EP1360342B1 - Procede et dispositif pour revetir de plasma une aube de turbine - Google Patents

Procede et dispositif pour revetir de plasma une aube de turbine Download PDF

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Publication number
EP1360342B1
EP1360342B1 EP02722074A EP02722074A EP1360342B1 EP 1360342 B1 EP1360342 B1 EP 1360342B1 EP 02722074 A EP02722074 A EP 02722074A EP 02722074 A EP02722074 A EP 02722074A EP 1360342 B1 EP1360342 B1 EP 1360342B1
Authority
EP
European Patent Office
Prior art keywords
blade
axis
coating
vane
turbine blade
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.)
Expired - Lifetime
Application number
EP02722074A
Other languages
German (de)
English (en)
Other versions
EP1360342A1 (fr
Inventor
Helge Reymann
Gerhard Johner
Claus Heuser
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
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 EP02722074A priority Critical patent/EP1360342B1/fr
Publication of EP1360342A1 publication Critical patent/EP1360342A1/fr
Application granted granted Critical
Publication of EP1360342B1 publication Critical patent/EP1360342B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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 process 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 carrying out of the procedure.
  • a coating process for plasma coating a turbine blade is apparent from EP 1 033 417 A1.
  • One of the possible, applied to the turbine blade coatings consists of an MCrAlX alloy, where M stands for a or several elements comprising iron, cobalt or nickel, Cr for chromium, Al for aluminum and X for one or more elements the group comprising yttrium, rhenium as well as the elements the rare earths stand.
  • This metallic layer is obtained by thermal spraying with the method VPS (Vacuum Plasma Spraying) or LPPS (Low Pressure Plasma Spraying) the turbine blade applied.
  • the gas turbine blade is made in particular of a nickel or iron or cobalt base superalloy.
  • the MCrAlX alloy is used in particular a corrosion and oxidation inhibition.
  • a layer is usually followed by a heat post-treatment at.
  • a process time of about 30 minutes while the postheat treatment the gas turbine blade a process duration 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 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 on one multi-axis robot is arranged. During the coating the turbine blade is at a coating temperature held from about 1100 ° K to 1200 ° K.
  • U.S. Patent 4,683,148 discloses the use of two Plasma torches.
  • DE 40 40 893 A1 discloses that more than two burners can be used to produce different, surprisingly advantageous structures by the development of vortex-like mixed microstructure. To what extent three burners can be controlled, about it no indications are given. The two or more burners are used to irradiate one and the same area with streams of particles containing different materials.
  • the object of the invention is to specify a method for Plasma coating of a turbine blade, in particular an improved quality of thermal plasma spraying applied coating has resulted. Further task
  • the invention is the specification of a coating device to carry out this process.
  • the object directed to a coating apparatus is 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.
  • FIG. 1 shows a coating device 1.
  • the coating device 1 has a coating chamber 3. With the coating chamber 3 is a pre-chamber 5 vacuum-tight connected. In the coating chamber 3 is one along a Blade axis 9 directed turbine blade 11 is arranged. The turbine blade 11 is on a in the coating chamber 3 leading blade manipulator 13 arranged. Via an expansion chamber connected to the coating chamber 3 15 also performs a burner manipulator 17 in the coating chamber 3. A first plasma torch 19 and a second plasma torch 21 are on a burner carrier 25th arranged. A third plasma torch 23 is on the burner manipulator 17 arranged. The three plasma torches 19, 21, 23 are decoupled from each other and thus independently controllable and movable.
  • FIG 2 shows a structurally particularly simple way of installation the three plasma torches 19, 21, 23.
  • the turbine blade 11 is thus a gas turbine blade made of a nickel or cobalt base superalloy base material 30. It has an airfoil 33, to which at her Blade tip a top platform 31 and blade foot side a foot platform 35 is adjacent. Between the platforms 31, 35, The blade 33 results in rounded areas 37, in which is especially the overspray when using only one Plasma torch can come as described above.
  • the turbine blade 11 is attached to the blade manipulator 13 so by means of the blade manipulator 13 in a direction of rotation 43 is rotatable about the blade axis 9. moreover it is in an axial direction 41 along the blade axis. 9 axially displaceable.
  • a first plasma torch 19 is injected along a first injection direction 67 on 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 injects along a second spray direction 63 on the turbine blade 11.
  • the second plasma torch 21st 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, while the second Plasma torch 21 along this direction at the height of Blade tip of the turbine blade 11 is arranged.
  • the first injection direction 67 forms with the second injection direction 63 an angle ⁇ , which is greater than 90 °. In this configuration serves the first plasma torch 19 of a coating the top platform 31, while the second plasma torch 21st a coating of the foot platform 35 is used.
  • a third Plasma torch 23 Approximately at the height of the intersection of the first injection direction 67th with the second injection direction 63 and on the opposite Side of the turbine blade 11 is arranged a third Plasma torch 23.
  • This third plasma torch 23 injects along a third spraying direction 53 onto the turbine blade 11.
  • the third plasma torch 23 is along a Rotation axis 56 rotatable about the rotational direction 55.
  • the turbine blade 11 Before coating the turbine blade 11 with a Coating 81, preferably an MCrAlX oxidation corrosion protection layer, the turbine blade 11 is heated. This happens in particularly uniform way through all three plasma torches 19, 21, 23 at the same time. After reaching the desired temperature the coating material is applied, wherein as described, the first plasma torch 19 and the second Plasma torches 21 serve the coating of the platforms 31, 35, while on the third plasma torch 23, a coating of the blade 33 is made.
  • a Coating 81 preferably an MCrAlX oxidation corrosion protection layer
  • the blade manipulator 13 is along the axial direction 41 movable, wherein the burner manipulator 17 synchronized can move so that from the burner 23 always the same Radius on the turbine blade 11 is coated.
  • the Burner 19, 21 are decoupled from this synchronous movement.
  • FIG. 3 shows a modification of the coating device 1 of Figure 2, this modification the third plasma torch 23 concerns. This is now in one direction 51 perpendicular to the plane E movable through the blade axis 9 and the third injection direction 53 is fixed. Furthermore, the third plasma torch 23 is also in its distance to the turbine blade 11 via a mobility along the third injection direction 53 movably arranged. While the axis of rotation 56 of the third plasma burner 23 according to the Arrangement in Figure 2 parallel to the blade axis. 9 was aligned, it is now along the spray direction 53 and thus directed perpendicular to the blade axis 9. The rotation axis 56 lies in the plane E.
  • FIG. 4 shows a joint mobility 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 torch 19, 21 in parallel moved to the blade axis 9.
  • a chain 73 moved parallel to the blade axis 9.

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  • 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)

Abstract

La présente invention concerne un procédé pour revêtir de plasma une aube de turbine (11). Selon ce procédé, au moins trois chalumeaux à plasma (19, 21, 23) sont utilisés en même temps, ce qui permet d'obtenir un revêtement (81) de particulièrement haute qualité, notamment constitué de McrAlX, sur un corps de base (30) composé d'un superalliage à base de nickel ou de cobalt. La présente invention concerne également un dispositif de revêtement (1) qui permet de mettre en oeuvre ledit procédé.

Claims (15)

  1. Procédé de revêtement au plasma d'une aube (11) de turbine dirigée le long d'un axe (9) d'aube, dans lequel on utilise simultanément au moins deux torches (19, 21, 23) à plasma pour la projection thermique au plasma,
       caractérisé    en ce que l'on utilise au moins trois torches (19, 21, 23) au plasma,
       en ce que l'on commande au moins deux des torches (19, 21, 23) au plasma indépendamment l'une de l'autre et
       en ce que l'on revêt par au moins deux torches (19, 21, 23) au plasma des parties de surface différentes de l'aube (11) de turbine.
  2. Procédé suivant la revendication 1,
       dans lequel l'une des torches (19, 21, 23) à plasma sert à réchauffer l'aube (11) de turbine.
  3. Procédé suivant la revendication 1,
       dans lequel on fait tourner l'aube (11) de turbine le long de l'axe (9) de l'aube.
  4. Procédé suivant la revendication 3,
       dans lequel on dirige une première des torches (19) dans une première direction (67) de projection sur l'aube (11) de la turbine et on la fait tourner par rapport à un premier axe (66) de rotation qui est perpendiculaire à sa première direction (67) de projection et
       qui est dans un plan (E) passant par cette première direction (67) de projection et l'axe (9) de l'aube.
  5. Procédé suivant la revendication 4,
       dans lequel on dirige une deuxième des torches (21) dans une deuxième direction (63) de projection sur l'aube (11) de turbine et on la fait tourner par rapport à un deuxième axe (62) de rotation, qui est perpendiculaire à cette deuxième direction (63) de projection et qui est dans un plan (E) passant par cette deuxième direction (63) de projection et par l'axe (9) de l'aube, la première direction (67) de projection et la deuxième direction (63) de projection faisant entre elles un angle (α) plus grand que 90°.
  6. Procédé suivant la revendication 5,
       dans lequel on déplace la première torche (19) et la deuxième torche (21) ensemble le long de l'axe (9) de l'aube.
  7. Procédé suivant la revendication 1,
       dans lequel on dirige une troisième des torches (23) dans une troisième direction (53) de projection sur l'aube (1) de turbine et on la fait tourner par rapport à un troisième axe (56) de rotation, qui est dans un plan (E) passant par cette troisième direction (53) de projection et par l'axe (9) de l'aube.
  8. Procédé suivant la revendication 7,
       dans lequel le troisième axe (56) de rotation est parallèle à l'axe (9) de l'aube.
  9. Procédé suivant la revendication 7,
       dans lequel le troisième axe (56) de rotation est perpendiculaire à l'axe (9) de l'aube.
  10. Procédé suivant la revendication 7,
       dans lequel on déplace la troisième torche (23) dans une direction (51) perpendiculaire au plan (E).
  11. Procédé suivant la revendication 7,
       dans lequel on déplace la troisième torche (23) le long de la troisième direction (53) de projection.
  12. Procédé suivant la revendication 7,
       dans lequel on déplace la troisième torche (23) parallèlement à l'axe (9) de l'aube.
  13. Procédé suivant la revendication 1,
       que l'on effectue sous vide.
  14. Procédé suivant la revendication 1,
       dans lequel on dépose par le revêtement au plasma une couche (81) de protection vis-à-vis de la corrosion et de l'oxydation en MCrAlX sur un corps (30) de base en alliage à base de nickel ou de cobalt de l'aube (11) de turbine.
  15. Dispositif (1) d'application d'un revêtement pour revêtir une aube (11) de turbine au moyen d'un procédé suivant l'une des revendications précédentes.
EP02722074A 2001-02-14 2002-02-13 Procede et dispositif pour revetir de plasma une aube de turbine Expired - Lifetime EP1360342B1 (fr)

Priority Applications (1)

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

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP01103457 2001-02-14
EP01103457A EP1233081A1 (fr) 2001-02-14 2001-02-14 Procédé et dispositif pour le revêtement par plasma d'une aube de turbine
EP02722074A EP1360342B1 (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

Publications (2)

Publication Number Publication Date
EP1360342A1 EP1360342A1 (fr) 2003-11-12
EP1360342B1 true EP1360342B1 (fr) 2005-08-31

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 Before (1)

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

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)

Families Citing this family (14)

* 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
EP2145974A1 (fr) * 2008-07-16 2010-01-20 Siemens Aktiengesellschaft Procédé destiné à l'injection de flammes à vitesse élevée
WO2009144109A1 (fr) * 2008-05-29 2009-12-03 Siemens Aktiengesellschaft Procédé de projection à la flamme supersonique
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
EP2444590B1 (fr) 2010-10-19 2014-08-06 Siemens Aktiengesellschaft Procédé de revêtement de trous de refroidissement
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

Family Cites Families (5)

* 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
US4334495A (en) * 1978-07-11 1982-06-15 Trw Inc. Method and apparatus for use in making an object
US4683148A (en) * 1986-05-05 1987-07-28 General Electric Company Method of producing high quality plasma spray deposits of complex geometry
CA2025302A1 (fr) * 1989-12-26 1991-06-27 General Electric Company Composite microlamine, renforce, a matrice metallique
US6120854A (en) * 1999-02-19 2000-09-19 Northrop Grumman Liquid crystal polymer coating process

Also Published As

Publication number Publication date
WO2002070772A1 (fr) 2002-09-12
US20040146657A1 (en) 2004-07-29
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
EP1233081A1 (fr) 2002-08-21

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