EP1468170B1 - Method for changing the frequency of blades for thermal turbo-machines - Google Patents

Method for changing the frequency of blades for thermal turbo-machines Download PDF

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Publication number
EP1468170B1
EP1468170B1 EP03700009A EP03700009A EP1468170B1 EP 1468170 B1 EP1468170 B1 EP 1468170B1 EP 03700009 A EP03700009 A EP 03700009A EP 03700009 A EP03700009 A EP 03700009A EP 1468170 B1 EP1468170 B1 EP 1468170B1
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EP
European Patent Office
Prior art keywords
blade
blades
frequency
coating
changing
Prior art date
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Expired - Fee Related
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EP03700009A
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German (de)
French (fr)
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EP1468170A1 (en
Inventor
Bruno Benedetti
Andreas Kieninger
Christoph Nagler
Jörg Stengele
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General Electric Technology GmbH
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Alstom Technology AG
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Publication of EP1468170A1 publication Critical patent/EP1468170A1/en
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    • 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
    • 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
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/311—Layer deposition by torch or flame spraying
    • 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

Definitions

  • the invention relates to the field of thermal fluid machines. It relates to a method for changing the frequency of blades, in particular turbine blades, which are already largely ready for use for installation in the turbomachine.
  • the performance of a gas turbine is essentially determined by the processed mass flows such as fuel and air.
  • the blade dimensions, z. B. the chord length, the blade height, the curvature, the profile, the twist and the Blade spacing determine the most suitable for the turbine flow data of a stage, such as inflow and outflow angle, pressure ratio, gas velocity and quantity.
  • the aim of the invention is to avoid the mentioned disadvantages of the prior art.
  • the invention is based on the object to develop a method for changing the frequency of blades, in particular turbine blades, which is quickly and easily applicable to already ready to use blades. Because of the high aerodynamic sensitivity of the blades, the changes in the airfoil profile should only be very small.
  • this object is achieved in a method according to the preamble of claim 1, that is applied to the ready blade ready a metallic coating of a material identical to the base material in the blade tip, wherein the thickness of the coating at the trailing edge and in the radial Direction towards the blade root continuously tapered.
  • the advantages of the invention are that it is possible with the inventive method, very quickly with turbine blades, which differences between the theoretical frequency calculation during the design phase and the actual measured frequency to change the frequency. Thereby, failure of the components during operation of the machine due to resonance excitation can be prevented.
  • the metallic coating is applied to the blade by means of flame spraying.
  • the flame spraying process is relatively universally applicable. Material thicknesses can be realized in relatively wide ranges.
  • soft continuous transitions in the order thickness can be achieved, with the application material can be placed locally in the right places, without any significant rework, such. B. a grinding, is necessary.
  • Fig. 1 shows a side view of a blade 1 of a gas turbine.
  • the guide vane 1 consists of an airfoil 2, a blade root 3 and a platform 4 arranged therebetween, from which the airfoil 2 extends integrally.
  • the blade root 3 is used for attachment the turbine blade 1 in a turbine rotor, not shown.
  • the airfoil 2 has a pressure side 5 and a (in Fig. 1 not visible) suction side 6, which adjoin one another at an exit edge 7, and a blade tip 9.
  • Fig. 1 is the view of the pressure side 5 of the airfoil 2 is shown.
  • Fig. 2 shows a section along the plane II-II of Fig. 1 , For reasons of simplicity, the inner contour of the blade 1, which has an internal cooling system, in Fig. 2 not shown.
  • the blade 2 which is ready for use is fitted with a metallic coating prior to installation on the blade tip 9 8 provided.
  • the coating (8) consists of a material identical to the base material.
  • the metal is preferably applied to the blade 2 by means of a known flame spraying process. It is important that the thickness of the metallic coating 8 continuously tapers at the outlet edge 7 and in the radial direction towards the blade root 3.
  • the inventive method is inexpensive and can be realized in a very short time.
  • the flame spraying process is particularly well suited, as it creates "smooth" continuous transitions in the application thickness and allows the material to be applied 8 to be placed precisely in the right place in the right places without the need for reworking.

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

Abstract

The invention relates to a method for changing the frequency of blades (1), especially turbine blades, for thermal turbo-machines, said blades having a paddle (2) comprising a suction side (6), a pressure side (5), an inlet edge (10), an outlet edge (7) and a blade tip (9), in addition to a blade root (3). The inventive method is characterised in that a metallic coating (8) consisting of a material which is identical to the base material is applied to the tip (9) of the blade (1) which is ready for use, the thickness of the coating (8) on the outlet edge (7) and in the radial direction towards the blade root (3) being continuously reduced.

Description

Technisches GebietTechnical area

Die Erfindung bezieht sich auf das Gebiet der thermischen Strömungsmaschinen. Sie betrifft ein Verfahren zur Frequenzveränderung von Schaufeln, insbesondere Turbinenschaufeln, welche bereits für den Einbau in die Strömungsmaschine weitgehend einsatzfertig sind.The invention relates to the field of thermal fluid machines. It relates to a method for changing the frequency of blades, in particular turbine blades, which are already largely ready for use for installation in the turbomachine.

Stand der TechnikState of the art

Die Leistung einer Gasturbine wird im wesentlichen bestimmt durch die verarbeiteten Massenströme wie Brennstoff und Luft.The performance of a gas turbine is essentially determined by the processed mass flows such as fuel and air.

Auf die Höhe des Wirkungsgrades einer Gasturbine hat neben den Dichtungen, Lagern usw. vor allem die Güte der Beschaufelung einen Einfluss. Die Schaufelabmessungen, z. B. die Sehnenlänge, die Schaufelhöhe, die Wölbung, das Profil, die Verwindung und der Schaufelabstand bestimmen dabei die für die Turbine geeignetesten Strömungsdaten einer Stufe, beispielweise An- und Abströmwinkel, Druckverhältnis, Gasgeschwindigkeit und -menge.In addition to the seals, bearings, etc. above all the quality of the blading has an influence on the level of efficiency of a gas turbine. The blade dimensions, z. B. the chord length, the blade height, the curvature, the profile, the twist and the Blade spacing determine the most suitable for the turbine flow data of a stage, such as inflow and outflow angle, pressure ratio, gas velocity and quantity.

Die Auslegung/Konstruktion einer neuen Gasturbine beruht heute auf Erfahrungen, Berechnungen und Versuchen. Dabei gibt es immer wieder Parameter, die durch Annahmen nur unzureichend das Optimum darstellen.The design / construction of a new gas turbine today is based on experience, calculations and tests. Again and again, there are parameters that only insufficiently represent the optimum through assumptions.

Unterschiede zwischen der theoretischen Frequenzkalkulation während der Design-Phase und der gemessenen Frequenz erfordern eine Veränderung der Schaufelfrequenz an der fertigen Schaufel, um zu verhindern, dass während des Betriebes der Maschine auf Grund von Resonanzanregung Bauteile ausfallen.Differences between the theoretical frequency calculation during the design phase and the measured frequency require a change in the blade frequency on the finished blade to prevent components from failing during operation of the machine due to resonance excitation.

Falls genügend Zeit zur Verfügung steht, kann eine Frequenzveränderung an den Schaufeln realisiert werden durch Anwendung von Druckgusswachsmodellen. Im oben beschriebene Fall ist diese Lösung unbrauchbar, weil die Bauteile bereits fertig für den Einsatz in der Turbine sind, so dass aus Kostengründen eine sehr schnelle Methode zur Frequenzveränderung an den Schaufeln notwendig ist.If enough time is available, a frequency change on the blades can be realized by using die cast wax models. In the case described above, this solution is useless because the components are already ready for use in the turbine, so that for cost reasons, a very fast method for changing the frequency of the blades is necessary.

Aus der Reparaturtechnik ist bekannt, mittels Flammspritzen bei Gleitlagern, Walzen, Zylindern usw. einen Materialauftrag zu realisieren. Nach dem Überschleifen sind diese Teile wieder gebrauchstüchtig und Neuteilen ebenbürtig. Hier geht es darum, das ursprüngliche Originalmass wieder herzustellen oder verschleissfestere Materialien aufzutragen.From the repair technique is known to realize by means of flame spraying in plain bearings, rollers, cylinders, etc. a material order. After sanding these parts are ready for use again and new parts equal. This is about restoring the original original size or applying more wear-resistant materials.

Bekannt ist auch, einen Materialauftrag auf bestimmte Bauteile mittels Schweissen aufzubringen. Das setzt aber voraus, dass schweissbare Materialien vorhanden sein müssen. Vor dem Gebrauch der Bauteile müssen diese ebenfalls überschliffen werden.It is also known to apply a material application to certain components by means of welding. This assumes, however, that weldable materials must be present. Before using the components, they must also be ground.

Aus EP 1 026 366 A1 ist bekannt, zur Vibrationsdämpfung einen Materialüberzug im Bereich der Schaufelspitze/Abströmkante einer Turbinenschaufel aufzubringen, wobei z. B. Plasmaspritzen oder andere physikalische oder chemische Aufdampfmethoden angewendet werden. Die Dicke der Schicht, welche aus einer Haftschicht aus Metall oder aus einem Metall/Seltene Erden-Komplex und einer darauf applizierten Oxidkeramikschicht besteht, wird über der Fläche der Schaufel variiert, um einen optimalen Dämpfungseffekt zu erzielen. Wenn die äussere Keramikschicht Vibrationen ausgesetzt ist, erfolgt in der duktilen Haftschicht ein viskoses Scheren, so dass die Amplitude der Vibrationen herabgesetzt wird.Out EP 1 026 366 A1 It is known to apply a material coating in the region of the blade tip / trailing edge of a turbine blade for vibration damping, wherein z. As plasma spraying or other physical or chemical vapor deposition methods are used. The thickness of the layer, which consists of an adhesive layer of metal or of a metal / rare earth complex and an oxide ceramic layer applied thereto, is varied over the surface of the blade in order to achieve an optimal damping effect. When the outer ceramic layer is subjected to vibration, viscous shearing occurs in the ductile adhesive layer, so that the amplitude of the vibrations is reduced.

Darstellung der ErfindungPresentation of the invention

Ziel der Erfindung ist es, die genannten Nachteile des Standes der Technik zu vermeiden. Der Erfindung liegt die Aufgabe zu Grunde, ein Verfahren zur Frequenzveränderung von Schaufeln, insbesondere Turbinenschaufeln, zu entwickeln, welches bei bereits einsatzfertigen Schaufeln schnell und einfach anwendbar ist. Wegen der hohen aerodynamischen Sensitivität der Schaufeln sollen die Veränderungen des Schaufelblattprofiles nur sehr klein sein.The aim of the invention is to avoid the mentioned disadvantages of the prior art. The invention is based on the object to develop a method for changing the frequency of blades, in particular turbine blades, which is quickly and easily applicable to already ready to use blades. Because of the high aerodynamic sensitivity of the blades, the changes in the airfoil profile should only be very small.

Erfindungsgemäss wird diese Aufgabe bei einem Verfahren gemäss Oberbegriff des Patentanspruches 1 dadurch gelöst, dass auf die bereits einsatzfertige Schaufel ein metallischer Überzug aus einem mit dem Grundwerkstoff identischen Material im Bereich der Schaufelspitze aufgebracht wird, wobei sich die Dicke des Überzuges an der Austrittskante und in radialer Richtung zum Schaufelfuss hin kontinuierlich verjüngt.According to the invention this object is achieved in a method according to the preamble of claim 1, that is applied to the ready blade ready a metallic coating of a material identical to the base material in the blade tip, wherein the thickness of the coating at the trailing edge and in the radial Direction towards the blade root continuously tapered.

Die Vorteile der Erfindung bestehen darin, dass es mit dem erfindungsgemässen Verfahren möglich ist, sehr schnell bei Turbinenschaufeln, welche Unterschiede zwischen der theoretischen Frequenzkalkulation während der Design-Phase und der tatsächlich gemessenen Frequenz aufweisen, die Frequenz zu verändern. Dadurch kann ein Ausfall der Bauteile während des Betriebes Maschine infolge von Resonanzanregung verhindert werden.The advantages of the invention are that it is possible with the inventive method, very quickly with turbine blades, which differences between the theoretical frequency calculation during the design phase and the actual measured frequency to change the frequency. Thereby, failure of the components during operation of the machine due to resonance excitation can be prevented.

Es ist vorteilhaft, wenn der metallische Überzug mittels Flammspritz-Verfahren auf das Schaufelblatt appliziert wird. Das Flammspritz-Verfahren ist relativ universell einsetzbar. Es lassen sich Materialdicken in relativ breiten Bereichen realisierbar.It is advantageous if the metallic coating is applied to the blade by means of flame spraying. The flame spraying process is relatively universally applicable. Material thicknesses can be realized in relatively wide ranges.

Ausserdem können weiche kontinuierliche Übergänge in der Auftragsdicke erzielt werden, wobei sich das Auftragsmaterial örtlich begrenzt an den richtigen Stellen platzieren lässt, ohne dass eine nennenswerte Nacharbeit, wie z. B. ein Überschleifen, notwendig ist.In addition, soft continuous transitions in the order thickness can be achieved, with the application material can be placed locally in the right places, without any significant rework, such. B. a grinding, is necessary.

Kurze Beschreibung der ZeichnungenBrief description of the drawings

In der Zeichnung ist ein Ausführungsbeispiel der Erfindung dargestellt. Es zeigen:

Fig. 1
eine Seitenansicht einer Gasturbinenschaufel und
Fig. 2
einen Schnitt entlang der Linie II-II in Fig. 1.
In the drawing, an embodiment of the invention is shown. Show it:
Fig. 1
a side view of a gas turbine blade and
Fig. 2
a section along the line II-II in Fig. 1 ,

Wege zur Ausführung der ErfindungWays to carry out the invention

Nachfolgend wird die Erfindung anhand eines Ausführungsbeispieles und der Fig. 1 und 2 näher erläutert.Hereinafter, the invention with reference to an embodiment and the Fig. 1 and 2 explained in more detail.

Fig. 1 zeigt in einer Seitenansicht eine Laufschaufel 1 einer Gasturbine. Die Leitschaufel 1 besteht aus einem Schaufelblatt 2, einem Schaufelfuss 3 und einer dazwischen angeordneten Plattform 4, von der aus sich das Schaufelblatt 2 integral erstreckt. Der Schaufelfuss 3 dient der Befestigung der Turbinenschaufel 1 in einem nicht dargestellten Turbinenrotor. Das Schaufelblatt 2 weist eine Druckseite 5 und eine (in Fig. 1 nicht sichtbare) Saugseite 6, die an einer Austrittskante 7 aneinandergrenzen, sowie eine Schaufelspitze 9 auf. In Fig. 1 ist die Sicht auf die Druckseite 5 des Schaufelblattes 2 dargestellt. Fig. 1 shows a side view of a blade 1 of a gas turbine. The guide vane 1 consists of an airfoil 2, a blade root 3 and a platform 4 arranged therebetween, from which the airfoil 2 extends integrally. The blade root 3 is used for attachment the turbine blade 1 in a turbine rotor, not shown. The airfoil 2 has a pressure side 5 and a (in Fig. 1 not visible) suction side 6, which adjoin one another at an exit edge 7, and a blade tip 9. In Fig. 1 is the view of the pressure side 5 of the airfoil 2 is shown.

Fig. 2 zeigt einen Schnitt entlang der Ebene II-II von Fig. 1. Aus Vereinfachungsgründen ist die Innenkontur der Schaufel 1, welche ein internes Kühlungssystem aufweist, in Fig. 2 nicht dargestellt. Fig. 2 shows a section along the plane II-II of Fig. 1 , For reasons of simplicity, the inner contour of the blade 1, which has an internal cooling system, in Fig. 2 not shown.

Um Frequenzunterschiede zwischen der während der Design-Phase theoretisch kalkulierten Frequenz und der tatsächlich gemessenen Frequenz an der einsatzfertigen Schaufel 1 zu beseitigen und dadurch eine Resonanzanregung zu verhindern, wird erfindungsgemäss das an sich einsatzfertige Schaufelblatt 2 vor dem Einbau an der Schaufelspitze 9 mit einem metallischen Überzug 8 versehen. Der Überzug (8) besteht aus einem mit dem Grundwerkstoff identischen Material. Das Metall wird dabei vorzugsweise mittels an sich bekanntem Flammspritz-Verfahren auf dem Schaufelblatt 2 appliziert. Wichtig ist, dass sich die Dicke des metallischen Überzuges 8 an der Austrittskante 7 und in radialer Richtung zum Schaufelfuss 3 hin kontinuierlich verjüngt.In order to eliminate frequency differences between the theoretically calculated frequency during the design phase and the actually measured frequency on the ready-to-use blade 1 and thereby prevent resonant excitation, according to the invention the blade 2 which is ready for use is fitted with a metallic coating prior to installation on the blade tip 9 8 provided. The coating (8) consists of a material identical to the base material. The metal is preferably applied to the blade 2 by means of a known flame spraying process. It is important that the thickness of the metallic coating 8 continuously tapers at the outlet edge 7 and in the radial direction towards the blade root 3.

Im konkreten Fall wurde für eine Schaufel, welche aus dem Grundmaterial IN738LC bestand, folgendermassen vorgegangen:

  • Durch Versuche im Standfrequenzprüfstand wurde ein Vorgabewert ermittelt, indem mittels kleiner Massestücke, die an die Schaufelspitze geklebt wurden, der Faktor df/dm (Frequenzänderung in Abhängigkeit von der zusätzlichen Masse) bestimmt wurde. Selbstverständlich könnte dieser Faktor auch mit Hilfe einer Rechnung bestimmt werden.
  • Aufgrund des zulässigen Frequenzbandes und der gemessenen Istwerte ergab sich, dass im konkreten Fall die Eigenfrequenz um 7 Hz gesenkt werden muss.
  • Aus dem Wert df/dm und der Vorgabe, die Eigenfrequenz um 7 Hz zu senken, wurde die aufzubringende Masse an der Schaufelspitze mit 23 g errechnet. Dies entspricht einem Materialvolumen von 2.8 cm3 für IN738LC (Beschichtungsmaterial = Grundmaterial). Das Beschichtungsmaterial wurde auf die obersten 50 mm der Schaufel verteilt, so dass sich eine Schichtdicke von 0.3 mm ergab.
  • Zur Überprüfung wurden nun zuerst nur einige Schaufeln beschichtet und die Massenänderung und Frequenzänderung nachgemessen. Es ergaben sich folgende Werte: dm=28.6 g, df=5.0 Hz.
  • Aufgrund dieser Messergebnisse wurde dann eine zusätzliche Masse von 32 g gefordert und aufgebracht, so das die Eigenfrequenzänderung von 7 Hz realisiert wurde.
In the specific case, the following procedure was followed for a blade made of the IN738LC base material:
  • By means of tests in the stand frequency test stand, a default value was determined by determining the factor df / dm (frequency change as a function of the additional mass) by means of small mass pieces which were glued to the blade tip. Of course, this factor could also be determined by means of an invoice.
  • Due to the permissible frequency band and the measured actual values, it was found that in this specific case the natural frequency had to be reduced by 7 Hz.
  • From the value df / dm and the requirement to lower the natural frequency by 7 Hz, the applied mass at the blade tip was calculated to be 23 g. This corresponds to a material volume of 2.8 cm 3 for IN738LC (coating material = base material). The coating material was spread on the top 50 mm of the blade to give a layer thickness of 0.3 mm.
  • For verification, only a few blades were first coated and the mass change and frequency change measured. The following values were obtained: dm = 28.6 g, df = 5.0 Hz.
  • Based on these measurements, an additional mass of 32 g was required and applied, so that the natural frequency change of 7 Hz was realized.

Das erfindungsgemässe Verfahren ist kostengünstig und in sehr kurzer Zeit realisierbar. Das Flammspritz-Verfahren ist besonders gut geeignet, da damit "weiche" kontinuierliche Übergänge in der Auftragsdicke schafft und sich das aufzutragende Material 8 örtlich genau begrenzt an den richtigen Stellen platzieren lässt, ohne dass eine Nacharbeit notwendig wäre.The inventive method is inexpensive and can be realized in a very short time. The flame spraying process is particularly well suited, as it creates "smooth" continuous transitions in the application thickness and allows the material to be applied 8 to be placed precisely in the right place in the right places without the need for reworking.

Selbstverständlich ist die Erfindung nicht auf das beschriebene Ausführungsbeispiel beschränkt.Of course, the invention is not limited to the embodiment described.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Schaufelshovel
22
Schaufelblattairfoil
33
Schaufelfussblade root
44
Plattformplatform
55
Druckseite von Pos. 2Pressure side of pos. 2
66
Saugseite von Pos. 2Suction side of pos. 2
77
Austrittskante von Pos. 2Exit edge of pos. 2
88th
Metallischer ÜberzugMetallic coating
99
Schaufelspitze von Pos. 2Blade tip of Pos. 2
1010
Eintrittskante von Pos. 2Leading edge of pos. 2

Claims (2)

  1. Method of altering the frequency of blades (1) comprising an airfoil (2), having a suction side (6), a pressure side (5), a leading edge (10), a trailing edge (7) and a blade tip (9), and comprising a blade root (3), in particular turbine blades, for thermal fluid-flow machines, characterized in that a metallic coating (8) consisting of a material identical to the parent material is applied to the blade (1), already ready for use, in the region of the blade tip (9), the thickness of the coating (8) tapering continuously at the trailing edge (7) and in the radial direction toward the blade root (3).
  2. Method according to Claim 1, characterized in that the metallic coating (8) is applied by means of a known flame spraying process.
EP03700009A 2002-01-22 2003-01-16 Method for changing the frequency of blades for thermal turbo-machines Expired - Fee Related EP1468170B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
CH00104/02A CH695461A5 (en) 2002-01-22 2002-01-22 A process for the frequency change of blades for thermal turbomachinery.
CH1042002 2002-01-22
PCT/CH2003/000022 WO2003062606A1 (en) 2002-01-22 2003-01-16 Method for changing the frequency of blades for thermal turbo-machines

Publications (2)

Publication Number Publication Date
EP1468170A1 EP1468170A1 (en) 2004-10-20
EP1468170B1 true EP1468170B1 (en) 2010-12-15

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US (1) US20050042384A1 (en)
EP (1) EP1468170B1 (en)
CH (1) CH695461A5 (en)
DE (1) DE50313322D1 (en)
WO (1) WO2003062606A1 (en)

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WO2003062606A1 (en) 2003-07-31
EP1468170A1 (en) 2004-10-20
US20050042384A1 (en) 2005-02-24
CH695461A5 (en) 2006-05-31

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