EP2255074B1 - Couche de protection contre le battement de gouttes destinée à une aube - Google Patents

Couche de protection contre le battement de gouttes destinée à une aube Download PDF

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Publication number
EP2255074B1
EP2255074B1 EP09716222A EP09716222A EP2255074B1 EP 2255074 B1 EP2255074 B1 EP 2255074B1 EP 09716222 A EP09716222 A EP 09716222A EP 09716222 A EP09716222 A EP 09716222A EP 2255074 B1 EP2255074 B1 EP 2255074B1
Authority
EP
European Patent Office
Prior art keywords
blade
protective layer
matrix
plates
hard material
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.)
Not-in-force
Application number
EP09716222A
Other languages
German (de)
English (en)
Other versions
EP2255074A1 (fr
Inventor
Walter David
Jörg SCHÜRHOFF
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 EP09716222A priority Critical patent/EP2255074B1/fr
Publication of EP2255074A1 publication Critical patent/EP2255074A1/fr
Application granted granted Critical
Publication of EP2255074B1 publication Critical patent/EP2255074B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • 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
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines
    • 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
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/612—Foam

Definitions

  • the invention relates to a blade for a turbomachine, wherein the blade has an airfoil, wherein on the airfoil surface a protective layer comprising a matrix and a hard material is arranged.
  • turbomachinery covers water turbines, steam and gas turbines, wind turbines, centrifugal pumps and centrifugal compressors as well as propellers. These machines have in common that they serve the purpose of extracting energy from one fluid in order to drive another machine or, conversely, to supply energy to a fluid in order to increase its pressure.
  • the drop impact erosion forms an undesirable phenomenon.
  • Drop impact erosion may occur at the leading edges of the blades.
  • the steam flow in steam turbines may form fog droplets that are trapped and collected by the vanes. These mist droplets can grow into comparatively large drops of water and finally tear off from the trailing edge of the guide vane. Due to their high kinetic energy, these water drops preferably lead to the so-called drop impact erosion at the blade inlet edges, in which the surface of the blade inlet edge is damaged by material removal.
  • the drops in this case have a diameter in the order of 50 .mu.m to 400 .mu.m. Much smaller drops are harmless and larger ones do not occur.
  • the US 6,670,049 A discloses a blade for a turbomachine, the blade having an airfoil, wherein on the airfoil surface a protective layer comprising a matrix and a hard material is arranged.
  • the invention begins, whose task is to form an effective protective layer on a blade in order to avoid the drop impact erosion.
  • a blade for a turbomachine wherein the blade has an airfoil, wherein on the airfoil surface a protective layer comprising a matrix and a hard material is arranged, wherein a plurality of plates formed from the hard material are arranged in the matrix such that the plates overlapping each other along the airfoil surface and having a curved shape.
  • the path is taken to form a protective layer of essentially two components, namely a matrix and a hard material arranged in this matrix.
  • This hard material is formed as a plate and arranged in the matrix, that the plates are on the one hand one above the other and next to each other and on the other overlapping are arranged to each other.
  • the overlap effectively prevents a drop falling on this protective layer can at most ablate the matrix by a crash to a plate. Since the plates are arranged side by side, one above the other and overlapping to each other, it can happen that at most the material removal of the matrix takes place up to a plate and thus further material removal is stopped.
  • the underlying under the protective layer blade surface is thus completely kept away from the water droplets. A drop impact erosion is therefore no longer possible on the blade surface.
  • the plates are arranged substantially parallel to the airfoil surface.
  • Conceivable are any arrangements of the plates to each other, which, so to speak, have a opaque arrangement.
  • the opaque arrangement means the following: one in the direction of the airfoil surface, i. to a surface normal, leading viewing direction is a continuous view of the airfoil surface, so to speak denied by the arrangement of the plates.
  • a substantially parallel arrangement of the plates to the blade surface is comparatively inexpensive to produce, since only a displacement of the plates has to be made next to each other or one above the other.
  • the matrix is a metallic matrix.
  • the metallic matrix can consist, for example, of solderable individual metals (eg copper Cu, silver Ag, nickel Ni, cobalt Co, tin Sn, lead Pb) or also of alloys based thereon (eg Ag-Sn, Cu-Ni, Sn-Cu , Pb-Ag, Ni-Cr).
  • the matrix should also have a certain protection against drop impact erosion.
  • a metallic matrix provides protection against drop impact erosion, resulting in less material removal.
  • the protective layer is formed as a film.
  • a film is naturally easy to apply to a non-flat surfaces.
  • the airfoil surface has a generally non-planar geometry.
  • a film is usually flexible and therefore can be easily placed on the airfoil surface.
  • the matrix is a solder.
  • a solder usually consists of an alloy of different metals and is used for soldering. The solder has the property that the melting point of this alloy is lower than that of the individual metals.
  • Various materials for a solder are known in the art. The solder must in principle be suitable for being arranged on a blade by soldering.
  • the solder can be made, for example, from solderable individual metals (eg copper Cu, silver Ag, nickel Ni, cobalt Co, tin Sn, lead Pb) or also from alloys based thereon (eg Ag-Sn, Cu-Ni, Sn-Cu, Pb -Ag, Ni-Cr).
  • solderable individual metals eg copper Cu, silver Ag, nickel Ni, cobalt Co, tin Sn, lead Pb
  • alloys based thereon eg Ag-Sn, Cu-Ni, Sn-Cu, Pb -Ag, Ni-Cr.
  • the hard material consists of individual hard metals or steels (eg hardened steel), metal alloys (eg Co-base alloys such as "stellites") or of ceramic materials (eg carbides such as tungsten carbide, oxides such as aluminum oxide, nitrides like titanium nitride).
  • metal alloys eg Co-base alloys such as "stellites”
  • ceramic materials eg carbides such as tungsten carbide, oxides such as aluminum oxide, nitrides like titanium nitride.
  • the hard material has a hardness greater than 400 HV.
  • FIG. 1 shows a cross-sectional view of a portion of an airfoil surface 1 and a protective layer 2.
  • the protective layer 2 is applied to a not shown blade of a turbomachine.
  • a turbomachine is for example a steam turbine or a gas turbine.
  • the blade has an airfoil shaped with an airfoil profile.
  • Such blades are preferably used in low-pressure steam turbines.
  • droplets 3 form on the vanes. These drops 3 strike the protective layer 2 with high kinetic energy with an impact direction 3. As a result of the high kinetic energy of the drops 3, a piece of material is knocked out of the protective layer 2.
  • a trough remains 5.
  • the in the FIG. 1 illustrated protective layer comprises a matrix 6 and arranged in the matrix 6 hard material 7.
  • the hard material 7 is however spherical or pratzig educated. It is therefore possible that there is a distance between two hard materials 7. In such a space between two hard materials 7, drops 3 can remove the matrix 6 as far as the airfoil surface 1.
  • FIG. 2 is a not belonging to the invention protective layer 2 to see.
  • the in the FIG. 2 shown protective layer 2 also has the matrix 6 and a hard material 7.
  • the hard material 7 is here formed in a plurality of plates 10.
  • the plates 10 are in the FIG. 2 flat and straight. According to the invention, the plates 10 are bent.
  • the shape of the plates 10 may be concave or convex.
  • the plates may be stacked one above the other such that a layer of concave plates overlies a layer of convex plates.
  • a convex plate is characterized by the fact that two points on the surface can be connected by a straight line, whereby this straight line does not touch the plate.
  • a concave plate is characterized by the fact that two points on the surface can be connected by a straight line, which line touches the plate or even passes through the plate. For example, a horseshoe shape or a U-shape would be possible. However, a trained as a plate 10 hard material 7 is comparatively quick and inexpensive to produce.
  • the protective layer 2 is soldered or fused onto the blade leaf surface 1.
  • the plates 10 are arranged such that they lie next to each other for one side and on the other hand, however, one above the other but offset from one another. Therefore, an overlap of the plates 10 is possible.
  • a drop 3 coming from the direction of impact 4 can now at most remove the matrix 6 up to the plate 10.
  • An ablation of the matrix 6 to the airfoil surface 1 is now no longer possible because of the displacement or overlapping of the plates 10.
  • FIG. 2 right picture is a snapshot, so to speak. It can be seen that the drops 3 can remove the matrix 6 at most up to the first and second plate planes 8, 9.
  • the plates 10 may be arranged obliquely to the airfoil surface 1. Bending of the plate 10 is also possible.
  • the matrix 6 is a metallic matrix.
  • the protective layer 2 is formed as a film, i. the protective layer 2 is formed with the smallest possible spatial extent in the direction of the normal of the airfoil surface 1.
  • the material of the matrix 6 should be chosen such that the protective layer 2 is flexible and easily flexible.
  • the matrix 6 is made of solder in an alternative embodiment. With this material, it is possible to connect the protective layer 2 directly to the airfoil surface 1 by means of soldering.
  • the hard material consists of individual hard metals or steels (e.g., hardened steel), metal alloys (e.g., Co-based alloys such as stellites) or ceramics (e.g., carbides such as tungsten carbide, oxides such as alumina, nitrides such as titanium nitride).
  • metal alloys e.g., Co-based alloys such as stellites
  • ceramics e.g., carbides such as tungsten carbide, oxides such as alumina, nitrides such as titanium nitride.
  • the protective layer 2 can be connected to the airfoil surface 1 by means of fusion.
  • FIG. 3 In the FIG. 3 is a not belonging to the invention perspective view of the protective layer 2 is shown.
  • the plates 10 are arranged side by side and one above the other along the airfoil surface 1.
  • the plates 10 are arranged overlapping each other.
  • a drop 3 coming from the direction of impact 4 is prevented from hitting the blade leaf surface 1 by the offset plates 10 arranged one above the other and next to one another.
  • FIG. 4 a perspective view of the protective layer 2 is shown.
  • the structure of the protective layer 2 is according to FIG. 4 the structure of the protective layer 2 according to FIG. 3 similar.
  • the difference is that the plates are curved concave or convex.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une aube pour une turbomachine, l'aube possédant une pale d'aube et une couche de protection (2) comprenant une matrice (6) et un matériau dur (7) étant disposée sur cette pale d'aube, la couche de protection (2) étant constituée de plaques (10) disposées à recouvrement l'une à côté de l'autre et l'une au-dessus de l'autre.

Claims (8)

  1. Aube pour une turbomachine, l'aube ayant une lame d'aube, dans laquelle il est disposé sur la surface (1) de la lame d'aube, une couche (2) de protection comprenant une matrice (6) et une matière (7) dure,
    caractérisé
    en ce que plusieurs plaques (10) en la matière (7) dure sont disposées dans la matrice (6) de manière à ce que les plaques (10) se chevauchent l'une l'autre le long de la surface (1) de la lame d'aube et aient une forme courbée.
  2. Aube suivant la revendication 1, dans laquelle les plaques (10) sont disposées sensiblement parallèlement à la surface (1) de la lame d'aube.
  3. Aube suivant la revendication 1 ou 2, dans laquelle la matrice (6) est une matrice métallique.
  4. Aube suivant l'une des revendications précédentes, caractérisée en ce que la couche (2) de protection est constituée sous la forme d'une feuille.
  5. Aube suivant l'une des revendications précédentes, dans laquelle la matrice (6) est une brasure.
  6. Aube suivant la revendication 5, dans laquelle la couche (2) de protection est reliée à la surface (1) de la lame d'aube au moyen d'une brasure.
  7. Aube suivant l'une des revendications 1 à 5, dans laquelle la couche (2) de protection est reliée à la surface (1) de la lame d'aube au moyen d'une masse fondue.
  8. Aube suivant l'une des revendications précédentes, dans laquelle la matière (7) dure est en métaux ou aciers durs individuels (par exemple en acier trempé), en alliages de métaux (par exemple alliages à base de Co comme « stellite ») ou en matériaux céramiques (par exemple en carbures, comme en carbure de tungstène, en oxydes, comme en oxyde d'aluminium, en nitrures, comme en nitrure de titane).
EP09716222A 2008-02-29 2009-01-13 Couche de protection contre le battement de gouttes destinée à une aube Not-in-force EP2255074B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09716222A EP2255074B1 (fr) 2008-02-29 2009-01-13 Couche de protection contre le battement de gouttes destinée à une aube

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP08003815A EP2096263A1 (fr) 2008-02-29 2008-02-29 Couche de protection contre les gouttes pour une aube
PCT/EP2009/050313 WO2009109410A1 (fr) 2008-02-29 2009-01-13 Couche de protection contre le battement de gouttes destinée à une aube
EP09716222A EP2255074B1 (fr) 2008-02-29 2009-01-13 Couche de protection contre le battement de gouttes destinée à une aube

Publications (2)

Publication Number Publication Date
EP2255074A1 EP2255074A1 (fr) 2010-12-01
EP2255074B1 true EP2255074B1 (fr) 2012-05-30

Family

ID=39684132

Family Applications (2)

Application Number Title Priority Date Filing Date
EP08003815A Withdrawn EP2096263A1 (fr) 2008-02-29 2008-02-29 Couche de protection contre les gouttes pour une aube
EP09716222A Not-in-force EP2255074B1 (fr) 2008-02-29 2009-01-13 Couche de protection contre le battement de gouttes destinée à une aube

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP08003815A Withdrawn EP2096263A1 (fr) 2008-02-29 2008-02-29 Couche de protection contre les gouttes pour une aube

Country Status (3)

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EP (2) EP2096263A1 (fr)
CN (1) CN101960098B (fr)
WO (1) WO2009109410A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012200491B4 (de) * 2012-01-13 2015-05-28 Lufthansa Technik Ag Gasturbinenschaufel für ein Flugzeugtriebwerk und Verfahren zur Beschichtung einer Gasturbinenschaufel
JP2020501064A (ja) 2016-11-18 2020-01-16 エムエイチアイ ヴェスタス オフショア ウィンド エー／エス 雨滴径に基づく風力タービンの制御

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB347138A (en) * 1930-01-22 1931-04-22 Charles Algernon Parsons Improvements relating to steam turbines
DE4110941A1 (de) * 1991-03-30 1992-10-01 Berndt Dr Brenner Tropfenschlagerosionsgeschuetzte turbinenschaufel und verfahren zu ihrer herstellung
US6670049B1 (en) * 1995-05-05 2003-12-30 General Electric Company Metal/ceramic composite protective coating and its application
DE19617556A1 (de) * 1996-05-02 1997-11-06 Asea Brown Boveri Thermisch belastete Schaufel für eine Strömungsmaschine
US6527165B1 (en) * 2000-03-24 2003-03-04 General Electric Company Method of making an environmental resistant brazed assembly including a wear resistant surface portion
US20060110254A1 (en) * 2004-11-24 2006-05-25 General Electric Company Thermal barrier coating for turbine bucket platform side faces and methods of application

Also Published As

Publication number Publication date
CN101960098B (zh) 2014-07-09
WO2009109410A1 (fr) 2009-09-11
CN101960098A (zh) 2011-01-26
EP2096263A1 (fr) 2009-09-02
EP2255074A1 (fr) 2010-12-01

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