EP2137381A1 - Method for producing coated turbine blades and blade ring for a rotor of a turbine with axial flow - Google Patents

Method for producing coated turbine blades and blade ring for a rotor of a turbine with axial flow

Info

Publication number
EP2137381A1
EP2137381A1 EP08736059A EP08736059A EP2137381A1 EP 2137381 A1 EP2137381 A1 EP 2137381A1 EP 08736059 A EP08736059 A EP 08736059A EP 08736059 A EP08736059 A EP 08736059A EP 2137381 A1 EP2137381 A1 EP 2137381A1
Authority
EP
European Patent Office
Prior art keywords
blade
turbine
turbine blade
airfoil
blades
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.)
Granted
Application number
EP08736059A
Other languages
German (de)
French (fr)
Other versions
EP2137381B1 (en
Inventor
Fathi Ahmad
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 PL08736059T priority Critical patent/PL2137381T3/en
Priority to EP08736059A priority patent/EP2137381B1/en
Publication of EP2137381A1 publication Critical patent/EP2137381A1/en
Application granted granted Critical
Publication of EP2137381B1 publication Critical patent/EP2137381B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D5/14—Form or construction
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • F05D2230/10—Manufacture by removing material
    • 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
    • F05D2230/80—Repairing, retrofitting or upgrading methods
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/19—Two-dimensional machined; miscellaneous
    • 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
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49318—Repairing or disassembling
    • 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
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • 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
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49337—Composite blade
    • 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
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49339—Hollow blade
    • 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
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49718—Repairing
    • Y10T29/49721—Repairing with disassembling
    • Y10T29/49723—Repairing with disassembling including reconditioning of part
    • Y10T29/49725—Repairing with disassembling including reconditioning of part by shaping
    • Y10T29/49726—Removing material

Definitions

  • the invention relates to a method for producing a coated turbine blade in which a turbine blade is coated with at least one protective layer and wherein at least one recess is inserted into a blade tip of a blade of the turbine blade to adjust the natural frequency of the turbine blade. Furthermore, the invention relates to a blade ring for a rotor of an axial flow turbine.
  • a corrosion protection layer of the type MCrAlY is often applied to the cast turbine blade.
  • the application of the protective layer takes place in the region of its surface, which is exposed to the hot gas during operation of the gas turbine. This area includes both the blade and the platform of the turbine bucket on which the airfoil forms.
  • a heat-insulating layer can additionally be applied in the abovementioned area in order to keep the heat input from the hot gas into the base material of the turbine blade as low as possible.
  • the turbine blades are designed such that their natural frequency deviates from the excitation frequencies of the stationary gas turbine. Therefore, during the development of the turbine blade, care is taken that the finished turbine blade as a whole meets the requirements for self-resonance.
  • Turbine blade is positively influenced the vibration property. Their natural frequency can be shifted to greater natural frequencies by removing the mass, in particular at its outer end.
  • the object of the invention is to provide a method for producing coated turbine blades whose natural frequency corresponds to the requirements for use within a stationary gas turbine. Another object is to provide a blade ring, the blades of which are particularly resistant to induced by the hot gas vibrational excitation.
  • the application of a corrosion layer to a turbine blade results in a significant increase in mass, which reduces the natural frequency of the turbine blade in question.
  • the natural frequency of the turbine blade reaches near one of the excitation frequencies, so that a damaging or life-shortening vibration excitation of the turbine blade or of the blade is more probable during operation of the gas turbine.
  • Turbine blades which continuously experience vibrational excitation and oscillate continuously during operation of the gas turbine, have an increased risk of breakage and a shortened service life.
  • the load that the turbine experienced by the vibration excitation is also referred to as HCF load (High Cycle Fatigue).
  • the invention proposes, in particular, a used turbine rotor blade, which has already consumed part of its service life and is to be extended by a so-called refurbishment work-up, to be adapted for operation in the stationary gas turbine. Since the refurbishment often includes stripping of a turbine blade and recoating in the above-mentioned areas, the reclaimed turbine blade is to be subjected to a natural frequency check after coating, possibly by removing mass in the area of the blade tip of the blade. can be sert. By removing the mass at the free
  • the natural frequency is shifted away from the excitation frequencies.
  • the turbine blades then lead to a ring of turbine blades according to the invention for the rotor of a turbine, which is then especially insensitive to vapors caused by hot gas vibrational excitation.
  • a ring of turbine blades according to the invention for the rotor of a turbine, which is then especially insensitive to vapors caused by hot gas vibrational excitation.
  • all turbine blades of the ring have been produced by the method according to the invention.
  • the holes can be a drilling depth of up to 50% of - based on the installation position of the turbine blade in a stationary gas turbine - radial extent of the blade. This is possible because in this area comparatively low mechanical stresses occur in the airfoil and a weakening of the material cross section is permissible despite the high centrifugal forces.
  • a plurality of bores are performed, which are distributed along the airfoil center line. The airfoil centerline does not have to pass through the holes.
  • the holes can also be arranged laterally of the blade leaf center line entland this. Overall, this arrangement leaves the integrity and strength of the turbine blade unimpaired. It is envisaged that when a given mass is to be removed by drilling in the blade, rather a larger number of holes are to be provided with a small depth than a small number of holes with a larger depth.
  • the method may also be applied to a turbine blade having an internally coolable airfoil.
  • the bores are provided at the points of the blade, in which so-called support ribs between the suction side airfoil wall and the pressure-side airfoil wall open into this.
  • bores can also be introduced in the section of the trailing edge in which the suction side wall and pressure side wall converge.
  • it may be provided that, after the bores have been introduced, their openings are superficially sealed by means of a plug or a solder. be concluded. The holes are not filled, so that a cavity remains.
  • FIG. 3 shows a perspective view of the blade of a turbine blade with blade tip side arranged holes
  • FIG. 4 shows the cross section through an inventive, internally cooled turbine blade.
  • the method 10 for producing coated turbine blades comprises, in a first step 12, the coating of the turbine blade with a protective layer.
  • the protective layer is preferably a corrosion protection layer of the MCrAlY type.
  • a two-layer protective layer comprising as a bondcoat a layer of the type MCrAlY, on which a ceramic thermal barrier coating (TBC) has been applied further out. Since the turbine blade is cast as a rule and accordingly comprises a cast base body, by the application of the protective layer, in particular a corrosion protection layer whose mass is further increased.
  • the associated with the increase in mass change in the natural frequency of the turbine blade can by the Inserting recesses at the blade tip of the blade of the turbine blade are compensated in a second method step 14. It is provided that so many and such deep recesses are introduced into the end face of the blade of the turbine blade until the turbine blade meets the requirements of the natural frequency. It may be that despite the application of the method according to the invention, the natural frequency can not be strongly influenced enough that it meets the requirements. In this case, the turbine blade is not suitable for further use.
  • FIG. 2 shows a method 20 in which used turbine blades, that are already used during operation of a stationary gas turbine, are partially renewed by a refurbishment process - the so-called refurbishment.
  • the refurbishment serves as a lifetime extending measure for the turbine blade.
  • turbine blades are exposed to a hot gas of the gas turbine during their operation.
  • the turbine blades are removed and, if reprocessable, fed to the refurbishment process.
  • the processing process comprises a step 24 in which, if necessary, coated turbine blades are stripped. De-coating is required if, for example, there are intermediate or major cracks in the protective layer or if partial chipping or abrasion causes the actual layer thickness to shrink below a required minimum.
  • a subsequent optional step 26 cracks which may have occurred in the base material of the turbine blade are eliminated by known repair methods.
  • the turbine blade is then recoated with a single-layer or two-layer protective layer, after which, in a last step 30, holes are bored in the end face of the blade tip in the direction of a blade root of the turbine blade. Can be drilled to adjust the natural frequency bucket.
  • a turbine blade 40 is partially shown in perspective view.
  • the turbine blade 40 comprises, as is known, a blade root which is not shown in cross-section in the manner of a fir tree and is adjoined by a blade platform (not shown).
  • a freestanding blade 42 is arranged, which is aerodynamically curved in the form of a drop in cross-section.
  • the airfoil 42 includes a pressure side 44 and a suction side 46.
  • FIG. 3 only the airfoil tip 48 is shown, which lies opposite the end of the airfoil 42 fastened to the platform.
  • the aerodynamically curved airfoil 42 includes a blade centerline 50 that extends centrally between the suction side 46 and the pressure side 44 from a leading edge to a trailing edge.
  • the airfoil midline 50 is shown in phantom line style.
  • four recesses in the form of bores 52 are provided distributed along the airfoil midpoint line 50, which extend from the end face of the airfoil 42 in the direction of the blade root of the turbine blade 40.
  • FIG. runner 40 the cross section through the airfoil 42 of a turbine produced by the process according to the invention is shown in FIG. runner 40 shown.
  • the cut was placed in the area of the blade tip 48.
  • the turbine blade 40 according to FIG. 4 comprises the cast base body 41, onto which a protective layer 54 has been applied on the suction side and on the pressure side.
  • the protective layer 54 has the mass of
  • Turbine blade 40 significantly increased, which has resulted in a change of the natural frequency to lower frequencies.
  • 42 bores 52 are introduced from the end face of the blade.
  • the holes 52 are provided at the locations in the airfoil 42 at which the support ribs 56 present in the interior connect to the pressure-side or suction-side blade wall 44, 46. It can also be provided, in the region of the trailing edge of the turbine blade 40, on which the suction-side pressure wall 46 with the pressure-side
  • Blade wall 44 unites to attach the holes 52, which are preferably distributed in this section of the airfoil center line there.
  • the invention thus proposes a method for producing coated turbine blades 40 whose frequency characteristic can be adapted to the required boundary conditions in a particularly simple manner.
  • the introduction of recesses into a blade tip 48 of the airfoil 42 of the turbine blade 40 takes place after the coating of the turbine blade 40.
  • a method is specified with which the vibration characteristic of the turbine blade can be set particularly easily and variably. Scrap of turbine blades 40 can thus be reduced.
  • already used turbine blades can be prepared in a refurbishment process so that they can be reused.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Application Of Or Painting With Fluid Materials (AREA)

Abstract

The method involves coating a turbine blade (40) with a protective layer (54) and a recess is inserted in a blade vane (48) of a blade (42) of the turbine blade for adjusting the resonance frequency of the turbine blade. The recesses are introduced after coating of the turbine blade. An independent claim is also included for a blade ring for a rotor of a turbine with axial flow.

Description

Beschreibungdescription
Verfahren zum Herstellen von beschichteten Turbinenlaufschaufeln und Laufschaufelring für einen Rotor einer axial durchströmten TurbineA method of making coated turbine blades and blade ring for a rotor of an axial flow turbine
Die Erfindung betrifft ein Verfahren zum Herstellen einer beschichteten Turbinenlaufschaufel, bei dem eine Turbinenlaufschaufel mit mindestens einer Schutzschicht beschichtet wird und bei dem zur Einstellung der Eigenfrequenz der Turbinenlaufschaufel mindestens eine Ausnehmung in eine Schaufelspitze eines Schaufelblatts der Turbinenlaufschaufel eingebracht wird. Ferner betrifft die Erfindung einen Laufschaufelring für einen Rotor einer axial durchströmten Turbine.The invention relates to a method for producing a coated turbine blade in which a turbine blade is coated with at least one protective layer and wherein at least one recess is inserted into a blade tip of a blade of the turbine blade to adjust the natural frequency of the turbine blade. Furthermore, the invention relates to a blade ring for a rotor of an axial flow turbine.
Es ist bekannt, Turbinenlaufschaufeln mit einer Schutzschicht zu versehen, damit diese beim Betrieb in einer Gasturbine eine erhöhte Lebensdauer aufweisen. Als Schutzschicht wird dabei häufig eine Korrosionsschutzschicht des Typs MCrAlY auf die gegossen gefertigte Turbinenlaufschaufel aufgebracht. Die Aufbringung der Schutzschicht erfolgt dabei in dem Bereich ihrer Oberfläche, welcher im Betrieb der Gasturbine dem Heißgas ausgesetzt ist. Dieser Bereich umfasst sowohl das Schau- felblatt sowie die Plattform der Turbinenlaufschaufel, an welcher sich das Schaufelblatt anformt. Neben der Korrosionsschutzschicht kann zudem eine Wärmedämmschicht im vorgenannten Bereich aufgebracht werden, um den Wärmeeintrag aus dem Heißgas in das Grundmaterial der Turbinenlaufschaufel so ge- ring wie möglich zu halten.It is known to provide turbine blades with a protective layer so that they have an increased lifetime when operating in a gas turbine. As a protective layer, a corrosion protection layer of the type MCrAlY is often applied to the cast turbine blade. The application of the protective layer takes place in the region of its surface, which is exposed to the hot gas during operation of the gas turbine. This area includes both the blade and the platform of the turbine bucket on which the airfoil forms. In addition to the anticorrosion layer, a heat-insulating layer can additionally be applied in the abovementioned area in order to keep the heat input from the hot gas into the base material of the turbine blade as low as possible.
Des Weiteren ist bekannt, dass Turbinenlaufschaufeln einer Schwingungsanregung im Betrieb der Gasturbine ausgesetzt sind. Die Schwingungsanregung erfolgt aufgrund der Rotation des Rotors, an dem die Turbinenlaufschaufeln befestigt sind. Einen weiteren Beitrag zur Schwingungsanregung erfahren die Schaufelblätter der Turbinenlaufschaufeln durch das auf sie auftreffende Heißgas. Da die Schaufelblätter der Turbinen- laufschaufeln - in Strömungsrichtung des Heißgases gesehen - hinter einem Kranz von Turbinenleitschaufein umlaufen, werden diese durch zyklisch auftreffendes Heißgas zum Schwingen angeregt. Daher ist es erforderlich, das jede Turbinenlauf- schaufei eine ausreichend hohe Eigenfrequenz aufweist, dass sowohl die von der Rotordrehzahl als auch die vom Heißgas herrührende Schwingungsanregung mit den jeweiligen Anregungsfrequenzen nicht zu einer unzulässig hohen Schwingung des Schaufelblatts führt. Dementsprechend werden im Stand der Technik die Turbinenlaufschaufeln derartig ausgelegt, dass deren Eigenfrequenz von den Anregungsfrequenzen der stationären Gasturbine abweicht. Daher wird bei der Entwicklung der Turbinenlaufschaufel darauf geachtet, dass die fertige Turbinenlaufschaufel insgesamt den Anforderungen bezüglich der Eigenresonanz genügt.Furthermore, it is known that turbine blades are exposed to vibrational excitation during operation of the gas turbine. The vibration excitation occurs due to the rotation of the rotor to which the turbine blades are attached. Another contribution to the vibration excitation experienced by the blades of the turbine blades through the impinging hot gas. Since the blades of the turbine Rotor blades - seen in the flow direction of the hot gas - circulate behind a ring of Turbinenleitschaufein, these are excited by cyclically impinging hot gas to vibrate. It is therefore necessary that each turbine runner has a sufficiently high natural frequency that both the vibration excitation resulting from the rotor speed and the hot gas at the respective excitation frequencies does not lead to an unduly high vibration of the airfoil. Accordingly, in the prior art, the turbine blades are designed such that their natural frequency deviates from the excitation frequencies of the stationary gas turbine. Therefore, during the development of the turbine blade, care is taken that the finished turbine blade as a whole meets the requirements for self-resonance.
Im Fertigungsprozess der Turbinenlaufschaufel ist daher vorgesehen, jede einzelne Turbinenlaufschaufel auf ihre Schwingungseigenschaften zu überprüfen. Sofern die Turbinenlauf- schaufei den vorgegebenen Frequenzwerten an Eigenfrequenz nicht erfüllt, ist diese zu verwerfen oder mittels geeigneter Maßnahmen derart zu manipulieren, dass diese danach für den Betrieb geeignet ist und die Anforderungen an die Eigenfrequenz erfüllt. Um Turbinenlaufschaufeln, welche allein auf- grund Ihrer Schwingungseigenschaft nicht zum Einsatz in der Gasturbine vorgesehen sind, der Benutzung doch zuzuführen, ist bekannt, am Schaufelblatt der Turbinenlaufschaufel stirnseitig eine Ausnehmung einzubringen, wodurch die Masse der Turbinenlaufschaufel an ihrem freien, schwingfähigen Ende reduziert werden kann. Durch die Reduzierung der Masse derIn the manufacturing process of the turbine blade is therefore intended to check each turbine blade on their vibration characteristics. If the turbine rotor does not fulfill the given frequency values at natural frequency, it must be discarded or manipulated by means of suitable measures in such a way that it is subsequently suitable for operation and fulfills the requirements for the natural frequency. In order to supply turbine blades, which are not intended for use in the gas turbine alone because of their vibration property, it is known to introduce a recess on the blade of the turbine blade frontally, whereby the mass of the turbine blade can be reduced at its free, oscillatory end , By reducing the mass of
Turbinenlaufschaufel wird die Schwingungseigenschaft positiv beeinflusst. Ihre Eigenfrequenz kann durch das Entfernen der Masse, insbesondere an ihrem äußeren Ende, zu größeren Eigenfrequenzen verschoben werden.Turbine blade is positively influenced the vibration property. Their natural frequency can be shifted to greater natural frequencies by removing the mass, in particular at its outer end.
Außerdem ist bekannt, dass an zuvor in Gasturbinen eingesetzten Turbinenlaufschaufeln Maßnahmen zur Lebensdauerverlängerung durchgeführt werden. Diese Maßnahmen umfassen einerseits die Beseitigung von während des Betriebs entstandenen Rissen und andererseits die Erneuerung der auf den Turbinenlaufschaufeln vorgesehenen Schutzschichten.In addition, it is known that measures for extending the life of the turbine blades previously used in gas turbines are carried out. These measures include on the one hand the elimination of cracks generated during operation and, on the other hand, the renewal of the protective layers provided on the turbine blades.
Aufgabe der Erfindung ist die Bereitstellung eines Verfahrens zum Herstellen von beschichteten Turbinenlaufschaufeln, deren Eigenfrequenz den Anforderungen für den Einsatz innerhalb einer stationären Gasturbine entspricht. Weitere Aufgabe ist die Bereitstellung eines Laufschaufelrings, dessen Laufschaufelblätter besonders unanfällig gegen eine vom Heißgas herbeigeführte Schwingungsanregung sind.The object of the invention is to provide a method for producing coated turbine blades whose natural frequency corresponds to the requirements for use within a stationary gas turbine. Another object is to provide a blade ring, the blades of which are particularly resistant to induced by the hot gas vibrational excitation.
Die auf das Verfahren bezogene Aufgabe wird durch ein Verfahren gemäß den Merkmalen des Anspruchs 1 gelöst, wobei sich vorteilhafte Ausgestaltungen in den Unteransprüchen widerspiegeln. Die auf den Laufschaufelring bezogene Aufgabe wird durch die Merkmale des Anspruchs 9 gelöst.The object related to the method is achieved by a method according to the features of claim 1, wherein advantageous embodiments are reflected in the subclaims. The related to the blade ring task is solved by the features of claim 9.
Die Erfindung geht von der Erkenntnis aus, dass das Einbrin- gen der Ausnehmungen zur Einstellung der Eigenfrequenz nach dem Beschichten der Turbinenlaufschaufel erfolgen soll. Erst nach dem Beschichten der Turbinenlaufschaufel hat diese ihre endgültige Gestalt und ihr endgültiges Gewicht erreicht, wobei auch die Eigenfrequenz (= Resonanzfrequenz) der Turbinen- laufschaufei davon abhängt. Insbesondere das Aufbringen einer Korrosionsschicht auf eine Turbinenlaufschaufel führt zu einer signifikanten Massenzunahme, wodurch sich die Eigenfrequenz der betreffenden Turbinenlaufschaufel verkleinert. Hierdurch besteht die Gefahr, dass die Eigenfrequenz der Tur- binenlaufschaufel in die Nähe einer der Anregungsfrequenzen gelangt, so dass eine schädliche oder die Lebensdauer verkürzende Schwingungsanregung der Turbinenlaufschaufel bzw. des Schaufelblatts beim Betrieb der Gasturbine wahrscheinlicher ist. Turbinenlaufschaufeln, die während des Betriebs der Gas- turbine fortlaufend eine Schwingungsanregung erfahren und fortlaufend schwingen, weisen eine erhöhte Bruchgefahr und eine verkürzte Lebensdauer auf. Die Belastung, die die Turbi- nenschaufel durch die Schwingungsanregung erfährt, wird auch als HCF-Belastung bezeichnet (High Cycle Fatigue) .The invention is based on the recognition that the introduction of the recesses for setting the natural frequency should take place after the coating of the turbine blade. Only after the coating of the turbine blade has this reached its final shape and final weight, whereby the natural frequency (= resonance frequency) of the turbine rotor blade depends on it. In particular, the application of a corrosion layer to a turbine blade results in a significant increase in mass, which reduces the natural frequency of the turbine blade in question. As a result, there is a risk that the natural frequency of the turbine blade reaches near one of the excitation frequencies, so that a damaging or life-shortening vibration excitation of the turbine blade or of the blade is more probable during operation of the gas turbine. Turbine blades, which continuously experience vibrational excitation and oscillate continuously during operation of the gas turbine, have an increased risk of breakage and a shortened service life. The load that the turbine experienced by the vibration excitation, is also referred to as HCF load (High Cycle Fatigue).
Die Erfindung schlägt vor, insbesondere eine gebrauchte Tur- binenlaufschaufei, die bereits einen Teil ihrer Lebensdauer verbraucht hat und durch ein sog. Refurbishment - Aufarbeitung - eine Lebensdauerverlängerung erhalten soll, für den Betrieb in der stationären Gasturbine anzupassen. Da das Refurbishment häufig das Entschichten einer Turbinenlauf- schaufei umfasst sowie ein Wiederbeschichten in den vorgenannten Bereichen, ist die aufgearbeitete Turbinenlaufschaufel nach dem Beschichten einer Überprüfung der Eigenfrequenz zu unterziehen, wobei ggf. durch das Entfernen von Masse im Bereich der Schaufelspitze des Schaufelblatts diese verbes- sert werden kann. Durch die Entfernung der Masse am freienThe invention proposes, in particular, a used turbine rotor blade, which has already consumed part of its service life and is to be extended by a so-called refurbishment work-up, to be adapted for operation in the stationary gas turbine. Since the refurbishment often includes stripping of a turbine blade and recoating in the above-mentioned areas, the reclaimed turbine blade is to be subjected to a natural frequency check after coating, possibly by removing mass in the area of the blade tip of the blade. can be sert. By removing the mass at the free
Ende der Turbinenlaufschaufel wird die Eigenfrequenz von den Anregungsfrequenzen weg verschoben.At the end of the turbine blade, the natural frequency is shifted away from the excitation frequencies.
Häufig wird bei der Aufbereitung der Turbinenlaufschaufel auch ein sog. Upgrade (Modernisierung) der Gasturbine durchgeführt, was zu einer höheren Leistungsabgabe und zu einem verbesserten Wirkungsgrad der Gasturbine durch eine Erhöhung der zulässigen Heißgastemperatur führen soll. Die höhere zulässige Heißgastemperatur führen dazu, dass sowohl die Korro- sionsschutzschicht als auch die Wärmedämmschicht mit einer größeren Schichtdicke als ursprünglich geplant auf die entschichtete Turbinenschaufel aufgetragen werden muss, damit diese auch den höheren Temperaturen standhalten kann. Die größere Schichtdicke führt zu einer Zunahme an Masse. Um die Massenzunahme zu kompensieren und die ursprünglichen Schwingungseigenschaften der Turbinenlaufschaufel wieder zu erreichen, wird in die Stirnseite der Schaufelspitze des Schaufelblatts ein Loch in Richtung des Schaufelfußes der Turbinenschaufel gebohrt, wodurch die schwingungsrelevante Masse am freien Ende der Turbinenlaufschaufel entnommen werden kann. Eingebaut in den Rotor einer Turbine führen die Turbinenlaufschaufeln dann zu einem erfindungsgemäßen Ring aus Turbinenlaufschaufeln für den Rotor einer Turbine, welcher dann besondern unanfällig ist für von Heißgas herruührende Schwinungsanregung der Schaufelblätter. Vorzugsweise sind dabei alle Turbinenlaufschaufeln des Rings mit dem erfindungsgemäßen Verfahren hergestellt worden.Frequently, in the preparation of the turbine blade and a so-called. Upgrade (modernization) of the gas turbine is performed, which should lead to a higher power output and improved efficiency of the gas turbine by increasing the allowable hot gas temperature. The higher permissible hot gas temperature means that both the corrosion protection layer and the thermal barrier coating with a greater layer thickness than originally planned must be applied to the stripped turbine blade, so that it can withstand the higher temperatures. The larger layer thickness leads to an increase in mass. To compensate for the increase in mass and restore the original turbine blade vibration characteristics, a hole is drilled in the face of the blade tip of the airfoil in the direction of the blade root of the turbine blade, whereby the vibration relevant mass at the free end of the turbine blade can be removed. Installed in the rotor of a turbine, the turbine blades then lead to a ring of turbine blades according to the invention for the rotor of a turbine, which is then especially insensitive to vapors caused by hot gas vibrational excitation. Preferably, all turbine blades of the ring have been produced by the method according to the invention.
Die Bohrungen können eine Bohrtiefe von bis zu 50% der - bezogen auf die Einbaulage der Turbinenlaufschaufel in einer stationären Gasturbine - radialen Erstreckung des Schaufelblatts betragen. Dies ist möglich, da in diesem Bereich ver- gleichsweise geringe mechanische Belastungen im Schaufelblatt auftreten und eine Schwächung des Materialquerschnitts trotz der hohen Fliehkräfte zulässig ist. Vorzugsweise werden mehrere Bohrungen durchgeführt, welche entlang der Schaufelblattmittenlinie verteilt sind. Die Schaufelblattmittenlinie muss dabei nicht durch die Bohrungen hindurch verlaufen. Die Bohrungen können auch seitlich der Schaufelblattmittenlinie entland dieser angeordnet sein. Insgesamt bleibt durch diese Anordnung die Integrität und Festigkeit der Turbinenlaufschaufel unbeeinträchtigt. Es ist dabei vorgesehen, dass, wenn eine gegebene Masse durch Bohrungen im Schaufelblatt entfernt werden soll, eher eine größere Anzahl von Bohrungen mit einer geringen Bohrtiefe vorzusehen sind als eine geringe Anzahl von Bohrungen mit einer größeren Bohrtiefe.The holes can be a drilling depth of up to 50% of - based on the installation position of the turbine blade in a stationary gas turbine - radial extent of the blade. This is possible because in this area comparatively low mechanical stresses occur in the airfoil and a weakening of the material cross section is permissible despite the high centrifugal forces. Preferably, a plurality of bores are performed, which are distributed along the airfoil center line. The airfoil centerline does not have to pass through the holes. The holes can also be arranged laterally of the blade leaf center line entland this. Overall, this arrangement leaves the integrity and strength of the turbine blade unimpaired. It is envisaged that when a given mass is to be removed by drilling in the blade, rather a larger number of holes are to be provided with a small depth than a small number of holes with a larger depth.
Vorzugsweise kann das Verfahren auch bei einer Turbinenlaufschaufel angewendet werden, welche ein innen kühlbares Schaufelblatt aufweist. In diesem Fall sind die Bohrungen an den Stellen des Schaufelblatts vorzusehen, bei denen so genannte Stützrippen zwischen der saugseitigen Schaufelblattwand und der druckseitigen Schaufelblattwand in diese einmünden. Alternativ oder zusätzlich können zudem Bohrungen in dem Abschnitt der Hinterkante eingebracht werden, in dem Saugseitenwand und Druckseitenwand zusammenlaufen. Um eine Korrosion der Turbinenlaufschaufel im Inneren der Bohrungen bzw. der Ausnehmungen zu vermeiden, kann vorgesehen sein, dass nach dem Einbringen der Bohrungen deren Öffnungen mittels eines Stopfens oder eines Lots oberflächlich ver- schlössen werden. Die Bohrungen werden dabei aber nicht aufgefüllt, so dass ein Hohlraum verbleibt.Preferably, the method may also be applied to a turbine blade having an internally coolable airfoil. In this case, the bores are provided at the points of the blade, in which so-called support ribs between the suction side airfoil wall and the pressure-side airfoil wall open into this. Alternatively or additionally, bores can also be introduced in the section of the trailing edge in which the suction side wall and pressure side wall converge. In order to prevent corrosion of the turbine blade inside the bores or the recesses, it may be provided that, after the bores have been introduced, their openings are superficially sealed by means of a plug or a solder. be concluded. The holes are not filled, so that a cavity remains.
Die Erfindung wird anhand einer Zeichnung erläutert, wobei identische Bezugszeichen gleich wirkende Bauteile beschreiben .The invention will be explained with reference to a drawing, wherein identical reference numerals describe the same acting components.
Es zeigen:Show it:
FIG 1 das erfindungsgemäße Verfahren zum Herstellen von beschichteten Turbinenlaufschaufeln,1 shows the inventive method for producing coated turbine blades,
FIG 2 den Ablauf und das Verfahren zum Aufarbeiten von gebrauchten Turbinenlaufschaufeln,2 shows the procedure and the method for reprocessing used turbine blades,
FIG 3 eine perspektivische Ansicht auf das Schaufelblatt einer Turbinenlaufschaufel mit schaufelspitzseitig angeordneten Bohrungen und3 shows a perspective view of the blade of a turbine blade with blade tip side arranged holes and
FIG 4 den Querschnitt durch eine erfindungsgemäße, innengekühlte Turbinenlaufschaufel.4 shows the cross section through an inventive, internally cooled turbine blade.
Das erfindungsgemäße Verfahren 10 ist in FIG 1 dargestellt. Das Verfahren 10 zum Herstellen von beschichteten Turbinenlaufschaufeln umfasst in einem ersten Schritt 12 das Beschichten der Turbinenlaufschaufel mit einer Schutzschicht. Die Schutzschicht ist dabei vorzugsweise eine Korrosionsschutzschicht vom Typ MCrAlY. Alternativ kann auch eine zwei- lagige Schutzschicht vorgesehen sein, die als Bondcoat eine Schicht vom Typ MCrAlY umfasst, auf der weiter außen eine keramische Wärmedämmschicht (thermal barrier coat-TBC) aufgebracht worden ist. Da die Turbinenlaufschaufel in der Regel gegossen ist und dementsprechend einen gegossenen Grundkörper umfasst, wird durch das Aufbringen der Schutzschicht, insbesondere eine Korrosionsschutzschicht, deren Masse weiter erhöht. Die mit der Massenerhöhung einhergehende Veränderung der Eigenfrequenz der Turbinenlaufschaufel kann durch das Einbringen von Ausnehmungen an der Schaufelspitze des Schaufelblatts der Turbinenlaufschaufel in einem zweiten Verfahrensschritt 14 kompensiert werden. Es ist dabei vorgesehen, dass derartig viele und derartig tiefe Ausnehmungen in die Stirnseite des Schaufelblatts der Turbinenlaufschaufel eingebracht werden, bis die Turbinenlaufschaufel den Anforderungen an die Eigenfrequenz genügt. Es kann dabei sein, dass trotz der Anwendung des erfindungsgemäßen Verfahrens die Eigenfrequenz nicht stark genug beeinflusst werden kann, dass diese den Anforderungen genügt. In diesem Falle ist die Turbinenlaufschaufel für eine weitere Nutzung nicht geeignet.The method 10 according to the invention is shown in FIG. The method 10 for producing coated turbine blades comprises, in a first step 12, the coating of the turbine blade with a protective layer. The protective layer is preferably a corrosion protection layer of the MCrAlY type. Alternatively, it is also possible to provide a two-layer protective layer comprising as a bondcoat a layer of the type MCrAlY, on which a ceramic thermal barrier coating (TBC) has been applied further out. Since the turbine blade is cast as a rule and accordingly comprises a cast base body, by the application of the protective layer, in particular a corrosion protection layer whose mass is further increased. The associated with the increase in mass change in the natural frequency of the turbine blade can by the Inserting recesses at the blade tip of the blade of the turbine blade are compensated in a second method step 14. It is provided that so many and such deep recesses are introduced into the end face of the blade of the turbine blade until the turbine blade meets the requirements of the natural frequency. It may be that despite the application of the method according to the invention, the natural frequency can not be strongly influenced enough that it meets the requirements. In this case, the turbine blade is not suitable for further use.
In FIG 2 ist ein Verfahren 20 dargestellt, bei dem gebrauchte, d.h. bereits im Betrieb einer stationären Gastur- bine eingesetzte Turbinenlaufschaufeln durch einen Aufarbei- tungsprozess - das so genannte Refurbishment - teilerneuert werden. Das Refurbishment dient als eine die Lebensdauer verlängernde Maßnahme für die Turbinenlaufschaufel. Demnach werden Turbinenlaufschaufeln in einem ersten Verfahrensschritt 22 einem Heißgas der Gasturbine bei deren Betrieb ausgesetzt. Während einer Inspektion bzw. Revision der Gasturbine werden die Turbinenlaufschaufeln ausgebaut und, sofern wiederaufar- beitbar, dem Aufarbeitungsprozess zugeführt. Der Aufarbei- tungsprozess umfasst dabei einen Schritt 24, in dem gegeben- enfalls beschichtete Turbinenlaufschaufeln entschichtet werden. Die EntSchichtung ist erforderlich, wenn beispielsweise mittlere oder größere Risse in der Schutzschicht vorhanden sind oder Teilabplatzungen oder Abrieb die tatsächliche Schichtdicke unter ein erforderliches Mindestmaß schrumpfen ließen. In einem nachfolgenden optionalen Schritt 26 sind gegebenenfalls im Grundmaterial der Turbinenlaufschaufel entstandene Risse durch bekannte Reparaturverfahren zu eliminieren. In einem weiteren Schritt 28 erfolgt dann das Wiederbeschichten der Turbinenlaufschaufel mit einer einlagigen oder zweilagigen Schutzschicht, wonach abschließend in einem letzten Schritt 30 das Bohren von Löchern in die Stirnseite der Schaufelspitze in Richtung eines Schaufelfußes der Turbinen- laufschaufel zur Einstellung der Eigenfrequenz gebohrt werden können .FIG. 2 shows a method 20 in which used turbine blades, that are already used during operation of a stationary gas turbine, are partially renewed by a refurbishment process - the so-called refurbishment. The refurbishment serves as a lifetime extending measure for the turbine blade. Accordingly, in a first method step 22 turbine blades are exposed to a hot gas of the gas turbine during their operation. During an inspection or revision of the gas turbine, the turbine blades are removed and, if reprocessable, fed to the refurbishment process. The processing process comprises a step 24 in which, if necessary, coated turbine blades are stripped. De-coating is required if, for example, there are intermediate or major cracks in the protective layer or if partial chipping or abrasion causes the actual layer thickness to shrink below a required minimum. In a subsequent optional step 26, cracks which may have occurred in the base material of the turbine blade are eliminated by known repair methods. In a further step 28, the turbine blade is then recoated with a single-layer or two-layer protective layer, after which, in a last step 30, holes are bored in the end face of the blade tip in the direction of a blade root of the turbine blade. Can be drilled to adjust the natural frequency bucket.
In FIG 3 ist eine Turbinenlaufschaufel 40 teilweise in per- spektivischer Darstellung gezeigt. Die Turbinenlaufschaufel 40 umfasst bekanntermaßen einen nicht dargestellten im Querschnitt tannenbaumförmigen Schaufelfuß, an dem sich eine nicht dargestellte Schaufelplattform anschließt. An der Schaufelplattform ist ein freistehendes Schaufelblatt 42 an- geordnet, welches im Querschnitt tropfenförmig ausgebildet aerodynamisch gekrümmt ist. Das Schaufelblatt 42 umfasst eine Druckseite 44 und eine Saugseite 46. In FIG 3 ist lediglich die Schaufelblattspitze 48 dargestellt, welcher dem an der Plattform befestigten Ende des Schaufelblatts 42 gegenüber- liegt. Zwischen der Schaufelblattspitze 48 und der Plattform weist das Schaufelblatt 42 eine Höhe H auf, welche, bezogen auf ihre Einbaulage in einer axial durchströmten stationären Gasturbine, in Richtung der Radialrichtung erfasst werden kann. Das aerodynamisch gekrümmte Schaufelblatt 42 umfasst eine Schaufelmittenlinie 50, welche mittig zwischen der Saugseite 46 und der Druckseite 44 von einer Anströmkante zu einer Hinterkante verläuft. Die Schaufelblattmittenlinie 50 ist in strichpunktierter Linienart dargestellt. Entlang der Schaufelblattmittenlinie 50 verteilt sind beispielsweise vier Ausnehmungen in Form von Bohrungen 52 vorgesehen, welche sich von der Stirnseite des Schaufelblatts 42 in Richtung des Schaufelfußes der Turbinenlaufschaufel 40 erstrecken. Mittels der Bohrungen 52 wurde am freien Ende der Turbinenlaufschaufel 40 das Gewicht reduziert, wodurch die Eigenfrequenz zu höheren Frequenzen verschoben worden ist.In FIG. 3, a turbine blade 40 is partially shown in perspective view. The turbine blade 40 comprises, as is known, a blade root which is not shown in cross-section in the manner of a fir tree and is adjoined by a blade platform (not shown). On the blade platform, a freestanding blade 42 is arranged, which is aerodynamically curved in the form of a drop in cross-section. The airfoil 42 includes a pressure side 44 and a suction side 46. In FIG. 3, only the airfoil tip 48 is shown, which lies opposite the end of the airfoil 42 fastened to the platform. Between the blade tip 48 and the platform, the blade 42 has a height H, which, based on its installation position in an axially flowed stationary gas turbine, can be detected in the radial direction. The aerodynamically curved airfoil 42 includes a blade centerline 50 that extends centrally between the suction side 46 and the pressure side 44 from a leading edge to a trailing edge. The airfoil midline 50 is shown in phantom line style. For example, four recesses in the form of bores 52 are provided distributed along the airfoil midpoint line 50, which extend from the end face of the airfoil 42 in the direction of the blade root of the turbine blade 40. By means of the holes 52, the weight was reduced at the free end of the turbine blade 40, whereby the natural frequency has been shifted to higher frequencies.
Mittels der stirnseitig angeordneten Bohrungen kann ungefähr eine 10%ige Frequenzverschiebung der Eigenfrequenz erfolgen. Das in FIG 3 dargestellte Schaufelblatt 42 ist dabei unge- kühlt.By means of the bores arranged on the front side approximately a 10% frequency shift of the natural frequency can take place. The airfoil 42 shown in FIG. 3 is uncooled.
In FIG 4 ist der Querschnitt durch das Schaufelblatt 42 einer nach dem erfindungsgemäßen Verfahren hergestellten Turbinen- laufschaufei 40 gezeigt. Der Schnitt wurde dabei in den Bereich der Schaufelblattspitze 48 gelegt. Die Turbinenschaufel 40 gemäß FIG 4 umfasst den gegossenen Grundkörper 41, auf den saugseitig als auch druckseitig eine Schutzschicht 54 aufge- bracht worden ist. Die Schutzschicht 54 hat die Masse der4, the cross section through the airfoil 42 of a turbine produced by the process according to the invention is shown in FIG. runner 40 shown. The cut was placed in the area of the blade tip 48. The turbine blade 40 according to FIG. 4 comprises the cast base body 41, onto which a protective layer 54 has been applied on the suction side and on the pressure side. The protective layer 54 has the mass of
Turbinenlaufschaufel 40 signifikant erhöht, wodurch sich eine Änderung der Eigenfrequenz zu geringeren Frequenzen ergeben hat. Um diese Verschiebung der Eigenfrequenz zu kompensieren, werden von der Stirnseite des Schaufelblatts 42 Bohrungen 52 eingebracht. Die Bohrungen 52 sind an den Stellen im Schaufelblatt 42 vorgesehen, an denen sich die im Inneren vorhandenen Stützrippen 56 mit der druckseitigen oder saugseitigen Schaufelwand 44, 46 verbinden. Auch kann vorgesehen sein, im Bereich der Hinterkante der Turbinenlaufschaufel 40, an dem sich die saugseitige Druckwand 46 mit der druckseitigenTurbine blade 40 significantly increased, which has resulted in a change of the natural frequency to lower frequencies. In order to compensate for this shift in the natural frequency, 42 bores 52 are introduced from the end face of the blade. The holes 52 are provided at the locations in the airfoil 42 at which the support ribs 56 present in the interior connect to the pressure-side or suction-side blade wall 44, 46. It can also be provided, in the region of the trailing edge of the turbine blade 40, on which the suction-side pressure wall 46 with the pressure-side
Schaufelwand 44 vereint, die Bohrungen 52 anzubringen, welche dabei vorzugsweise in diesem Abschnitt der Schaufelblattmittenlinie dort verteilt sind.Blade wall 44 unites to attach the holes 52, which are preferably distributed in this section of the airfoil center line there.
Insgesamt schlägt somit die Erfindung ein Verfahren zum Herstellen von beschichteten Turbinenlaufschaufeln 40 vor, deren Frequenzeigenschaft besonders einfach an die erforderlichen Randbedingungen angepasst werden kann. Hierzu ist vorgesehen, dass das Einbringen von Ausnehmungen in eine Schaufelspitze 48 des Schaufelblatts 42 der Turbinenschaufel 40 nach dem Beschichten der Turbinenlaufschaufel 40 erfolgt. Hierdurch ist eine Methode angegeben, mit der die Schwingungseigenschaft der Turbinenschaufel besonders einfach und variabel eingestellt werden kann. Ausschuss von Turbinenlaufschaufeln 40 kann somit reduziert werden. Ebenso ist es möglich, eine aufgrund von Designänderungen sonst unbrauchbar gewordene Turbinenschaufel derartig anzupassen, dass sie zumindest den Anforderungen bezüglich der Eigenfrequenz wieder genügt. Auch können mit dem erfindungsgemäßen Verfahren bereits gebrauchte Turbinenschaufeln in einem Refurbishment-Prozess so aufbereitet werden, dass sie wiederverwendet werden können. Overall, the invention thus proposes a method for producing coated turbine blades 40 whose frequency characteristic can be adapted to the required boundary conditions in a particularly simple manner. For this purpose, it is provided that the introduction of recesses into a blade tip 48 of the airfoil 42 of the turbine blade 40 takes place after the coating of the turbine blade 40. In this way, a method is specified with which the vibration characteristic of the turbine blade can be set particularly easily and variably. Scrap of turbine blades 40 can thus be reduced. Likewise, it is possible to adapt a turbine blade otherwise unusable due to design changes in such a way that it at least meets the requirements with respect to the natural frequency again. Also, with the inventive method already used turbine blades can be prepared in a refurbishment process so that they can be reused.

Claims

Patentansprüche claims
1. Verfahren (10, 20) zum Herstellen einer beschichteten Turbinenlaufschaufel (40), bei dem eine Turbinenlaufschaufel (40) mit mindestens einer Schutzschicht (54) beschichtet wird und bei dem zur Einstellung der Eigenfrequenz der Turbinenlaufschaufel (40) mindestens eine Ausnehmung in eine Schaufelspitze (48) eines Schaufelblatts (42) der Turbinenlaufschaufel (40) eingebracht wird, dadurch gekennzeichnet, dass das Einbringen der Ausnehmung nach dem Beschichten der Turbinenlaufschaufel (40) erfolgt.A method (10, 20) for producing a coated turbine blade (40) in which a turbine blade (40) is coated with at least one protective layer (54) and at least one recess for adjusting the natural frequency of the turbine blade (40) Blade tip (48) of a blade (42) of the turbine blade (40) is introduced, characterized in that the introduction of the recess after the coating of the turbine blade (40) takes place.
2. Verfahren (10, 20) nach Anspruch 1, bei dem als Ausnehmung ein Loch (52) in die Schaufelspitze (48) in Richtung eines Schaufelfußes der Turbinenlaufschaufeln (40) gebohrt wird.2. The method (10, 20) according to claim 1, wherein as a recess a hole (52) in the blade tip (48) in the direction of a blade root of the turbine blades (40) is drilled.
3. Verfahren (10, 20) nach Anspruch 1 oder 2, bei dem die Bohrtiefe bis zu 50% der - bezogen auf die Einbaulage der Turbinenlaufschaufel (40) - radialen Erstreckung des Schaufelblatts (42) beträgt.3. The method (10, 20) according to claim 1 or 2, wherein the drilling depth is up to 50% of - based on the installation position of the turbine blade (40) - radial extent of the airfoil (42).
4. Verfahren (10, 20) nach einem der Ansprüche 1 bis 3, bei dem mehrere Bohrungen (52) durchgeführt werden, welche entlang der Schaufelblattmittenlinie (50) verteilt sind.4. The method (10, 20) according to any one of claims 1 to 3, wherein a plurality of bores (52) are performed, which are distributed along the airfoil center line (50).
5. Verfahren (10, 20) nach einem der Ansprüche 1 bis 4, welches nach dem Entschichten einer Turbinenlaufschaufel5. The method (10, 20) according to any one of claims 1 to 4, which after stripping a turbine blade
(40) durchgeführt wird.(40).
6. Verfahren (10 ,20) einem der Ansprüche 1 bis 5, welches auf eine Turbinenlaufschaufel (40) mit einem innenkühlbaren Schaufelblatt (42) angewendet wird. A method (10, 20) according to any one of claims 1 to 5, which is applied to a turbine blade (40) having an internally-cooled airfoil (42).
7. Verfahren (10, 20) nach einem der vorangehenden Ansprüche, bei dem die Ausnehmungen wieder verschlossen werden.7. The method (10, 20) according to any one of the preceding claims, wherein the recesses are closed again.
8. Verfahren (10, 20) nach einem der vorangehenden Ansprüche, bei dem als Schutzschicht (54) eine Korrosionsschutzschicht und/oder Wärmedämmschicht auf die Turbinenlaufschaufel aufgebracht wird.8. The method (10, 20) according to any one of the preceding claims, wherein the protective layer (54) a corrosion protection layer and / or thermal barrier coating is applied to the turbine blade.
9. Laufschaufelring für einen Rotor einer axial durchströmten Turbine, mit einer Anzahl von Turbinenlaufschaufeln, welche nach einem Verfahren nach einem der Ansprüche 1 bis 8 hergestellt sind.9. A blade ring for a rotor of an axial flow turbine, with a number of turbine blades, which are prepared by a method according to any one of claims 1 to 8.
10. Laufschaufelring nach Anspruch 9, bei dem alle Turbinenlaufschaufeln nach einem Verfahren der Ansprüche 1 bis 8 hergestellt sind 10. Blade ring according to claim 9, wherein all the turbine blades are produced by a method of claims 1 to 8
EP08736059A 2007-04-23 2008-04-10 Method for producing coated turbine blades Not-in-force EP2137381B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PL08736059T PL2137381T3 (en) 2007-04-23 2008-04-10 Method for producing coated turbine blades
EP08736059A EP2137381B1 (en) 2007-04-23 2008-04-10 Method for producing coated turbine blades

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP07008237A EP1985803A1 (en) 2007-04-23 2007-04-23 Process for manufacturing coated turbine blades
PCT/EP2008/054338 WO2008128902A1 (en) 2007-04-23 2008-04-10 Method for producing coated turbine blades and blade ring for a rotor of a turbine with axial flow
EP08736059A EP2137381B1 (en) 2007-04-23 2008-04-10 Method for producing coated turbine blades

Publications (2)

Publication Number Publication Date
EP2137381A1 true EP2137381A1 (en) 2009-12-30
EP2137381B1 EP2137381B1 (en) 2010-09-29

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EP07008237A Withdrawn EP1985803A1 (en) 2007-04-23 2007-04-23 Process for manufacturing coated turbine blades
EP08736059A Not-in-force EP2137381B1 (en) 2007-04-23 2008-04-10 Method for producing coated turbine blades

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EP07008237A Withdrawn EP1985803A1 (en) 2007-04-23 2007-04-23 Process for manufacturing coated turbine blades

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US (1) US8607455B2 (en)
EP (2) EP1985803A1 (en)
JP (1) JP2010525229A (en)
CN (1) CN101663465B (en)
AT (1) ATE483097T1 (en)
CA (1) CA2684810C (en)
DE (1) DE502008001450D1 (en)
ES (1) ES2353358T3 (en)
MX (1) MX2009010923A (en)
PL (1) PL2137381T3 (en)
RU (1) RU2430239C2 (en)
WO (1) WO2008128902A1 (en)

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Also Published As

Publication number Publication date
JP2010525229A (en) 2010-07-22
CA2684810A1 (en) 2008-10-30
RU2009142996A (en) 2011-05-27
RU2430239C2 (en) 2011-09-27
CN101663465B (en) 2013-07-31
EP2137381B1 (en) 2010-09-29
EP1985803A1 (en) 2008-10-29
ES2353358T3 (en) 2011-03-01
PL2137381T3 (en) 2011-04-29
DE502008001450D1 (en) 2010-11-11
US20100129554A1 (en) 2010-05-27
MX2009010923A (en) 2009-11-02
CN101663465A (en) 2010-03-03
WO2008128902A1 (en) 2008-10-30
ATE483097T1 (en) 2010-10-15
CA2684810C (en) 2013-02-05
US8607455B2 (en) 2013-12-17

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