et procédé de pulvériation thermique
US8191504B2 (en) * 2006-11-27 2012-06-05 United Technologies Corporation Coating apparatus and methods
JP5710159B2 (ja) * 2010-06-29 2015-04-30 株式会社東芝 溶射システムおよび溶射方法
CN102500531A (zh) * 2011-09-30 2012-06-20 库博汽车标准配件（昆山）有限公司 离子焰喷射装置
FR2991614B1 (fr) * 2012-06-06 2014-07-18 Snecma Procede de rechargement global de piece metallique pour turboreacteurs d'aeronefs, et outillage de protection globale pour la mise en œuvre du procede
US9126232B2 (en) * 2013-02-21 2015-09-08 Pratt & Whitney Canada Corp. Method of protecting a surface
US10294806B2 (en) 2013-03-15 2019-05-21 United Technologies Corporation Multiple coating configuration
KR101615911B1 (ko) 2014-05-30 2016-05-12 주식회사 아이스기술 회전체가 구비된 진공로를 이용하여 모재를 브레이징 코팅하는 방법
FR3092779B1 (fr) * 2019-02-19 2021-02-26 Safran Aircraft Engines Outillage amélioré pour le revêtement de léchettes
DE102020209085A1 (de) * 2020-07-21 2022-01-27 MTU Aero Engines AG Leitschaufelanordnung für eine strömungsmaschine

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3461268A (en) * 1967-01-24 1969-08-12 Inoue K Kinetic deposition of particulate materials
US4683148A (en) * 1986-05-05 1987-07-28 General Electric Company Method of producing high quality plasma spray deposits of complex geometry
DE4040893A1 (de) * 1989-12-26 1991-06-27 Gen Electric Verstaerkte mikrolaminierte metall-matrix-verbundstruktur

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4334495A (en) * 1978-07-11 1982-06-15 Trw Inc. Method and apparatus for use in making an object
US6120854A (en) * 1999-02-19 2000-09-19 Northrop Grumman Liquid crystal polymer coating process

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3461268A (en) * 1967-01-24 1969-08-12 Inoue K Kinetic deposition of particulate materials
US4683148A (en) * 1986-05-05 1987-07-28 General Electric Company Method of producing high quality plasma spray deposits of complex geometry
DE4040893A1 (de) * 1989-12-26 1991-06-27 Gen Electric Verstaerkte mikrolaminierte metall-matrix-verbundstruktur

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009144109A1 (fr) * 2008-05-29 2009-12-03 Siemens Aktiengesellschaft Procédé de projection à la flamme supersonique
EP2145974A1 (fr) * 2008-07-16 2010-01-20 Siemens Aktiengesellschaft Procédé destiné à l'injection de flammes à vitesse élevée
EP2444590A1 (fr) * 2010-10-19 2012-04-25 Siemens Aktiengesellschaft Procédé de revêtement de trous de refroidissement
US8920882B2 (en) 2010-10-19 2014-12-30 Siemens Aktiengesellschaft Setting the quantity of cooling air for a turbine blade or vane by controlled overspray

Also Published As

Publication number Publication date
WO2002070772A1 (fr) 2002-09-12
US20040146657A1 (en) 2004-07-29
EP1360342B1 (fr) 2005-08-31
CN1237197C (zh) 2006-01-18
EP1360342A1 (fr) 2003-11-12
CN1699615A (zh) 2005-11-23
CA2438156A1 (fr) 2002-09-12
JP2004526056A (ja) 2004-08-26
DE50204081D1 (de) 2005-10-06
CN1491292A (zh) 2004-04-21

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