EP0702130B1 - Procédé pour la production d'un revêtement abrasif pour des constituants métalliques de propulseurs - Google Patents

Procédé pour la production d'un revêtement abrasif pour des constituants métalliques de propulseurs Download PDF

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Publication number
EP0702130B1
EP0702130B1 EP95113444A EP95113444A EP0702130B1 EP 0702130 B1 EP0702130 B1 EP 0702130B1 EP 95113444 A EP95113444 A EP 95113444A EP 95113444 A EP95113444 A EP 95113444A EP 0702130 B1 EP0702130 B1 EP 0702130B1
Authority
EP
European Patent Office
Prior art keywords
lining
component
coated
coating
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
EP95113444A
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German (de)
English (en)
Other versions
EP0702130A2 (fr
EP0702130A3 (fr
Inventor
Johannes Dr. Schröder
Thomas Dr. Uihlein
Hans Weber
Herbert Fischer
Erwin Fischhaber
Norbert Legrand
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 EP0702130A2 publication Critical patent/EP0702130A2/fr
Publication of EP0702130A3 publication Critical patent/EP0702130A3/fr
Application granted granted Critical
Publication of EP0702130B1 publication Critical patent/EP0702130B1/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • 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
    • 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
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F05D2230/90—Coating; Surface treatment
    • 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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24355—Continuous and nonuniform or irregular surface on layer or component [e.g., roofing, etc.]
    • Y10T428/24372—Particulate matter
    • Y10T428/24413—Metal or metal compound
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24802—Discontinuous or differential coating, impregnation or bond [e.g., artwork, printing, retouched photograph, etc.]
    • Y10T428/24926—Discontinuous or differential coating, impregnation or bond [e.g., artwork, printing, retouched photograph, etc.] including ceramic, glass, porcelain or quartz layer
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/25—Web or sheet containing structurally defined element or component and including a second component containing structurally defined particles
    • Y10T428/256—Heavy metal or aluminum or compound thereof
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/25—Web or sheet containing structurally defined element or component and including a second component containing structurally defined particles
    • Y10T428/256—Heavy metal or aluminum or compound thereof
    • Y10T428/257—Iron oxide or aluminum oxide

Definitions

  • the invention relates to a method for producing a brush coating for metallic Engine components according to the preamble of claim 1.
  • Rub-on pads that serve as run-in pads can be rubbed off and used for engine components as described in US-A-3 042 365, relatively complex.
  • In these Inlet linings for example, incorporate blade tips from moving blades that usually only the hardness of the base material of the blade or the blade blade coating have and no specific armor of the blade tip in the form have a tarnish.
  • the efficiency of compressors and turbines in depends to a large extent on the gap size between the stator and rotor, it reduces with increasing processing of the blade tips by rubbing processes.
  • This Processing of blade tips or sealing tips on labyrinth seals still reinforced if to increase the erosion and temperature resistance of Inlet coverings increase the strength and hardness of these coverings. In this Fall must be the blade tips or the sealing tips of labyrinth seals can also be armored with a tarnish.
  • Such a run-on covering for blade tips is known from US-A-4 169 020.
  • This The tarnish coating consists of a metallic matrix with anchored in the matrix Hard material particles. Due to the high thermal conductivity of the metallic matrix material there is a disadvantage that the component overheats, e.g. the tip of the blade during the brushing process. Another disadvantage is that the hard material particles have no alignment and arbitrarily arranged in the matrix are so that the incorporation of the run-in covering in the run-in covering in one disorderly scratching the tips of the hard material particles in the enema exhausted. This does not result in a targeted reduction in the frictional heat.
  • EP-A-0 292 250 describes engine seals, i.a. in labyrinth design, at those rotating parts with a wear-resistant, ceramic or metal carbide Coating are provided, wherein as ceramic materials oxides of Al, Ti, Cr, Zr and Mg can be called.
  • the coating is applied with a laser Provide a large number of depressions, which free spaces between cutting-like Form edges. This geometrically rather undefined, more random and difficult to reproduce Surface geometry (“random pattern”) certainly has no optimal cutting properties.
  • US-A-5 223 332 protects two-layer hard coatings on metallic substrates, especially on engine blades, with a metal carbide adhesive layer and a ceramic top layer.
  • the combination coating is supposed to particularly firm adhesion to the substrate and particularly high wear resistance be achieved.
  • oxides of Al, Ca, Mg, Cr, Ti, Si, Zr and Y and chromium carbide are proposed. It is pointed out that the ceramic top layer should have cutting properties, there are but no concrete information on realizing these properties.
  • EP-A-0 661 415 deals with structured hard coatings on rotors, in particular on gas turbine blade tips, with a labyrinth-like ceramic structure in a metallic matrix.
  • the cutting-like edges of the ceramic structure protrude from the matrix, so that there is a large number of defined free spaces for absorbing abrasion.
  • the ceramic structure is first produced separately, for example by thermal spraying, and adapted to the shape of the blade tip by cutting. When the blade is manufactured by fine or precision casting, the structure is cast into the blade metal. After machining the blade tip to size, the ceramic structure is partially exposed again by deep etching. Good geometrical abrasion properties and high wear resistance can be expected from this geometrically defined ceramic structure with possibly asymmetrical cutting edges.
  • the disadvantage is the complex integration into the component.
  • the object of the invention is to provide a method for producing a brush coating to create metallic engine components that rely on reliable, reproducible and inexpensive, geometrically defined, wear-resistant Have ceramic structures with cutable edges and free spaces manufactured.
  • the component surface is roughened for better adhesion of the ceramic spray layer or coated with an adhesive layer.
  • An advantage of this method is that achieves a cuttable profile of the component surface with one spraying process can be done without complex preparation of the component surface and without time-consuming post-processing or incorporation of a cuttable profile into a Ceramic layer.
  • the shadow mask preferably consists of a wire mesh, whereby the ratio between mesh size and wire diameter between 2 and 6 and the wire diameter is preferably between 0.1 and 0.5 mm.
  • shadow masks from a wire mesh have the additional advantage that they are made from round Covers (wires) exist and thus the formation of cutable edges promote, since only a fraction of the wire surface orthogonal to the spray jet and a high proportion of the sprayed material from the wire towards the component surface is distracted so that there is cutting edge-like accumulation of spray material comes on the component surface.
  • wire mesh as perforated masks is that the stitches form squares and consequently sharp edges occur at an angle of 90 ° to each other. These angles can be too sharp triangular tips, as known from fine files, can be optimized. To the wire mesh is arranged so that it is diagonal from the angled spray jet is hit. As a result, scale-like cutting tips arise.
  • the alignment the scale-like cutting tips can by the location of the wire mesh and by the choice of the angle of incidence of the spray jet can be changed. This enables the inventive method optimal alignment of the scale-like Cutting tips in relation to the relative movement between the component with or without running-in surface and the component with start-up surface.
  • Fig. 1 shows a schematic diagram of a profiled scraping 1 for metallic Engine components 2, which have a run-on coating 3 which is in contact with one another incorporated into an inlet lining 4 of a second component 14, the starting lining 3 consists of a thermally sprayed ceramic layer and the ceramic layer is profiled in such a way that it has cutable edges 5 - 9, with between the edges 5 - 9 free spaces 10 - 13 are arranged, which are the abrasion of the inlet covering 4 pick up and clear out.
  • This moves during the brushing process Component 2 relative to component 14 in the direction of arrow A.
  • the cutting edges 5 - 9 of the profiled brushing surface are relative movements 3 arranged.
  • Engine components 2 are preferably blade tips of rotor blades, sealing tips of labyrinth seals or from shovel cover tapes.
  • FIG. 2 shows a photographic enlargement of a blade tip armor according to the invention on a scale of about 5: 1.
  • the blade and blade root are clearly recognizable.
  • On the tip of the airfoil there is a profiled rubbing surface made of gaps which are bright in relation to the blade contour to discharge the abrasion of an inlet lining into which this starting lining is incorporated during the brushing process.
  • a scale-like structure can be clearly seen on the tip of the blade.
  • this scale-like structure consists of ZrO 2 7Y 2 O 3 thermally sprayed through a wire mesh mask.
  • the wire thickness of the wire mesh mask is 0.22 mm with a clear mesh width of 0.4 mm.
  • the tarnish was applied at a spray angle of 25 °.
  • the airfoil width is 25 mm and the sprayed cutting edges are a maximum of 70 ⁇ m high.
  • the run-in cover is rubbed to a minimum gap width during the rubbing process and a smooth cut surface of the run-in cover is thereby produced.
  • Fig. 3 shows a schematic diagram of a spraying method with shadow mask 15 for production a blade tip armor 16 according to the invention on a blade 17.
  • the metallic component surface 19 is roughened or coated before coating a rough metallic adhesive layer made of MCrAlY.
  • the wire mesh 18 has a smooth wire 20 with a diameter between 0.1 and 0.5 mm.
  • the clear mesh size is larger by a factor of 2 to 6.
  • a ceramic Material is passed through the shadow mask 15 onto the component surface to be coated at a spray angle of 10 to 30 ° to form cutting edges and free space thermally sprayed. To a greatly exaggerated degree is shown in Fig.
  • the spray material does not adhere to the wire surface, but instead bounces off the wire surface and piles up between the wires.
  • larger areas are kept free of spray material and an asymmetrical distribution of the spray material between the wires reached so that cutting edges 21-25 form in predetermined directions.
  • the cutting edge height can increase from 25 to 150 ⁇ m.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Plasma & Fusion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Laminated Bodies (AREA)
  • Paints Or Removers (AREA)

Claims (3)

  1. Procédé pour la fabrication d'un revêtement d'usure par effleurement pour des composants métalliques de mécanismes qui présentent un revêtement de démarrage, qui s'enfonce lors de l'effleurement dans un revêtement de rodage, qui est caractérisé par les étapes de procédé suivantes :
    a) placement d'un masque à trous (18) sur la surface (19) de la pièce à revêtir,
    b) pulvérisation thermique d'un matériau céramique à travers le masque à trous (18) sur la surface (19) de la pièce à revêtir selon un angle de pulvérisation de 10 à 30° pour former des arêtes (21-25) et des espaces libres.
  2. Procédé selon la revendication 1, caractérisé en ce qu'on pulvérise comme matériau céramique du ZrO27Y2O3, du Al2O3 ou des oxydes mixtes.
  3. Procédé selon la revendication 1 ou 2, caractérisé en ce que les composants (2) métalliques du mécanisme à revêtir sont la pointe d'une pale d'une aube mécanique (17), une pointe d'étanchéité d'une garniture à labyrinthe ou une pointe d'étanchéité sur une bande de recouvrement d'une pointe d'aube.
EP95113444A 1994-09-16 1995-08-26 Procédé pour la production d'un revêtement abrasif pour des constituants métalliques de propulseurs Expired - Lifetime EP0702130B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4432998A DE4432998C1 (de) 1994-09-16 1994-09-16 Anstreifbelag für metallische Triebwerkskomponente und Herstellungsverfahren
DE4432998 1994-09-16

Publications (3)

Publication Number Publication Date
EP0702130A2 EP0702130A2 (fr) 1996-03-20
EP0702130A3 EP0702130A3 (fr) 1998-06-10
EP0702130B1 true EP0702130B1 (fr) 2003-04-23

Family

ID=6528373

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95113444A Expired - Lifetime EP0702130B1 (fr) 1994-09-16 1995-08-26 Procédé pour la production d'un revêtement abrasif pour des constituants métalliques de propulseurs

Country Status (5)

Country Link
US (2) US5756217A (fr)
EP (1) EP0702130B1 (fr)
AT (1) ATE238489T1 (fr)
DE (2) DE4432998C1 (fr)
ES (1) ES2196035T3 (fr)

Cited By (1)

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EP0702130A2 (fr) 1996-03-20
ES2196035T3 (es) 2003-12-16
US6171351B1 (en) 2001-01-09
DE4432998C1 (de) 1996-04-04
EP0702130A3 (fr) 1998-06-10
US5756217A (en) 1998-05-26
ATE238489T1 (de) 2003-05-15
DE59510655D1 (de) 2003-05-28

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