EP2096263A1 - Droplet impact protection layer for a blade - Google Patents

Droplet impact protection layer for a blade Download PDF

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Publication number
EP2096263A1
EP2096263A1 EP08003815A EP08003815A EP2096263A1 EP 2096263 A1 EP2096263 A1 EP 2096263A1 EP 08003815 A EP08003815 A EP 08003815A EP 08003815 A EP08003815 A EP 08003815A EP 2096263 A1 EP2096263 A1 EP 2096263A1
Authority
EP
European Patent Office
Prior art keywords
matrix
protective layer
blade
plates
airfoil surface
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Withdrawn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
EP08003815A
Other languages
German (de)
French (fr)
Inventor
Walter David
Jörg Dr. 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 EP08003815A priority Critical patent/EP2096263A1/en
Priority to EP09716222A priority patent/EP2255074B1/en
Priority to PCT/EP2009/050313 priority patent/WO2009109410A1/en
Priority to CN200980106671.3A priority patent/CN101960098B/en
Publication of EP2096263A1 publication Critical patent/EP2096263A1/en
Withdrawn legal-status Critical Current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
    • 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 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 having 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 are arranged.
  • 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 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 in addition overlapping to each other, it can happen at most that the material removal of the matrix takes place up to a plate and thus a 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 relatively inexpensive to produce, since only a displacement of the plates next to each other or one above the other has to be done.
  • 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 foil is naturally not easy on one to apply even 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 formed. 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 a protective layer 2 according to the invention can be seen.
  • the in the FIG. 2 shown protective layer 2 has as well as 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. But it is also conceivable that the plates 10 may have a curved shape. 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 ablate 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 ceramic materials (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”
  • ceramic materials 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 a 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.

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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

The bucket has multiple plates (10) formed from a hard material (7), and are arranged in a matrix (6) such that plates are arranged along a bucket blade surface area (1) in an overlapping manner. The matrix is a metallic matrix. A protective layer (2) is formed as film and is connected with the bucket blade surface area by a soldering. The hard material is arranged on the bucket blade surface area.

Description

Die Erfindung betrifft eine Schaufel für eine Strömungsmaschine, wobei die Schaufel ein Schaufelblatt aufweist, wobei auf der Schaufelblattoberfläche eine Schutzschicht umfassend eine Matrix und einen Hartstoff angeordnet ist.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.

Unter der Bezeichnung Strömungsmaschinen werden Wasserturbinen, Dampf- und Gasturbinen, Windräder, Kreiselpumpen und Kreiselverdichter sowie Propeller zusammengefasst. Diesen Maschinen ist gemeinsam, dass sie dem Zweck dienen, einem Fluid Energie zu entziehen, um damit eine andere Maschine anzutreiben oder umgekehrt einem Fluid Energie zuzuführen, um dessen Druck zu erhöhen.The term 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.

Bei Dampfturbinen als Ausführungsform einer Strömungsmaschine, bildet die Tropfenschlagerosion ein unerwünschtes Phänomen. Die Tropfenschlagerosion kann an den Eintrittskanten der Laufschaufeln auftreten. Im Dampfstrom bei Dampfturbinen können sich unter Umständen Nebeltröpfchen bilden, die von den Leitschaufeln eingefangen und gesammelt werden. Diese Nebeltröpfchen können zu vergleichsweise großen Wassertropfen heranwachsen und schließlich von der Abströmkante der Leitschaufel abreißen. Aufgrund ihrer hohen kinetischen Energie führen diese Wassertropfen vorzugsweise an den Laufschaufeleintrittskanten zu der sogenannten Tropfenschlagerosion, bei der die Oberfläche der Laufschaufeleintrittskante durch Materialabtragung beschädigt wird. Die Tropfen weisen hierbei einen Durchmesser in der Größenordnung von 50µm bis 400µm auf. Wesentlich kleinere Tropfen sind harmlos und größere kommen nicht vor.In steam turbines as an embodiment of a turbomachine, 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.

Es sind verschiedene Maßnahmen vorhanden, die eine Tropfenschlagerosion vermeiden sollen. So ist es beispielsweise bekannt, die auf den Leitschaufeln heranwachsenden Wassertröpfchen abzusaugen.There are several measures available to avoid drop impact erosion. For example, it is known to suck the water droplets growing on the vanes.

Des Weiteren ist es bekannt, die Laufschaufeleintrittskanten mit einer Schutzschicht zu versehen. Es ist ebenso bekannt die Laufschaufeleintrittskanten zu härten, damit eine Materialabtragung vermieden wird.Furthermore, it is known to provide the blade inlet edges with a protective layer. It is also known to cure the blade leading edges to avoid material erosion.

Wünschenswert wäre es Tropfenschlagerosion durch eine effektive Schutzschicht zu vermeiden. An dieser Stelle setzt die Erfindung an, deren Aufgabe es ist eine wirksame Schutzschicht auf einer Schaufel auszubilden, um die Tropfenschlagerosion zu vermeiden.It would be desirable to avoid drop impact erosion by an effective protective layer. At this point, the invention begins, whose task is to form an effective protective layer on a blade in order to avoid the drop impact erosion.

Diese Aufgabe wird gelöst durch eine Schaufel für eine Strömungsmaschine, wobei die Schaufel ein Schaufelblatt aufweist, wobei auf der Schaufelblattoberfläche eine Schutzschicht umfassend eine Matrix und einen Hartstoff angeordnet ist, wobei mehrere aus dem Hartstoff gebildete Platten derart in der Matrix angeordnet sind, dass die Platten überlappend zueinander entlang der Schaufelblattoberfläche angeordnet sind.This object is achieved by 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, 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 are arranged.

Somit wird der Weg eingeschlagen, eine Schutzschicht aus im Wesentlichen zwei Bestandteilen auszubilden, nämlich einer Matrix und einem in dieser Matrix angeordneten Hartstoff. Dieser Hartstoff ist als Platte ausgebildet und derart in der Matrix angeordnet, dass die Platten zum einen übereinander und nebeneinander liegen und zum anderen überlappend zueinander angeordnet sind. Durch die Überlappung wird wirksam verhindert, dass ein Tropfen der auf diese Schutzschicht fällt höchstens die Matrix durch einen Aufprall bis zu einer Platte abtragen kann. Da die Platten nebeneinander, übereinander und dazu noch überlappend zueinander angeordnet sind, kann es höchstens vorkommen, dass die Materialabtragung der Matrix bis zu einer Platte erfolgt und somit eine weitere Materialabtragung gestoppt wird. Die unter der Schutzschicht liegende Schaufelblattoberfläche wird somit gänzlich von den Wassertropfen ferngehalten. Eine Tropfenschlagerosion ist demnach an der Schaufelblattoberfläche nicht mehr möglich.Thus, 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 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 in addition overlapping to each other, it can happen at most that the material removal of the matrix takes place up to a plate and thus a 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.

Vorteilhafte Weiterbildungen sind in den Unteransprüchen angegeben.Advantageous developments are specified in the subclaims.

So ist es vorteilhaft, wenn die Platten im Wesentlichen parallel zur Schaufelblattoberfläche angeordnet sind. Denkbar sind jegliche Anordnungen der Platten zueinander, die sozusagen eine blickdichte Anordnung aufweisen. Unter der blickdichten Anordnung ist folgendes zu verstehen: Eine in Richtung der Schaufelblattoberfläche, d.h. zu einer Flächennormalen, führenden Blickrichtung wird ein durchgehender Blick auf die Schaufelblattoberfläche sozusagen verwehrt durch die Anordnung der Platten. Eine im Wesentlichen parallele Anordnung der Platten zur Schaufelblattoberfläche ist vergleichsweise kostengünstig herstellbar, da lediglich eine Verschiebung der Platten nebeneinander bzw. übereinander zu erfolgen hat.So it is advantageous if 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 relatively inexpensive to produce, since only a displacement of the plates next to each other or one above the other has to be done.

In einer weiteren vorteilhaften Weiterbildung ist die Matrix eine metallische Matrix. Die metallische Matrix kann beispielsweise aus lötbaren einzelnen Metallen (z.B. Kupfer Cu, Silber Ag, Nickel Ni, Kobalt Co, Zinn Sn, Blei Pb) oder auch aus Legierungen auf deren Basis bestehen (z.B. Ag-Sn, Cu-Ni, Sn-Cu, Pb-Ag, Ni-Cr).In a further advantageous development, 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).

Die Matrix soll neben der einfachen Aufnahme der aus Hartstoff gebildeten Platten auch einen gewissen Schutz vor Tropfenschlagerosion aufweisen. Eine metallische Matrix bietet einen Schutz vor Tropfenschlagerosion, was zu einer geringeren Materialabtragung führt.In addition to the simple absorption of the plates formed from hard material, 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.

Vorteilhafter Weise ist die Schutzschicht als Folie ausgebildet. Eine Folie ist naturgemäß leicht auf eine nicht ebene Flächen aufzubringen. Die Schaufelblattoberfläche weist eine in der Regel nicht ebene Geometrie auf. Eine Folie ist in der Regel flexibel und kann daher leicht auf die Schaufelblattoberfläche angeordnet werden. Vorteilhafter Weise ist die Matrix ein Lot. Ein Lot besteht meist aus einer Legierung aus verschiedenen Metallen und wird zum Löten verwendet. Das Lot hat die Eigenschaft, dass der Schmelzpunkt dieser Legierung niedriger ist als der der einzelnen Metalle. Es sind verschiedene Materialien für ein Lot im Stand der Technik bekannt. Das Lot muss grundsätzliche geeignet sein, um an eine Schaufel durch Lötung angeordnet zu werden. Das Lot kann beispielsweise aus lötbaren einzelnen Metallen (z.B. Kupfer Cu, Silber Ag, Nickel Ni, Kobalt Co, Zinn Sn, Blei Pb) oder auch aus Legierungen auf deren Basis (z.B. Ag-Sn, Cu-Ni, Sn-Cu, Pb-Ag, Ni-Cr) bestehen.Advantageously, the protective layer is formed as a film. A foil is naturally not easy on one to apply even 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. Advantageously, 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).

In einer weiteren vorteilhaften Weiterbildung besteht der Hartstoff aus einzelnen harten Metallen bzw. Stählen (z.B. gehärteter Stahl), Metall-Legierungen (z.B. Co-Basis Legierungen wie "Stellite") oder aus keramischen Werkstoffen (z.B. Karbide wie Wolframkarbid, Oxide wie Aluminiumoxid, Nitride wie Titannitrid).In a further advantageous development, 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).

Vorteilhafter Weise weist der Hartstoff eine Härte größer als 400 HV auf.Advantageously, the hard material has a hardness greater than 400 HV.

Diese Materialien haben sich als besonders vorteilhaft und geeignet für den Einsatz als Hartschicht erwiesen, die zu Platten geformt werden können und bieten einen hervorragenden Schutz vor Tropfenschlagerosion.These materials have been found to be particularly advantageous and suitable for use as a hardcoat that can be formed into sheets and offer excellent protection against drop impact erosion.

Nachfolgend wird ein Ausführungsbeispiel der Erfindung anhand der beigefügten schematischen Zeichnung näher erläutert. Es zeigen:

Figur 1
eine Querschnittsansicht durch einen Teil der Schaufelblattoberfläche mit einer Schutzschicht aus einer Matrix und sphärischen Hartstoffen,
Figur 2
eine Querschnittsansicht einer Schaufelblattoberfläche mit einer Schutzschicht aus einer Matrix und einem aus Hartstoff ausgebildete Platten,
Figur 3
eine teilperspektivische Ansicht der Schutzschicht.
An embodiment of the invention will be explained in more detail with reference to the accompanying schematic drawing. Show it:
FIG. 1
a cross-sectional view through part of the airfoil surface with a protective layer of a matrix and spherical hard materials,
FIG. 2
a cross-sectional view of an airfoil surface with a protective layer of a matrix and formed of hard material plates,
FIG. 3
a partial perspective view of the protective layer.

Gleiche Bezugszeichen haben in den verschiedenen Figuren die gleiche Bedeutung.Like reference numerals have the same meaning in the various figures.

Die Figur 1 zeigt eine Querschnittsansicht eines Teils einer Schaufelblattoberfläche 1 und einer Schutzschicht 2. Die Schutzschicht 2 wird auf eine nicht näher dargestellte Schaufel einer Strömungsmaschine aufgebracht. Eine Strömungsmaschine ist beispielsweise ein Dampfturbine oder eine Gasturbine. Die Schaufel weist ein mit einem Schaufelblattprofil geformtes Schaufelblatt auf. Solche Schaufelblätter werden vorzugsweise in Niederdruck-Dampfturbinen eingesetzt. In Niederdruck-Dampfturbinen bilden sich Tropfen 3 auf den Leitschaufeln aus. Diese Tropfen 3 treffen mit hoher kinetischer Energie mit einer Aufprallrichtung 3 auf die Schutzschicht 2 auf. In Folge der hohen kinetischen Energie der Tropfen 3 wird aus der Schutzschicht 2 ein Stück Material herausgeschlagen. Zurück bleibt eine Mulde 5.The 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. 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.

Die in der Figur 1 dargestellte Schutzschicht umfasst eine Matrix 6 und einen in der Matrix 6 angeordneten Hartstoff 7 auf. Der Hartstoff 7 ist allerdings sphärisch oder pratzig ausgebildet. Es ist daher möglich, dass zwischen zwei Hartstoffen 7 ein Abstand herrscht. In solch einem Raum zwischen zwei Hartstoffen 7 können Tropfen 3 die Matrix 6 bis zur Schaufelblattoberfläche 1 abtragen.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 formed. 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.

In der Figur 2 ist eine erfindungsgemäße Schutzschicht 2 zu sehen. Die in der Figur 2 dargestellte Schutzschicht 2 weist ebenso die Matrix 6 und einen Hartstoff 7 auf. Der Hartstoff 7 ist hier allerdings in mehrere Platten 10 ausgebildet. Die Platten 10 sind in der Figur 2 eben und gradlinig. Es ist aber auch denkbar, dass die Platten 10 eine gebogene Form aufweisen können. Beispielsweise wäre eine Hufeisenform oder eine U-Form möglich. Allerdings ist ein als Platte 10 ausgebildeter Hartstoff 7 vergleichsweise schnell und kostengünstig herstellbar. Die Schutzschicht 2 wird auf die Schaufelblattoberfläche 1 gelötet oder aufgeschmolzen.In the FIG. 2 a protective layer 2 according to the invention can be seen. The in the FIG. 2 shown protective layer 2 has as well as the matrix 6 and a hard material 7. However, the hard material 7 is here formed in a plurality of plates 10. The plates 10 are in the FIG. 2 flat and straight. But it is also conceivable that the plates 10 may have a curved shape. 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.

Die Platten 10 werden dabei derart angeordnet, dass sie zum einen nebeneinander liegen und zum anderen auch übereinander allerdings versetzt zueinander angeordnet sind. Daher ist eine Überlappung der Platten 10 möglich. Ein aus der Aufprallrichtung 4 kommender Tropfen 3 kann nunmehr höchstens die Matrix 6 bis zu der Platte 10 abtragen. Ein Abtragen der Matrix 6 bis zur Schaufelblattoberfläche 1 ist nunmehr nicht mehr möglich, wegen der Versetzung bzw. Überlappung der Platten 10. In der Figur 2 rechtes Bild ist eine Momentaufnahme sozusagen dargestellt. Es ist zu sehen, dass die Tropfen 3 die Matrix 6 höchstens bis zur ersten und zweiten Plattenebene 8, 9 abtragen können.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. In the FIG. 2 right picture is a snapshot, so to speak. It can be seen that the drops 3 can ablate the matrix 6 at most up to the first and second plate planes 8, 9.

Die Platten 10 können schräg zur Schaufelblattoberfläche 1 angeordnet sein. Eine Biegung der Platte 10 ist ebenso möglich. Die Matrix 6 ist eine metallische Matrix. Die Schutzschicht 2 wird als Folie ausgebildet, d.h. die Schutzschicht 2 wird mit einer möglichst geringen räumlichen Ausdehnung in der Richtung der Normalen der Schaufelblattoberfläche 1 ausgebildet. Darüber hinaus sollte das Material der Matrix 6 derart gewählt werden, dass die Schutzschicht 2 flexibel und leicht biegsam ist.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. In addition, the material of the matrix 6 should be chosen such that the protective layer 2 is flexible and easily flexible.

Die Matrix 6 wird in einer alternativen Ausführungsform aus Lot hergestellt. Mit diesem Material ist es möglich, die Schutzschicht 2 mittels einer Lötung mit der Schaufelblattoberfläche 1 direkt zu verbinden.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.

Der Hartstoff besteht aus einzelnen harten Metallen bzw. Stählen (z.B. gehärteter Stahl), Metall-Legierungen (z.B. Co-Basis Legierungen wie "Stellite") oder aus keramischen Werkstoffen (z.B. Karbide wie Wolframkarbid, Oxide wie Aluminiumoxid, Nitride wie Titannitrid).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 ceramic materials (e.g., carbides such as tungsten carbide, oxides such as alumina, nitrides such as titanium nitride).

Des Weiteren kann die Schutzschicht 2 mittels einer Schmelzung mit der Schaufelblattoberfläche 1 verbunden werden.Furthermore, the protective layer 2 can be connected to the airfoil surface 1 by means of fusion.

In der Figur 3 ist eine perspektivische Ansicht der Schutzschicht 2 dargestellt. Die Platten 10 sind entlang der Schaufelblattoberfläche 1 nebeneinander und übereinander angeordnet. Die Platten 10 sind dabei überlappend zueinander angeordnet. Ein aus der Aufprallrichtung 4 kommender Tropfen 3 wird durch die versetzten übereinander und nebeneinander angeordneten Platten 10 daran gehindert, auf die Schaufelblattoberfläche 1 zu treffen.In the FIG. 3 a 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.

Claims (8)

Schaufel für eine Strömungsmaschine, wobei die Schaufel ein Schaufelblatt aufweist,
wobei auf der Schaufelblattoberfläche (1) eine Schutzschicht (2) umfassend eine Matrix (6) und einen Hartstoff (7) angeordnet ist,
dadurch gekennzeichnet,
dass mehrere aus dem Hartstoff (7) ausgebildete Platten (10) derart in der Matrix (6) angeordnet sind, dass die Platten (10) überlappend zueinander entlang der Schaufelblattoberfläche (1) angeordnet sind.Blade for a turbomachine, the blade having an airfoil,
wherein on the airfoil surface (1) a protective layer (2) comprising a matrix (6) and a hard material (7) is arranged,
characterized,
in that a plurality of plates (10) formed from the hard material (7) are arranged in the matrix (6) such that the plates (10) are arranged overlapping one another along the airfoil surface (1). Schaufel nach Anspruch 1,
wobei die Platten (10) im Wesentlichen parallel zur Schaufelblattoberfläche (1) angeordnet sind.Shovel according to claim 1,
wherein the plates (10) are arranged substantially parallel to the airfoil surface (1). Schaufel nach Anspruch 1 oder 2,
wobei die Matrix (6) eine metallische Matrix ist.A blade according to claim 1 or 2,
wherein the matrix (6) is a metallic matrix. Schaufel nach einem der vorhergehenden Ansprüche,
wobei die Schutzschicht (2) als Folie ausgebildet ist.Shovel according to one of the preceding claims,
wherein the protective layer (2) is formed as a film. Schaufel nach einem der vorhergehenden Ansprüche,
wobei die Matrix (6) ein Lot ist.Shovel according to one of the preceding claims,
wherein the matrix (6) is a solder. Schaufel nach Anspruch 5,
wobei die Schutzschicht (2) mittels einer Lötung mit der Schaufelblattoberfläche (1) verbunden ist.Shovel according to claim 5,
wherein the protective layer (2) is connected to the airfoil surface (1) by means of soldering. Schaufel nach einem der Ansprüche 1 bis 5,
wobei die Schutzschicht (2) mittels einer Schmelzung mit der Schaufelblattoberfläche (1) verbunden ist.A blade according to any one of claims 1 to 5,
wherein the protective layer (2) is fusion bonded to the airfoil surface (1). Schaufel nach einem der vorhergehenden Ansprüche,
wobei der Hartstoff (7) aus einzelnen harten Metallen bzw. Stählen (z.B. gehärteter Stahl), Metall-Legierungen (z.B. Co-Basis Legierungen wie "Stellite") oder aus keramischen Werkstoffen (z.B. Karbide wie Wolframkarbid, Oxide wie Aluminiumoxid, Nitride wie Titannitrid) besteht.Shovel according to one of the preceding claims,
wherein the hard material (7) 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 such as titanium nitride ) consists.
EP08003815A 2008-02-29 2008-02-29 Droplet impact protection layer for a blade Withdrawn EP2096263A1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP08003815A EP2096263A1 (en) 2008-02-29 2008-02-29 Droplet impact protection layer for a blade
EP09716222A EP2255074B1 (en) 2008-02-29 2009-01-13 Droplet impact protection layer for a blade
PCT/EP2009/050313 WO2009109410A1 (en) 2008-02-29 2009-01-13 Droplet impact protection layer for a shovel
CN200980106671.3A CN101960098B (en) 2008-02-29 2009-01-13 Droplet impact protection layer for a shovel

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08003815A EP2096263A1 (en) 2008-02-29 2008-02-29 Droplet impact protection layer for a blade

Publications (1)

Publication Number Publication Date
EP2096263A1 true EP2096263A1 (en) 2009-09-02

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EP08003815A Withdrawn EP2096263A1 (en) 2008-02-29 2008-02-29 Droplet impact protection layer for a blade
EP09716222A Not-in-force EP2255074B1 (en) 2008-02-29 2009-01-13 Droplet impact protection layer for a blade

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CN (1) CN101960098B (en)
WO (1) WO2009109410A1 (en)

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Publication number Priority date Publication date Assignee Title
DE102012200491B4 (en) * 2012-01-13 2015-05-28 Lufthansa Technik Ag Gas turbine blade for an aircraft engine and method of coating a gas turbine blade
KR20190085080A (en) * 2016-11-18 2019-07-17 엠에이치아이 베스타스 오프쇼어 윈드 에이／에스 Wind turbine control based on raindrop size

Citations (4)

* 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
EP0507131A1 (en) * 1991-03-30 1992-10-07 Fraunhofer-Gesellschaft Zur Förderung Der Angewandten Forschung E.V. Turbine blade protected against water droplets abrasion and method of manufacture
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
US6670049B1 (en) * 1995-05-05 2003-12-30 General Electric Company Metal/ceramic composite protective coating and its application

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19617556A1 (en) * 1996-05-02 1997-11-06 Asea Brown Boveri Thermally loaded blade for a turbomachine
US20060110254A1 (en) * 2004-11-24 2006-05-25 General Electric Company Thermal barrier coating for turbine bucket platform side faces and methods of application

Patent Citations (4)

* 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
EP0507131A1 (en) * 1991-03-30 1992-10-07 Fraunhofer-Gesellschaft Zur Förderung Der Angewandten Forschung E.V. Turbine blade protected against water droplets abrasion and method of manufacture
US6670049B1 (en) * 1995-05-05 2003-12-30 General Electric Company Metal/ceramic composite protective coating and its application
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

Also Published As

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EP2255074A1 (en) 2010-12-01
CN101960098A (en) 2011-01-26
WO2009109410A1 (en) 2009-09-11
CN101960098B (en) 2014-07-09
EP2255074B1 (en) 2012-05-30

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