EP3362648A1 - Method for producing a base body of a turbine blade - Google Patents

Method for producing a base body of a turbine blade

Info

Publication number
EP3362648A1
EP3362648A1 EP16812708.2A EP16812708A EP3362648A1 EP 3362648 A1 EP3362648 A1 EP 3362648A1 EP 16812708 A EP16812708 A EP 16812708A EP 3362648 A1 EP3362648 A1 EP 3362648A1
Authority
EP
European Patent Office
Prior art keywords
blade
turbine
turbine blade
base body
platform
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
EP16812708.2A
Other languages
German (de)
French (fr)
Other versions
EP3362648B1 (en
Inventor
Fathi Ahmad
Radan RADULOVIC
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
Publication of EP3362648A1 publication Critical patent/EP3362648A1/en
Application granted granted Critical
Publication of EP3362648B1 publication Critical patent/EP3362648B1/en
Active 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/027—Arrangements for balancing
    • 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
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F05D2230/60—Assembly methods
    • F05D2230/61—Assembly methods using limited numbers of standard modules which can be adapted by machining
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • the invention relates to a method for producing a base body of a turbine blade, comprising at least the successive steps, providing the basic body, which along a virtual longitudinal axis successively comprises a blade root, a blade platform and an airfoil, detecting a value of a parameter representing a vibration characteristic of
  • the invention relates to a blade ring for a rotor of an axially flowed through turbine.
  • a corrosion protective layer of the MCrAlY type is frequently ⁇ fig ⁇ be applied to the produced in a casting process turbine blade.
  • the application of the protective layer takes place in the area of that surface which during operation is exposed to the hot gas of the gas turbine.
  • This range includes both the airfoil and the platform of the turbine ⁇ shovel to which the airfoil anformt.
  • a heat insulating layer within the aforementioned range may be applied to keep the heat input from the hot gas into the base material of the turbine ⁇ shovel as low as possible. The application of the layers thereby alters the vibration behavior of the turbine blade.
  • Hot gas-based vibration excitation with the respective excitation frequencies does not lead to an unduly high vibration of the blade. 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. In the development of the turbine blade is also taken to ensure that the finished turbine blade total meets the requirements be ⁇ lug the natural resonance, even in terms of to be expected rotor speeds.
  • Vibration response of the turbine blade and in particular ih ⁇ res airfoil detected Provided that the vibratory response of the turbine blade does not satisfy the predetermined frequency values at natural frequency, this is to be discarded or to manipulate ⁇ means of suitable measures so that it is meets the requirements of the natural frequency and therefore suitable for the operation.
  • a recess, a ⁇ accommodated in the tip of the blade whereby the Mass of the turbine blade at its rem free, swingable end can be reduced.
  • the vibration characteristic is positively influenced.
  • Their Eigenfre ⁇ frequency can be moved by removing the mass to higher values.
  • the object of the invention is to provide a method for producing basic bodies of turbine blades, the natural frequencies of which correspond to the requirements for use within a stationary gas turbine. Another object is the provision of a blade ring, ⁇ sen running blades particularly robust against one of
  • the invention is based on the realization that the Einbrin ⁇ gen of the recesses must be made to adjust the natural frequency, not only on the airfoil.
  • the measure for influencing the vibration properties of the turbine blades or of their cast base body can also take place on the blade root or on the so-called platform underside.
  • the platform underside is that side of the platform of a turbine blade or the base body, which faces the hot gas side of the platform and thus faces the blade root.
  • the introduction of recesses or the reduction of a Dimension be provided below the setpoint.
  • both measures could be combined with each other.
  • the advantages of both measures is that they do not change the constructive ⁇ turmechanische integrity of the blade worsen the aerodynamics. This makes it possible to achieve the predetermined life span and power values of the blade body or the turbine blade ultimately resulting therefrom.
  • the invention proposes that the blade root on the blade root and / or on the underside of the platform has an area whose shape and / or dimensions are chosen so that they have no structural mechanical functions. Due to this property and the dimensions originally provided, the base body comprises at least one region which is regarded as a sacrificial region in order to modify the vibration properties of the base body by reducing the mass there without the functional properties changing as well. To reduce the mass, for example, a recess can be made in a planar side of the blade root. Another example is the reduction of the width of a web which is provided on the platform underside of the turbine blade.
  • the areas are located there, where the measures described above can be carried out without changing the time required for the occurring during the operation of relevant mechanical stress devischa ⁇ African integrity of the base body significantly 29lech ⁇ tert. Consequently, those moments of inertia and that rigidity of the turbine blade to be changed, which border the life of the turbine blade in any case not be ⁇ .
  • the range in question is or are the ⁇ be taken of those areas outside surfaces of the body which are überströmbar of a hot gas.
  • the method can also be applied after the coating of turbine blades with an erosion and / or thermal barrier coating.
  • the method according to the invention is applied in a rather late phase of the manufacturing process of the turbine blades.
  • the base body usually produced in the casting process has already been brought to the specified size before the value of the parameter representing a vibration characteristic is detected.
  • This ensures that the vibration measurement is carried out on the almost finished turbine blade and thus further Fer ⁇ tion steps that can change the vibration characteristics of the body or the turbine blade, at least largely avoided.
  • the method can also prior to the coat of the base body are performed when ahead determinable by which the (average) value of the detected value of Para ⁇ meters due to the then subsequently applied coating changes.
  • the aforementioned measures can be carried out in order to select those basic body whose vibration characteristics and values could not be transferred into the associated target intervals despite the implementation of the inventive measures. In this way, the expense of waste can be avoided at an early stage.
  • FIG. 1 shows a flowchart with the different production steps of a method according to the invention for producing a main body of a turbine blade
  • FIG. 2 shows a flowchart with further manufacturing steps
  • FIG. 3 shows a perspective view of an underside of a base body of a turbine blade.
  • the method 10 according to the invention is shown in FIG.
  • the method 10 for producing a main body 30 (FIG.
  • a turbine blade comprises in a first step 12, the provision of the main body 30 of the turbine blade ⁇ blade.
  • the main body 30 comprises along a virtual Longitudinal axis 31 successively a blade root 32, a platform 34 and an airfoil 36th
  • the contour of the blade root 32 is fir-tree-shaped when viewed perpendicularly on its planar end face 38 and merges via a so-called blade neck 40 into an underside 42 of the platform 34.
  • the platform Opposite the underside 42, the platform has a hot gas side 44, at which the airfoil 36 connects monolithically. This is drop-shaped and aerodynamically curved to form a pressure side 46 and a suction side 48.
  • the blade root 32 extends over a length L between the two axially opposite planar end faces 38.
  • a size of at least one parameter of the base body 30 is detected, wherein at least one of the parameters represents a vibration property of the base body.
  • the egg ⁇ gene frequencies and the vibration modes are detected by the usual methods.
  • a third production step 16 the detected value (s) is compared with an (associated) target interval. If the detected values lie outside the associated target interval, according to the invention vibration-altering measures are carried out on the blade root 32 and / or on the underside 42 of the platform as the fourth production step.
  • These can be the introduction of one or more recesses 50 and / or the reduction of the previous dimensions such as length, width or height of certain features arranged there.
  • the County ⁇ ge L of the blade root can be shortened by a few hundredths of a millimeter to a level 32 which is below the otherwise provided target value for the length L.
  • the reduction of the mass of the main body 30 takes place in the region 49, which were provided in particular for it. This changes the weight and possibly the contact surface of the turbine run ⁇ fel under centrifugal force, which has a favorable effect on the vibration property of the turbine blade. If in doubt, the second, third and fourth and fourth
  • Steps 14, 16, 18 repeatedly executed as a series to check the suitability of the base body 30. Only when the un ⁇ ters visited turbine blades meets the requirements in terms of vibration property, this whe- the reindeer manufacturing process is passed.
  • the base body 30 or the turbine blade may also be one which is or should be provided with a protective layer.
  • the protective layer is preferably a corrosion protection layer of the type
  • Protective layer may be provided, which comprises as a bondcoat a layer of the type MCrAlY on which a ceramic thermal barrier coating (TBC) has been applied further out.
  • TBC ceramic thermal barrier coating
  • the coating of the main body 30 can be carried out before the first execution of the second production step 14 or after the last time the fourth production step 18 is carried out.
  • recess 50 is a frequency shift of the natural frequency.
  • the shape of the recesses 50 is arbitrary.
  • FIG. 2 shows a second flowchart for a further embodiment of a manufacturing method.
  • the manufacturing method includes the previously mentioned steps 12, 14, 16, 18, supplemented by partial DA between intended preparation steps 13 and 19, the preparation step 13 in which the base body 30 was He ⁇ supplemented on the one hand made at least largely to size becomes.
  • a hitherto uncoated base body 30 can be provided with an erosion and / or thermal barrier coating.
  • the invention thus proposes a method for producing turbine blades or their basic bodies 30, whose frequency characteristic can be adapted particularly easily to the required boundary conditions.
  • a method is specified with which the vibration characteristic of the turbine blade can be set particularly easily and variably. This allows the off ⁇ scrap rates in the production of turbine blades re- cuted be.

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)

Abstract

The invention relates to a method for producing turbine rotor blades or the base bodies (30) thereof, the frequency property of which can be adapted particularly easily to the required boundary conditions. To this end, recesses (50) are introduced into the blade root (32) and/or by reducing a dimension below the corresponding target value if the base body has (30) insufficient vibrational properties. In this way, a method is disclosed in which the vibrational property of the turbine rotor blades can be set in a particularly easy and variable manner. As a result, the reject rate in the production of turbine rotor blades can be reduced.

Description

Beschreibung description
Verfahren zum Herstellen eines Grundkörpers einer Turbinenschaufel Method for producing a base body of a turbine blade
Die Erfindung betrifft ein Verfahren zum Herstellen eines Grundkörpers einer Turbinenlaufschaufel, umfassend zumindest die aufeinander folgenden Schritte, Bereitstellen des Grundkörpers, welcher entlang einer virtuellen Längsachse aufei- nander folgend einen Schaufelfuß, eine Schaufelplattform und ein Schaufelblatt umfasst, Erfassen eines Werts eines eine Schwingungseigenschaft repräsentierenden Parameters des The invention relates to a method for producing a base body of a turbine blade, comprising at least the successive steps, providing the basic body, which along a virtual longitudinal axis successively comprises a blade root, a blade platform and an airfoil, detecting a value of a parameter representing a vibration characteristic of
Grundkörpers, Vergleichen des erfassten Werts mit einem vorgegeben Ziel-Intervall und sofern der erfasste Wert außerhalb des Ziel-Intervalls liegt, Reduzieren der Masse der Grundkör¬ pers. Ferner betrifft die Erfindung einen Laufschaufelring für einen Rotor einer axial durchströmten Turbine. Base body, comparing the detected value with a predetermined target interval and if the detected value is outside the target interval, reducing the mass of Grundkör ¬ pers. Furthermore, the invention relates to a blade ring for a rotor of an axially flowed through turbine.
Es ist bekannt, Turbinenlaufschaufeln mit einer Schutzschicht zu versehen, damit diese beim Betrieb in einer Gasturbine ei¬ ne erhöhte Lebensdauer aufweisen. Als Schutzschicht wird häu¬ fig eine Korrosionsschutzschicht des Typs MCrAlY auf die in einem Gießverfahren hergestellte Turbinenlaufschaufel aufge¬ bracht. Die Aufbringung der Schutzschicht erfolgt in dem Be- reich derjenigen Oberfläche, welcher im Betrieb dem Heißgas der Gasturbine ausgesetzt ist. Dieser Bereich umfasst sowohl das Schaufelblatt als auch die Plattform der Turbinenlauf¬ schaufel, 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 Turbinenlauf¬ schaufel so gering wie möglich zu halten. Das Aufbringen der Schichten verändert dabei das Schwingungsverhalten der Turbinenlaufschaufel . It is known to provide turbine blades with a protective layer so that they have ei ¬ ne increased life during operation in a gas turbine. As the protective layer, a corrosion protective layer of the MCrAlY type is frequently ¬ fig ¬ be applied to the produced in a casting process turbine blade. The application of the protective layer takes place in the area of that surface which during operation is exposed to the hot gas of the gas turbine. This range includes both the airfoil and the platform of the turbine ¬ shovel to which the airfoil anformt. In addition to the corrosion protection layer also a heat insulating layer within the aforementioned range may be applied to keep the heat input from the hot gas into the base material of the turbine ¬ shovel as low as possible. The application of the layers thereby alters the vibration behavior of the turbine blade.
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, dass jede Turbinenlauf¬ schaufel eine ausreichend hohe Eigenfrequenz aufweist, so dass sowohl die von der Rotordrehzahl als auch die vom 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 blades - viewed in the direction of flow of the hot gas - rotate behind a ring of Turbinenleitschaufein, they are excited by cyclically impinging hot gas to vibrate. It is therefore necessary for each turbine blade to have a sufficiently high natural frequency, so that both the rotor speed and the speed of rotation of the rotor blade are equal to each other
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 ausge- legt, dass deren Eigenfrequenz von den Anregungsfrequenzen der stationären Gasturbine abweicht. Bei der Entwicklung der Turbinenlaufschaufel wird zudem darauf geachtet, dass die fertige Turbinenlaufschaufel insgesamt den Anforderungen be¬ züglich der Eigenresonanz, auch im Hinblick auf die zu erwar- tenden Rotordrehzahlen genügt. Hot gas-based vibration excitation with the respective excitation frequencies does not lead to an unduly high vibration of the blade. 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. In the development of the turbine blade is also taken to ensure that the finished turbine blade total meets the requirements be ¬ züglich the natural resonance, even in terms of to be expected rotor speeds.
Im Fertigungsprozess der Turbinenlaufschaufel ist daher vor¬ gesehen, jede einzelne Turbinenlaufschaufel auf ihre Schwin¬ gungseigenschaften zu überprüfen. Bei dieser Überprüfung wird die Turbinenschaufel fußseitig eingespannt und per mechani¬ schem Impuls zum Schwingen angeregt. Daraufhin wird die In the manufacturing process of the turbine blade is therefore seen ¬ to review every turbine blade on their oscillations ¬ transfer properties. In this review, the turbine blade root side clamped and excited by mechanical ¬ schem pulse to vibrate. Then the
Schwingungsantwort der Turbinenschaufel und insbesondere ih¬ res Schaufelblattes erfasst. Sofern die Schwingungsantwort der Turbinenlaufschaufel den vorgegebenen Frequenzwerten an Eigenfrequenz nicht erfüllt, ist diese zu verwerfen oder mit¬ tels geeigneter Maßnahmen derart zu manipulieren, dass diese die Anforderungen an die Eigenfrequenz erfüllt und somit für den Betrieb geeignet ist. Um Turbinenlaufschaufeln, welche allein aufgrund Ihrer Schwingungseigenschaft nicht zum Ein- satz in der Gasturbine vorgesehen sind, der Benutzung doch zuzuführen, ist beispielsweise aus der EP 1 985 803 AI be¬ kannt, in der Spitze des Schaufelblatts eine Ausnehmung ein¬ zubringen, wodurch die Masse der Turbinenlaufschaufel an ih- rem freien, schwingfähigen Ende reduziert werden kann. Durch die Reduzierung der Masse der Turbinenlaufschaufel wird die Schwingungseigenschaft positiv beeinflusst. Ihre Eigenfre¬ quenz kann durch das Entfernen der Masse zu höheren Werten verschoben werden. Vibration response of the turbine blade and in particular ih ¬ res airfoil detected. Provided that the vibratory response of the turbine blade does not satisfy the predetermined frequency values at natural frequency, this is to be discarded or to manipulate ¬ means of suitable measures so that it is meets the requirements of the natural frequency and therefore suitable for the operation. In order, but to supply the turbine blades, which are not provided solely because of their vibration characteristic for switching set in the gas turbine using, for example, from EP 1985803 AI be ¬ known, a recess, a ¬ accommodated in the tip of the blade, whereby the Mass of the turbine blade at its rem free, swingable end can be reduced. By reducing the mass of the turbine blade, the vibration characteristic is positively influenced. Their Eigenfre ¬ frequency can be moved by removing the mass to higher values.
Daneben ist aus der EP 0 537 922 AI bekannt, in die Schaufel¬ plattform einer Turbinenlaufschaufel ein rohrförmigen Dämpfer einzusetzen. Dieser kann unter Fliehkraft sich geringfügig herausschieben und so zur Anlage an einer Plattform einerIt is also known from EP 0537922 Al to use a tubular damper in the blade ¬ platform of a turbine blade. This can slightly push out under centrifugal force and so to invest in a platform of a
Nachbarschaufel gelangen, um während des Betriebs Schaufel- zu-Schaufel-Schwingungen zu dämpfen. Neighboring scoop to dampen blade-to-blade vibrations during operation.
Aufgabe der Erfindung ist die Bereitstellung eines Verfahrens zum Herstellen von Grundkörpern von Turbinenlaufschaufeln, deren Eigenfrequenzen den Anforderungen für den Einsatz innerhalb einer stationären Gasturbine entsprechen. Weitere Aufgabe ist die Bereitstellung eines Laufschaufelrings , des¬ sen LaufSchaufelblätter besonders robust gegen eine vom The object of the invention is to provide a method for producing basic bodies of turbine blades, the natural frequencies of which correspond to the requirements for use within a stationary gas turbine. Another object is the provision of a blade ring, ¬ sen running blades particularly robust against one of
Heißgas herbeigeführte Schwingungsanregung sind. Hot gas induced vibrational excitation.
Die auf das Verfahren bezogene Aufgabe wird durch ein Verfah¬ ren gemäß den Merkmalen des Anspruchs 1 gelöst, wobei sich vorteilhafte Ausgestaltungen in den Unteransprüchen wider- spiegeln. Die auf den Laufschaufelring bezogene Aufgabe wird durch die Merkmale des Anspruchs 6 gelöst. The object relating to the method is achieved by a procedural ¬ ren according to the features of claim 1, wherein advantageous embodiments in the dependent claims reflect contradictory. The related to the blade ring task is solved by the features of claim 6.
Die Erfindung geht von der Erkenntnis aus, dass das Einbrin¬ gen der Ausnehmungen zur Einstellung der Eigenfrequenz nicht allein am Schaufelblatt erfolgen muss. Insbesondere kann auch die Maßnahme zur Beeinflussung der Schwingungseigenschaften der Turbinenschaufeln bzw. ihres gegossenen Grundkörpers auch am Schaufelfuß bzw. an der so genannten Plattformunterseite erfolgen. Die Plattformunterseite ist dabei diejenige Seite der Plattform einer Turbinenlaufschaufel bzw. des Grundkörpers, welcher der Heißgasseite der Plattform gegenüberliegt und somit dem Schaufelfuß zugewandt ist. Als Maßnahmen können das Einbringen von Ausnehmungen oder die Verkleinerung eines Abmaßes unter den Sollwert vorgesehen sein. Selbstverständ¬ lich ließen sich auch beide Maßnahmen miteinander kombinieren . Die Vorteile beider Maßnahmen sind, dass sie weder die struk¬ turmechanische Integrität des Schaufelblatts verändern noch deren Aerodynamik verschlechtern. Dies ermöglicht das Erreichen der vorbestimmten Lebendauer und Leistungswerte des Schaufelgrundkörpers bzw. der schlussendlich daraus entste- henden Turbinenlaufschaufel. The invention is based on the realization that the Einbrin ¬ gen of the recesses must be made to adjust the natural frequency, not only on the airfoil. In particular, the measure for influencing the vibration properties of the turbine blades or of their cast base body can also take place on the blade root or on the so-called platform underside. The platform underside is that side of the platform of a turbine blade or the base body, which faces the hot gas side of the platform and thus faces the blade root. As measures, the introduction of recesses or the reduction of a Dimension be provided below the setpoint. Selbstverständ ¬ Lich Also, both measures could be combined with each other. The advantages of both measures is that they do not change the constructive ¬ turmechanische integrity of the blade worsen the aerodynamics. This makes it possible to achieve the predetermined life span and power values of the blade body or the turbine blade ultimately resulting therefrom.
Mithin schlägt die Erfindung vor, dass der Schaufelgrundköper am Schaufelfuß und/oder an der Unterseite der Plattform einen Bereich aufweist, dessen Gestalt und/oder Abmaße so gewählt sind, dass diese keine strukturmechanischen Funktionen aufweisen. Aufgrund dieser Eigenschaft und den ursprünglich bereitgestellten Abmaßen umfasst der Grundkörper zumindest einen Bereich, der als Opferbereich angesehen wird, um durch dortige Massereduzierung die Schwingungseigenschaften des Grundkörpers zu verändern, ohne dass die funktionalen Eigenschaften sich mit ändern. Zur Massereduzierung kann beispielsweise in eine ebenflächige Seite des Schaufelfußes eine Ausnehmung eingebracht werden. Ein weiteres Beispiel ist der Reduzierung der Breite eines Steges, welches an der Platt- formunterseite der Turbinenschaufel vorgesehen ist. Thus, the invention proposes that the blade root on the blade root and / or on the underside of the platform has an area whose shape and / or dimensions are chosen so that they have no structural mechanical functions. Due to this property and the dimensions originally provided, the base body comprises at least one region which is regarded as a sacrificial region in order to modify the vibration properties of the base body by reducing the mass there without the functional properties changing as well. To reduce the mass, for example, a recess can be made in a planar side of the blade root. Another example is the reduction of the width of a web which is provided on the platform underside of the turbine blade.
Vorzugsweise sind die Bereiche dort angesiedelt, bei denen die voran beschriebenen Maßnahmen durchgeführt werden können, ohne dass sich die für die während des Betriebs auftretende relevante mechanische Belastung erforderliche strukturmecha¬ nische Integrität des Grundkörpers signifikant verschlech¬ tert. Mithin werden diejenigen Flächenträgheitsmomente und die diejenige Steifigkeit der Turbinenlaufschaufel verändert, die die Lebensdauer der Turbinenschaufel ohnehin nicht be¬ grenzen. Damit bleibt die vorbestimmte Lebensdauer der Turbi¬ nenlaufschaufel unbeeinflusst . Bevorzugt liegt der betreffende Bereich bzw. liegen die be¬ treffenden Bereiche außerhalb derjenigen Flächen des Grundkörpers, die von einem Heißgas überströmbar sind. Damit lässt sich das Verfahren auch nach dem Beschichten von Turbinen- laufschaufeln mit einer Erosions- und/oder Wärmedämmschicht anwenden . Preferably, the areas are located there, where the measures described above can be carried out without changing the time required for the occurring during the operation of relevant mechanical stress strukturmecha ¬ African integrity of the base body significantly verschlech ¬ tert. Consequently, those moments of inertia and that rigidity of the turbine blade to be changed, which border the life of the turbine blade in any case not be ¬. In order for the predetermined life of Turbi ¬ nenlaufschaufel unaffected. Preferably, the range in question is or are the ¬ be taken of those areas outside surfaces of the body which are überströmbar of a hot gas. Thus, the method can also be applied after the coating of turbine blades with an erosion and / or thermal barrier coating.
Vorzugsweise wird das erfindungsgemäße Verfahren in einer recht späten Phase des Herstellungsprozesses der Turbinen- schaufeln angewendet. Dies bedeutet, dass der üblicherweise im Gießverfahren hergestellte Grundkörper vor dem Erfassen des Werts des eine Schwingungseigenschaft repräsentierenden Parameters bereits auf Sollmaß gebracht worden ist. Damit wird gewährleistet, dass die Schwingungsmessung an der nahezu fertigen Turbinenlaufschaufel erfolgt und somit weitere Fer¬ tigungsschritte, die ebenso die Schwingungseigenschaften des Grundkörpers bzw. der Turbinenlaufschaufel verändern können, zumindest weitgehend vermieden werden. Weiter bevorzugt kann das Verfahren auch vor dem beschichten des Grundkörpers durchgeführt werden, wenn vorausbestimmbar ist, um welchen (mittleren) Wert der erfasste Wert des Para¬ meters aufgrund der dann nachträglich aufgebrachten Beschich- tung sich ändert. Dann sind bereits in einer früheren Phase des Herstellprozesses die vorgenannten Maßnahmen durchführbar, um diejenigen Grundkörper zu selektieren, deren Schwingungseigenschaften und -werte trotz der Durchführung der erfindungsgemäßen Maßnahmen nicht in die zugehörigen Ziel- Intervalle überführt werden konnten. Hiermit können Aufwen- düngen für Ausschuss frühzeitig vermieden werden. Preferably, the method according to the invention is applied in a rather late phase of the manufacturing process of the turbine blades. This means that the base body usually produced in the casting process has already been brought to the specified size before the value of the parameter representing a vibration characteristic is detected. This ensures that the vibration measurement is carried out on the almost finished turbine blade and thus further Fer ¬ tion steps that can change the vibration characteristics of the body or the turbine blade, at least largely avoided. More preferably, the method can also prior to the coat of the base body are performed when ahead determinable by which the (average) value of the detected value of Para ¬ meters due to the then subsequently applied coating changes. Then already at an earlier stage of the manufacturing process, the aforementioned measures can be carried out in order to select those basic body whose vibration characteristics and values could not be transferred into the associated target intervals despite the implementation of the inventive measures. In this way, the expense of waste can be avoided at an early stage.
Zweckmäßiger weise sind nur einige der Turbinenlaufschaufeln eines Schaufelkranzes, oder gar alle gemäß dem vorgenannten Verfahren hergestellt. Conveniently, only some of the turbine blades of a blade ring, or even all made according to the aforementioned method.
In dieser Anmeldung wird begrifflich zwischen einer Turbinenlaufschaufel und einem Grundkörper einer Turbinenlaufschaufel unterschieden. Dabei wird unter einer Turbinenlaufschaufel diejenige verstanden, die fertig hergestellt und dafür vorge¬ sehen ist, dass sie ohne weitere Bearbeitung an einem Rotor einer Turbine befestigt werden kann. Im Unterschied dazu wird unter dem Grundkörper einer Turbinenlaufschaufel ein Turbi¬ nenlaufschaufelrohling verstanden, der sich noch inmitten des Herstellungsprozesses befindet, an dessen Ende die fertige Turbinenlaufschaufel steht. Mithin betrifft die Erfindung nur einige der insgesamt erforderlichen Herstellungsschritte zum Fertigen einer einsatzbereiten Turbinenlaufschaufel, wobei die hier genannten Verfahrensschritte auch die allerletzten Herstellungsschritte zum Herstellen der einsatzbereiten Turbinenschaufel darstellen können. In this application, conceptually becomes between a turbine blade and a main body of a turbine blade distinguished. Is understood to mean a turbine blade one that produced finished and therefor is seen ¬ that it can be attached without further processing to a rotor of a turbine. In contrast, a Turbi ¬ nenlaufschaufelrohling is understood to mean the base of a turbine blade, which is still in the middle of the manufacturing process, at the end of the finished turbine blade is. Thus, the invention relates only to some of the manufacturing steps required overall for manufacturing a ready-to-use turbine blade, wherein the method steps mentioned here can also represent the very last production steps for producing the ready-to-use turbine blade.
Die Erfindung wird anhand einer Zeichnung erläutert, wobei identische Bezugszeichen gleich wirkende Bauteile beschrei¬ ben . The invention will be explained with reference to a drawing, wherein identical reference numerals identically acting components beschrei ¬ ben.
Es zeigen: Show it:
FIG 1 ein Ablaufdiagramm mit den unterschiedlichen Herstellungsschritten eines erfindungsgemäßen Verfahren zum Her- stellen eines Grundkörpers einer Turbinenlaufschaufel, 1 shows a flowchart with the different production steps of a method according to the invention for producing a main body of a turbine blade,
FIG 2 ein Ablaufdiagramm mit weiteren Herstellungsschritten und FIG 3 eine perspektivische Ansicht auf eine Unterseite eines Grundkörpers einer Turbinenlaufschaufel. 2 shows a flowchart with further manufacturing steps, and FIG. 3 shows a perspective view of an underside of a base body of a turbine blade.
Das erfindungsgemäße Verfahren 10 ist in FIG 1 dargestellt. Das Verfahren 10 zum Herstellen eines Grundkörpers 30 (Fig.The method 10 according to the invention is shown in FIG. The method 10 for producing a main body 30 (FIG.
3) einer Turbinenlaufschaufel umfasst in einem ersten Schritt 12 das Bereitstellen des Grundkörpers 30 der Turbinenlauf¬ schaufel. Der Grundkörper 30 umfasst entlang einer virtuellen Längsachse 31 aufeinander folgend einen Schaufelfuß 32, eine Plattform 34 und ein Schaufelblatt 36. 3) of a turbine blade comprises in a first step 12, the provision of the main body 30 of the turbine blade ¬ blade. The main body 30 comprises along a virtual Longitudinal axis 31 successively a blade root 32, a platform 34 and an airfoil 36th
Die Kontur des Schaufelfußes 32 ist bei senkrechter Sicht auf seine ebenflächige Stirnseite 38 tannenbaumförmig und geht über einen so genannten Schaufelhals 40 in eine Unterseite 42 der Plattform 34 über. Der Unterseite 42 gegenüberliegend weist die Plattform eine Heißgasseite 44 auf, an der das Schaufelblatt 36 sich monolithisch anschließt. Dieses ist tropfenförmig ausgebildet und unter Ausbildung einer Druckseite 46 und einer Saugseite 48 aerodynamisch gekrümmt. The contour of the blade root 32 is fir-tree-shaped when viewed perpendicularly on its planar end face 38 and merges via a so-called blade neck 40 into an underside 42 of the platform 34. Opposite the underside 42, the platform has a hot gas side 44, at which the airfoil 36 connects monolithically. This is drop-shaped and aerodynamically curved to form a pressure side 46 and a suction side 48.
Der Schaufelfuß 32 erstreckt sich über eine Länge L zwischen den beiden sich axial einander gegenüberliegenden ebenflächi- gen Stirnseiten 38. The blade root 32 extends over a length L between the two axially opposite planar end faces 38.
In einem zweiten Herstellungsschritt 14 wird eine Größe von mindestens einem Parameter des Grundkörpers 30 erfasst, wobei mindestens einer der Parameter eine Schwingungseigenschaft des Grundkörpers repräsentiert. Üblicherweise werden die Ei¬ genfrequenzen und die Schwingungsmoden mit den üblichen Methoden erfasst. In a second production step 14, a size of at least one parameter of the base body 30 is detected, wherein at least one of the parameters represents a vibration property of the base body. Usually, the egg ¬ gene frequencies and the vibration modes are detected by the usual methods.
In einem dritten Herstellungsschritt 16 wird der erfasste Wert bzw. werden die erfassten Werte mit einem (zugehörigen) Ziel-Intervall verglichen. Liegen die erfassten Werte außerhalb des zugehörigen Ziel-Intervalls, werden erfindungsgemäß am Schaufelfuß 32 und/oder an der Unterseite 42 der Plattform 36 schwingungsverändernde Maßnahmen als vierter Herstellungs- schritt durchgeführt. Diese können das Einbringen von einer oder mehreren Ausnehmungen 50 und/oder das Verkleinern der bisherigen Abmaße wie Länge, Breite oder Höhe bestimmter, dort angeordneter Merkmale sein. Beispielsweise kann die Län¬ ge L des Schaufelfußes 32 um einige hundertstel Millimeter gekürzt werden auf ein Maß, welches unter den ansonsten vorgesehenen Sollwert für die Länge L liegt. Die Reduzierung der Masse des Grundkörpers 30 erfolgt in demjenigen Bereich 49, der insbesondere dafür vorgesehen wurden. Damit ändert sich das Gewicht und ggf. die Anpressfläche der Turbinenlaufschau¬ fel unter Fliehkraft, was auf die Schwingungseigenschaft der Turbinenlaufschaufel günstig auswirkt. Im Zweifelsfall werden die zweiten, dritten und vierten In a third production step 16, the detected value (s) is compared with an (associated) target interval. If the detected values lie outside the associated target interval, according to the invention vibration-altering measures are carried out on the blade root 32 and / or on the underside 42 of the platform as the fourth production step. These can be the introduction of one or more recesses 50 and / or the reduction of the previous dimensions such as length, width or height of certain features arranged there. For example, the County ¬ ge L of the blade root can be shortened by a few hundredths of a millimeter to a level 32 which is below the otherwise provided target value for the length L. The reduction of the mass of the main body 30 takes place in the region 49, which were provided in particular for it. This changes the weight and possibly the contact surface of the turbine run ¬ fel under centrifugal force, which has a favorable effect on the vibration property of the turbine blade. If in doubt, the second, third and fourth
Schritte 14, 16 ,18 als Serie wiederholt ausgeführt, um die Eignung des Grundkörpers 30 zu überprüfen. Erst wenn die un¬ tersuchte Turbinenlaufschaufeln den Anforderungen hinsichtlich der Schwingungseigenschaft genügt, wird diese dem weite- ren Herstellungsprozess übergeben. Steps 14, 16, 18 repeatedly executed as a series to check the suitability of the base body 30. Only when the un ¬ ters visited turbine blades meets the requirements in terms of vibration property, this weite- the reindeer manufacturing process is passed.
Bei dem Grundkörper 30 bzw. bei der Turbinenlaufschaufel kann es sich auch um eine handeln, die mit einer Schutzschicht versehen ist bzw. versehen werden soll. Die Schutzschicht ist dabei vorzugsweise eine Korrosionsschutzschicht vom Typ The base body 30 or the turbine blade may also be one which is or should be provided with a protective layer. The protective layer is preferably a corrosion protection layer of the type
MCrAlY. Alternativ kann auch eine zwei- oder mehrlagige MCrAlY. Alternatively, a two- or multi-layered
Schutzschicht vorgesehen sein, die als Bondcoat eine Schicht vom Typ MCrAlY umfasst, auf der weiter außen eine keramische Wärmedämmschicht (thermal barrier coat-TBC) aufgebracht wor- den ist. Durch das Aufbringen der Schutzschicht, insbesondere eine Korrosionsschutzschicht, wird die Masse des Grundkörpers weiter erhöht. Die mit der Massenerhöhung einhergehende Veränderung der Eigenfrequenz kann durch das Einbringen von Ausnehmungen 50 am Schaufelfuß 32 bzw. der Unterseite der Platt- form 34 kompensiert werden. Es ist dabei vorgesehen, dass derartig viele und derartig tiefe Ausnehmungen 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 An¬ forderungen genügt. In diesem Falle ist der Grundkörper für eine kommerzielle Nutzung nicht geeignet. Protective layer may be provided, which comprises as a bondcoat a layer of the type MCrAlY on which a ceramic thermal barrier coating (TBC) has been applied further out. By applying the protective layer, in particular a corrosion protection layer, the mass of the base body is further increased. The change in the natural frequency associated with the increase in mass can be compensated for by inserting recesses 50 on the blade root 32 or the underside of the platform 34. It is provided that so many and such deep recesses are introduced until the turbine blade meets the requirements of the natural frequency. It may be this is that despite the application of the method according to the invention, the natural frequency can not be influenced strongly enough that this satisfies the requirements to ¬. In this case, the body is not suitable for commercial use.
Die Beschichtung des Grundkörpers 30 kann vor dem erstmaligen Durchführen des zweiten Herstellungsschritts 14 oder nach dem letztmaligen Durchführen des vierten Herstellungsschrittes 18 erfolgen . Mittels der stirnseitig in den Schaufelfuß 32 angeordneten Ausnehmung 50 erfolgt eine Frequenzverschiebung der Eigenfrequenz. Die Gestalt der Ausnehmungen 50 ist beliebig. The coating of the main body 30 can be carried out before the first execution of the second production step 14 or after the last time the fourth production step 18 is carried out. By means of the end face arranged in the blade root 32 recess 50 is a frequency shift of the natural frequency. The shape of the recesses 50 is arbitrary.
Fig. 2 zeigt ein zweites Ablaufdiagramm für ein weiteres Ausführungsbeispiel eines Herstellverfahrens. Gemäß dem weiteren Ausführungsbeispiel umfasst das Herstellverfahren die bisher erwähnten Schritte 12, 14, 16, 18, ergänzt um teilweise da- zwischen durchzuführende Herstellungsschritte 13 und 19. Er¬ gänzt wurde einerseits der Herstellungsschritt 13, in welchem der Grundkörper 30 zumindest weitestgehend auf Maß gefertigt wird. Mit anderen Worten: in diesem Herstellungsschritt wer¬ den die gußtoleranzbehafteten Maße des Grundkörpers 30 auf die planmäßigen Sollwerte, die ihrerseits ebenso toleranzbe¬ haftet sein können, gebracht. FIG. 2 shows a second flowchart for a further embodiment of a manufacturing method. According to another embodiment of the manufacturing method includes the previously mentioned steps 12, 14, 16, 18, supplemented by partial DA between intended preparation steps 13 and 19, the preparation step 13 in which the base body 30 was He ¬ supplemented on the one hand made at least largely to size becomes. In other words, in this manufacturing step ¬ to the gußtoleranzbehafteten extent of the base body 30 to the scheduled setpoints that can be liable for its part also toleranzbe ¬ brought.
Im Herstellungsschritt 19 kann ein bis dahin unbeschichteter Grundkörper 30 mit einer Erosions- und/oder Wärmedämmschicht versehen werden. In the manufacturing step 19, a hitherto uncoated base body 30 can be provided with an erosion and / or thermal barrier coating.
Insgesamt schlägt somit die Erfindung ein Verfahren zum Herstellen von Turbinenlaufschaufeln bzw. von deren Grundkörpern 30 vor, deren Frequenzeigenschaft besonders einfach an die erforderlichen Randbedingungen angepasst werden kann. Hierzu ist vorgesehen, dass das Einbringen von Ausnehmungen 50 in den Schaufelfuß 32 und/oder durch verkleinern eines Abmaßes unter den entsprechenden Sollwert erfolgt, sofern der Grund- köper 30 unzureichende Schwingungseigenschaften aufweist. Hierdurch ist eine Methode angegeben, mit der die Schwingungseigenschaft der Turbinenlaufschaufel besonders einfach und variabel eingestellt werden kann. Damit kann die Aus¬ schussquote bei der Herstellung von Turbinenlaufschaufeln re- duziert werden. Overall, the invention thus proposes a method for producing turbine blades or their basic bodies 30, whose frequency characteristic can be adapted particularly easily to the required boundary conditions. For this purpose, it is provided that the introduction of recesses 50 into the blade root 32 and / or by reducing a dimension below the corresponding desired value, if the base body 30 has insufficient vibration properties. As a result, a method is specified with which the vibration characteristic of the turbine blade can be set particularly easily and variably. This allows the off ¬ scrap rates in the production of turbine blades re- duced be.

Claims

Patentansprüche claims
Verfahren (10, 20) zum Herstellen eines Grundkörpers (30) bzw. einer Turbinenlaufschaufel (40) umfassend zumindest die aufeinander folgenden Schritte, Method (10, 20) for producing a main body (30) or a turbine blade (40) comprising at least the successive steps,
a) Bereitstellen des Grundkörpers (30), welcher entlang einer Längsachse (31) aufeinander folgend einen Schaufel¬ fuß (32), eine Schaufelplattform (34) und ein Schaufelblatt (36) umfasst, comprising a) providing the basic body (30), which along a longitudinal axis (31) successively one blade ¬ foot (32), a blade platform (34) and an airfoil (36),
b) Erfassen einer Werts von mindestens einem Parameter des Grundkörpers (30), wobei mindestens einer der Parame¬ ter eine Schwingungseigenschaft des Grundkörpers (30) re¬ präsentiert, b) detecting a value of at least one parameter of the basic body (30), wherein at least one of the parame ter ¬ a vibration characteristic of the base body (30) re ¬ presented,
c) Vergleichen des erfassten Werts mit einem vorgegeben Ziel-Intervall,  c) comparing the detected value with a predetermined target interval,
d) sofern der erfasste Wert außerhalb des Ziel-Intervalls liegt, Reduzieren der Masse der Grundkörpers (30), dadurch gekennzeichnet,  d) if the detected value is outside the target interval, reducing the mass of the main body (30), characterized
dass die Reduzierung der Masse am Schaufelfuß (32) und/oder am Schaufelplattform (34) durch Einbringen mindestens einer Ausnehmung (50) und/oder durch Verkleinerung eines Abmaßes unter den entsprechenden Sollwert erfolgt .  that the reduction of the mass on the blade root (32) and / or on the blade platform (34) by introducing at least one recess (50) and / or by reducing a dimension below the corresponding target value.
Verfahren (10, 20) nach Anspruch 1, Method (10, 20) according to claim 1,
bei dem der Schaufelfuß (32) und/oder die Schaufelplatt¬ form (34) einen Bereich (49) umfassen, in dem die Ausnehmungen (50) einbringbar bzw. das Abmaß verringerbar sind, wodurch sich das Flächenträgheitsmoment und damit die Steifigkeit der Turbinenlaufschaufel verändert. wherein the blade root (32) and / or the Schaufelplatt ¬ form (34) comprise a region (49) in which the recesses (50) can be introduced or the dimension can be reduced, thereby changing the area moment of inertia and thus the rigidity of the turbine blade ,
Verfahren (10, 20) nach Anspruch 1 oder 2, Method (10, 20) according to claim 1 or 2,
bei dem der betreffende Bereich (49) bzw. die betreffenden Bereiche (49) außerhalb derjenigen Flächen des Grund¬ körpers (30) liegt bzw. liegen, die von einem Heißgas überströmbar sind. Verfahren (10, 20) nach Anspruch 1, 2 oder 3, wherein the area of interest (49) or the relevant areas (49) outside of those surfaces of the base ¬ body (30) is or are that are überströmbar of a hot gas. Method (10, 20) according to claim 1, 2 or 3,
bei dem vor der Durchführung des Schritts b) zumindest die meisten Abmaße des Grundkörpers (30) auf ihr Sollmaß gebracht werden. in which, prior to the implementation of step b), at least most of the dimensions of the basic body (30) are brought to their nominal dimensions.
Verfahren (10, 20) nach einem der vorangehenden Ansprüche, Method (10, 20) according to one of the preceding claims,
bei dem vor dem Schritt b) oder nach dem Schritt d) als Schutzschicht eine Korrosionsschutzschicht und/oder Wär¬ medämmschicht auf den Grundkörper (30) aufgebracht wird. in which before the step b) or after the step d) as a protective layer, a corrosion protection layer and / or Wär ¬ medämmschicht is applied to the base body (30).
Laufschaufelring für einen Rotor einer axial durchströmten Turbine, Blade ring for a rotor of an axial flow turbine,
mit einer Anzahl von Turbinenlaufschaufeln, deren Grundkörper (30) nach einem Verfahren nach einem der Ansprüche 1 bis 5 hergestellt sind. with a number of turbine blades, whose base bodies (30) are produced by a method according to one of claims 1 to 5.
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EP2762678A1 (en) * 2013-02-05 2014-08-06 Siemens Aktiengesellschaft Method for misaligning a rotor blade grid
US20170028703A1 (en) * 2014-04-10 2017-02-02 United Technologies Corporation Real-time resonant inspection for additive manufacturing
EP2957792B1 (en) * 2014-06-20 2020-07-29 United Technologies Corporation Reduced vibratory response rotor for a gas powered turbine

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WO2017114644A1 (en) 2017-07-06
US20190338645A1 (en) 2019-11-07
JP2019500545A (en) 2019-01-10
CN108474254B (en) 2020-04-24
EP3362648B1 (en) 2019-10-23
US10669857B2 (en) 2020-06-02
EP3187685A1 (en) 2017-07-05
JP6586242B2 (en) 2019-10-02
CN108474254A (en) 2018-08-31

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