EP0451512B1 - Procédé pour le revêtement d'aubes - Google Patents

Procédé pour le revêtement d'aubes Download PDF

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Publication number
EP0451512B1
EP0451512B1 EP91103660A EP91103660A EP0451512B1 EP 0451512 B1 EP0451512 B1 EP 0451512B1 EP 91103660 A EP91103660 A EP 91103660A EP 91103660 A EP91103660 A EP 91103660A EP 0451512 B1 EP0451512 B1 EP 0451512B1
Authority
EP
European Patent Office
Prior art keywords
blades
protective coating
process according
coating
flame spraying
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
EP91103660A
Other languages
German (de)
English (en)
Other versions
EP0451512A1 (fr
Inventor
Tibor Koromzay
Sejko Kolev
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.)
ABB Asea Brown Boveri Ltd
Original Assignee
ABB Asea Brown Boveri Ltd
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 ABB Asea Brown Boveri Ltd filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0451512A1 publication Critical patent/EP0451512A1/fr
Application granted granted Critical
Publication of EP0451512B1 publication Critical patent/EP0451512B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/002—Cleaning of turbomachines
    • 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
    • C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
    • 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
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • C23C4/067—Metallic material containing free particles of non-metal elements, e.g. carbon, silicon, boron, phosphorus or arsenic
    • 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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades

Definitions

  • the present invention relates to a method for coating blades according to the preamble of claim 1.
  • the air drawn in by the compressor also contains water vapor and solid and gaseous impurities. These have a negative impact due to erosion, pollution and corrosion.
  • the deposits on the blades sometimes have a considerable concentration of corrosive components such as NaCl and KCl.
  • the salts also lead to increased pitting corrosion in the compressor area and to a complex chemical reduction in the strength of the blade material.
  • water vapor concentration occurs in the compressor inlet area, which explains the increased corrosion attack of the front rows of blades.
  • blades of rotating thermal machines are often provided with protective layers. This is used both for steam and gas turbine blades and for compressor blades.
  • the main thing is to increase resistance to corrosion and oxidizing attacks as well as erosion and wear (wear and tear). If, despite the surface treatment, the blades show damage whose degree could jeopardize operational safety, you proceed to Removal of the blades: either they are replaced by new ones or reconditioned and reinstalled. This removal and installation is associated with relatively high costs and time. Furthermore, the actual state of the blading is only visible after a relatively long time, ie after pre-cleaning, so the decision as to whether or not reconditioning of the blades is feasible or already necessary can only be made much later. The disadvantages of this method are the great loss of time, the higher operating costs of the system, higher costs for revisions and the uncertainty about the question of the reconditionability of the blades.
  • This sintering or baking process during coating consists of a heat treatment at approx. 350 degrees Celsius over a holding time of approx. 10-12 hours.
  • quite large plants with a specific geometric configuration must be provided for carrying out the individual process steps, just think that during the sintering process the entire bladed part of the rotor must be enclosed by a furnace cover.
  • the invention seeks to remedy this.
  • the object of the invention is to propose a more rational method for reconditioning the blades in a method of the type mentioned at the outset in terms of the times required and the costs involved.
  • the object of the invention is also to maximize the life of the coating by means of suitable methods and protective layers. This object is achieved with the method according to the characterizing part of claim 1.
  • the bladed rotor does not have to be lifted out of its storage in the stator for the first process of reconditioning: the cleaning or protective layer removal can be done before the machine, ie the compressor, is actually switched off, i.e. during a Final phase of the operation ("on line"). A uniform loading of the blades to be treated is thus achieved, the efficiency of this cleaning process thus achieved, which ensures extensive removal of any protective layer that may be present, making an immediate decision about the reconditionability of the blades possible. This decision can be made after the machine has been switched off and the upper part of the stator has been removed.
  • Another important advantage of the invention is that using a high-speed flame spraying method, the blades pretreated in the installed state are given a corresponding protective layer, preferably based on Si and Al, locally and as required, this coating method without heat treatment over long periods and can be carried out without the help of special additional systems.
  • the service life of this type of coating is much longer than that of the layers currently used for this so-called complete coating. Since the pretreatment of the blades or the post-treatment after spraying on the protective layer for the life of the coating is of great importance, immediate corrections can be made, depending on the identified need. What is created in a very short time with low reconditioning costs by means of a process of high environmental compatibility is top-quality blading, which guarantees the operational safety of the system over a longer period of time.
  • FIG. 1 shows a conventional gas turbine group 11, consisting essentially of a compressor part 11a, a combustion chamber 11b and a turbine part 11c.
  • a distinction must be made as to whether they were uncoated or coated in their original condition. Irrespective of this requirement, the blades are cleaned for the first time before the machine, ie the compressor, is switched off. In the case of coated blades, this cleaning is preferably based on erosion by means of a soft jet granulate. Of course, the cleaning of uncoated blades can only be carried out using an aqueous solvent, for example trichlorethylene. Through a centrally placed three-jet nozzle 1 (see also Fig.
  • the circuit relating to the multi-jet nozzle 1 consists of a ball valve 2, which is connected downstream of a mixing chamber 3 in the direction of flow of the cleaning agent and serves to regulate the quantity.
  • the pressure in this mixing chamber 3 is represented by a manometer 7.
  • a container 4 is provided upstream of the mixing chamber 3, in which, for example, a granulate is in stock, a sieve 5 and an inlet valve 6 each ensuring that the mixing chamber 3 is supplied with a homogeneous material.
  • the required pressure in the container 4 is provided via an air supply line 10, a pressure reducing valve 8 and a main valve 9 in the air line being further aids of the circuit. Appropriate precautions can also be used to treat turbine blading.
  • the blades are subjected to further cleaning or protective layer removal. This is done, as shown in FIGS. 3 and 4, by means of an oscillating, erosive bath 14.
  • the bladed rotor 11a and 11c is removed from the stator and placed on trestles 13a and 13b in such a way that a certain part of the blading immersed in the bath 14.
  • the individual are erosive by means of a vibration generator 15 Components of the bath 14 are excited to vibrate, whereupon the residual dirt or the residual protective layer on the blades is removed.
  • all blade types of a rotor of a gas turbine group can be treated with it.
  • a final cleaning is carried out according to FIG. 5 with an industrial glass blasting agent 18. This final cleaning is based on erosion removal by the means mentioned, which can consist of glass. A certain part of the blading is covered with a special capsule 16; with simultaneous suction 19 of the injected agent, cleaning is accomplished using one or more jet nozzles 17.
  • FIG. 6 shows one way in which the high speed flame spraying process can be carried out.
  • a sheath 16 accessible from the side is provided, which encircles a number of prepared blades.
  • the protective layer is applied to the blades by means of a spray nozzle 20, it being readily possible to guide the jet nozzle 20 manually.
  • a suction device 19 ensures that excess agent can be removed immediately from the area surrounding the blades.
  • the chemical structure of the above protective layers as well the application process (high-speed flame spraying process) also described above provides a less erosion-sensitive "sacrificial anode" layer, which actively protects the base material against corrosion.
  • the application process which is a high-energy coating process, provides well-adhering and erosion-resistant protective layers which have the desired electrical connection to the base material without further protective layer-specific aftertreatment.
  • the proposed protective layers can additionally be provided with a cover layer. This protective layer can be black, for example. Such a dirt-repellent cover layer enables ice to be more easily recognized on the blades by means of ice detectors.
  • the high-speed flame spraying process which runs at a particle speed of at least 300 m / s, represents an optimal interlocking of the coating with the base material of the blades. Even with a thicker protective layer, it is ensured that the coating does not flake off. This can be explained by the fact that when the powder particles impact, the high kinetic energy creates residual compressive stresses in the previously sprayed layer. The maximized resistance to erosion is due to the fact that the layers used here have a very high hardness.
  • the method proposed here results in the oxide content of the layer being lower than in the case of protective layers sprayed in air. This means that the layer is cleaner, which is why it oxidizes less quickly, with oxidation only occurring on the surface at most.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Plasma & Fusion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Physics & Mathematics (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Application Of Or Painting With Fluid Materials (AREA)
  • Coating Apparatus (AREA)

Claims (8)

  1. Procédé de revêtement des aubes d'une machine thermique tournante avec un compresseur, caractérisé en ce que, à l'état de fonctionnement de la machine thermique, les aubes sont soumises à une première opération de nettoyage au moyen d'un agent mélangé au courant d'air circulant vers le compresseur, en ce que les aubes sont, après ouverture de la machine à l'état stationnaire, soumises à au moins une opération de préparation pour l'étape ultérieure de revêtement, et en ce que les aubes sont, à l'état stationnaire, revêtues d'une couche de recouvrement au moyen d'un procédé de projection à la flamme à grande vitesse, qui projette les particules de la couche de protection avec une vitesse d'au moins 300 m/s sur la surface de la matière de base.
  2. Procédé suivant la revendication 1, caractérisé en ce que, pendant l'opération de préparation avant le dépôt de la couche de protection, les aubes sont traitées dans un bain érosif oscillant.
  3. Procédé suivant la revendication 1, caractérisé en ce que les aubes sont soumises, à l'état stationnaire après le dépôt de la couche de protection, à un post-traitement pour diminuer la rugosité de la surface et/ou pour déposer une couche de recouvrement.
  4. Procédé suivant la revendication 1, caractérisé en ce que la couche de protection déposée par le procédé de projection à la flamme à grande vitesse est composée de 6 - 15 % en poids de Si, le reste étant de l'aluminium.
  5. Procédé suivant la revendication 1, caractérisé en ce que la couche de protection déposée par le procédé de projection à la flamme à grande vitesse est composée d'aluminium.
  6. Procédé suivant la revendication 1, caractérisé en ce que la couche de protection déposée par le procédé de projection à la flamme à grande vitesse est composée de 80 % en poids de Al, de 5 - 15 % en poids de Si, le reste étant du Cu, Mn, Mg, Ni.
  7. Procédé suivant la revendication 1, caractérisé en ce que l'agent mélangé au courant d'air pour le nettoyage des aubes est composée d'un granulat en jet mou.
  8. Procédé suivant la revendication 3, caractérisé en ce que la couche de recouvrement est composée d'une laque réactive de polyuréthane à base de matière synthétique.
EP91103660A 1990-04-11 1991-03-11 Procédé pour le revêtement d'aubes Expired - Lifetime EP0451512B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH1237/90 1990-04-11
CH123790 1990-04-11

Publications (2)

Publication Number Publication Date
EP0451512A1 EP0451512A1 (fr) 1991-10-16
EP0451512B1 true EP0451512B1 (fr) 1993-08-04

Family

ID=4205685

Family Applications (1)

Application Number Title Priority Date Filing Date
EP91103660A Expired - Lifetime EP0451512B1 (fr) 1990-04-11 1991-03-11 Procédé pour le revêtement d'aubes

Country Status (9)

Country Link
EP (1) EP0451512B1 (fr)
JP (1) JP3027214B2 (fr)
CA (1) CA2039944C (fr)
DE (1) DE59100238D1 (fr)
DK (1) DK0451512T3 (fr)
ES (1) ES2044634T3 (fr)
PL (1) PL165873B1 (fr)
RU (1) RU2062303C1 (fr)
UA (1) UA27027A1 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH08193568A (ja) * 1995-01-13 1996-07-30 Hitachi Ltd 水力機械のランナ及びその製造方法
AT403059B (de) * 1995-10-04 1997-11-25 Engel Gmbh Maschbau Verfahren zur herstellung einer beschichtung auf der oberfläche von plastifizierschnecken für spritzgiessmaschinen
AT402943B (de) * 1995-10-04 1997-09-25 Engel Gmbh Maschbau Verfahren zur herstellung von verschleiss- und korrosionsgeschützten oberflächen auf plastifizierschnecken für spritzgiessmaschinen
DE102004001575A1 (de) 2004-01-10 2005-08-04 Mtu Aero Engines Gmbh Verfahren zur Herstellung von Hohlschaufeln sowie eines Rotors mit Hohlschaufeln
US8113787B2 (en) 2007-06-20 2012-02-14 Alstom Technology Ltd. Turbomachine blade with erosion and corrosion protective coating and method of manufacturing
WO2008116757A2 (fr) * 2007-03-27 2008-10-02 Alstom Technology Ltd Pale de turbomachine avec revêtement de protection contre l'érosion et la corrosion, et procédé de fabrication de cette dernière
EP2752559A1 (fr) * 2013-01-08 2014-07-09 Siemens Aktiengesellschaft Procédé de nettoyage d'un rotor d'une turbine à gaz à l'intérieur d'un boîtier
CN110420769B (zh) * 2019-08-02 2020-06-09 柳州联顺戴克雷汽车部件有限公司 一种具有调配功能的防起粒的喷涂设备

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2709569A (en) * 1948-08-28 1955-05-31 Thompson Prod Inc Impeller member and method of making same
US3010843A (en) * 1958-04-28 1961-11-28 Gen Motors Corp Abradable protective coating for compressor casings
FR2564350B1 (fr) * 1984-05-17 1987-11-20 Snecma Procede de reparation par diffusion

Also Published As

Publication number Publication date
DK0451512T3 (da) 1993-12-27
ES2044634T3 (es) 1994-01-01
PL289795A1 (en) 1991-12-02
RU2062303C1 (ru) 1996-06-20
DE59100238D1 (de) 1993-09-09
CA2039944C (fr) 2001-01-02
PL165873B1 (pl) 1995-02-28
UA27027A1 (uk) 2000-02-28
JPH04225865A (ja) 1992-08-14
JP3027214B2 (ja) 2000-03-27
EP0451512A1 (fr) 1991-10-16
CA2039944A1 (fr) 1991-10-12

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