EP3362648B1 - Method for producing a base part of a turbine blade - Google Patents

Method for producing a base part of a turbine blade Download PDF

Info

Publication number
EP3362648B1
EP3362648B1 EP16812708.2A EP16812708A EP3362648B1 EP 3362648 B1 EP3362648 B1 EP 3362648B1 EP 16812708 A EP16812708 A EP 16812708A EP 3362648 B1 EP3362648 B1 EP 3362648B1
Authority
EP
European Patent Office
Prior art keywords
base body
blade
turbine
turbine blade
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.)
Active
Application number
EP16812708.2A
Other languages
German (de)
French (fr)
Other versions
EP3362648A1 (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

Images

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 base body, which successively comprises a blade root, a blade platform and an airfoil along a virtual longitudinal axis, detecting a value of a parameter of the base body representing a vibration characteristic Comparing the detected value with a predetermined target interval and if the detected value is outside the target interval, reducing the mass of the main body. Furthermore, the invention relates to a blade ring for a rotor of an axial flow turbine.
  • a protective layer As a protective layer, a MCrAlY type anticorrosion layer is often applied to the turbine blade produced by a casting process. The application of the protective layer takes place in the region of that surface which is exposed during operation to the hot gas of the gas turbine. This area includes both the airfoil and the platform of the turbine blade on which the airfoil forms.
  • a heat-insulating layer can also be applied in the abovementioned area in order to minimize the heat input from the hot gas into the base material of the turbine blade. The application of the layers thereby alters the vibration behavior of the turbine blade.
  • the turbine blades are designed such that their natural frequency deviates from the excitation frequencies of the stationary gas turbine.
  • care is also taken to ensure that the finished turbine blade as a whole satisfies the requirements for natural resonance, also with regard to the expected rotor speeds.
  • the turbine blade In the manufacturing process of the turbine blade is therefore intended to check each turbine blade on their vibration characteristics.
  • the turbine blade In this test, the turbine blade is clamped at the foot and excited by mechanical impulse to vibrate. Then the vibration response of the turbine blade and in particular its blade is detected. If the vibration response of the turbine blade does not meet the predetermined frequency values at natural frequency, this is to be rejected or manipulated by suitable measures such that it meets the requirements of the natural frequency and thus is suitable for operation.
  • the supply still supply is for example from the EP 1 985 803 A1 known to introduce a recess in the tip of the airfoil, whereby the mass of the turbine blade at her free, swingable end can be reduced. By reducing the mass of the turbine blade, the vibration characteristic is positively influenced. Its natural frequency can be shifted to higher values by removing the mass.
  • 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 to provide a blade ring, the blades are particularly robust against induced by the hot gas vibrational excitation.
  • the invention is based on the recognition that the introduction of the recesses for setting the natural frequency need not be made solely on the blade.
  • 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. Of course, both measures could be combined.
  • the invention proposes that the blade root body on the blade root and / or on the underside of the platform has a region whose shape and / or dimensions are selected 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.
  • a recess can be made in a planar side of the blade root. Another example is the reduction in the width of a ridge provided on the platform underside of the turbine bucket.
  • the areas are located where the measures described above can be carried out without significantly deteriorating the structural mechanical integrity of the base body required for the relevant mechanical load occurring during operation.
  • those moments of inertia and that rigidity of the turbine blade are changed, which in any case does not limit the life of the turbine blade. This leaves the predetermined service life of the turbine blade unaffected.
  • 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.
  • the method can also be carried out before coating the base body, if it can be predicted by what (average) value the detected value of the parameter changes due to the then subsequently applied coating. Then already in an earlier stage of the manufacturing process, the aforementioned measures can be carried out 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. Hereby expenses for waste can be avoided at an early stage.
  • a turbine blade is understood to mean that which is finished and provided for being able to be attached to a rotor of a turbine without further processing.
  • the basic body of a turbine blade is understood to mean a turbine blade blank which is still in the middle of the manufacturing process, at the end of which the finished turbine blade is located.
  • 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.
  • the inventive method 10 is in FIG. 1 shown.
  • the method 10 for producing a basic body 30 (FIG. Fig. 3 ) of a turbine blade comprises in a first step 12 the provision of the main body 30 of the turbine 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 natural 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, vibration-changing measures are carried out according to the invention 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 length L of the blade root 32 can be shortened by a few hundredths of a millimeter to a level which is below the otherwise prescribed setpoint 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 blade under centrifugal force, which has a favorable effect on the vibration property of the turbine blade.
  • the second, third and fourth steps 14, 16, 18 are repeatedly executed as a series in order to check the suitability of the main body 30. Only when the investigated turbine blades meet the requirements with regard to the vibration characteristic is it passed on to the further production process.
  • 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 MCrAlY type.
  • a two-layer or multi-layer protective layer comprising, as a bondcoat, a layer of the MCrAlY type on which a ceramic thermal barrier coating (TBC) has been applied further out.
  • TBC ceramic thermal barrier coating
  • the natural frequency can not be strongly influenced enough that it meets the requirements. In this case, the body is not suitable for commercial use.
  • 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 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 shows a second flowchart for another embodiment of a manufacturing process.
  • the manufacturing method comprises the previously mentioned steps 12, 14, 16, 18, supplemented by production steps 13 and 19 to be carried out partially therebetween.
  • the production step 13 in which the main body 30 is made to size as far as possible was supplemented.
  • the dimensions of the main body 30 that are subject to the greasing tolerances are brought to the planned nominal values, which in turn can also be subject to tolerances.
  • 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 can reduce the reject rate in the manufacture of turbine blades.

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)

Description

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 aufeinander folgend einen Schaufelfuß, eine Schaufelplattform und ein Schaufelblatt umfasst, Erfassen eines Werts eines eine Schwingungseigenschaft repräsentierenden Parameters des Grundkörpers, Vergleichen des erfassten Werts mit einem vorgegeben Ziel-Intervall und sofern der erfasste Wert außerhalb des Ziel-Intervalls liegt, Reduzieren der Masse der Grundkörpers. Ferner betrifft die Erfindung einen Laufschaufelring für einen Rotor einer axial durchströmten Turbine.The invention relates to a method for producing a base body of a turbine blade, comprising at least the successive steps, providing the base body, which successively comprises a blade root, a blade platform and an airfoil along a virtual longitudinal axis, detecting a value of a parameter of the base body representing a vibration characteristic Comparing the detected value with a predetermined target interval and if the detected value is outside the target interval, reducing the mass of the main body. 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 häufig eine Korrosionsschutzschicht des Typs MCrAlY auf die in einem Gießverfahren hergestellte Turbinenlaufschaufel aufgebracht. Die Aufbringung der Schutzschicht erfolgt in dem Bereich derjenigen Oberfläche, welcher im Betrieb dem Heißgas der Gasturbine ausgesetzt ist. Dieser Bereich umfasst sowohl das Schaufelblatt als auch 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 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 an increased lifetime when operating in a gas turbine. As a protective layer, a MCrAlY type anticorrosion layer is often applied to the turbine blade produced by a casting process. The application of the protective layer takes place in the region of that surface which is exposed during operation to the hot gas of the gas turbine. This area includes both the airfoil and the platform of the turbine blade on which the airfoil forms. In addition to the anticorrosion layer, a heat-insulating layer can also be applied in the abovementioned area in order to minimize the heat input from the hot gas into the base material of the turbine blade. 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 Turbinenlaufschaufeln - in Strömungsrichtung des Heißgases gesehen - hinter einem Kranz von Turbinenleitschaufeln umlaufen, werden diese durch zyklisch auftreffendes Heißgas zum Schwingen angeregt. Daher ist es erforderlich, dass jede Turbinenlaufschaufel eine ausreichend hohe Eigenfrequenz aufweist, so 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. Bei der Entwicklung der Turbinenlaufschaufel wird zudem darauf geachtet, dass die fertige Turbinenlaufschaufel insgesamt den Anforderungen bezüglich der Eigenresonanz, auch im Hinblick auf die zu erwartenden Rotordrehzahlen 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 blades - seen in the flow direction of the hot gas - rotate behind a ring of turbine vanes, they are excited by cyclically impinging hot gas to vibrate. Therefore, it is necessary that each turbine blade has a sufficiently high natural frequency, so that both the rotor speed and the hot gas originating vibration excitation with 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. During the development of the turbine blade, care is also taken to ensure that the finished turbine blade as a whole satisfies the requirements for natural resonance, also with regard to the expected rotor speeds.

Im Fertigungsprozess der Turbinenlaufschaufel ist daher vorgesehen, jede einzelne Turbinenlaufschaufel auf ihre Schwingungseigenschaften zu überprüfen. Bei dieser Überprüfung wird die Turbinenschaufel fußseitig eingespannt und per mechanischem Impuls zum Schwingen angeregt. Daraufhin wird die Schwingungsantwort der Turbinenschaufel und insbesondere ihres Schaufelblattes erfasst. Sofern die Schwingungsantwort der Turbinenlaufschaufel den vorgegebenen Frequenzwerten an Eigenfrequenz nicht erfüllt, ist diese zu verwerfen oder mittels 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 Einsatz in der Gasturbine vorgesehen sind, der Benutzung doch zuzuführen, ist beispielsweise aus der EP 1 985 803 A1 bekannt, in der Spitze des Schaufelblatts eine Ausnehmung einzubringen, wodurch die Masse der Turbinenlaufschaufel an ihrem freien, schwingfähigen Ende reduziert werden kann. Durch die Reduzierung der Masse der Turbinenlaufschaufel wird die Schwingungseigenschaft positiv beeinflusst. Ihre Eigenfrequenz kann durch das Entfernen der Masse zu höheren Werten verschoben werden.In the manufacturing process of the turbine blade is therefore intended to check each turbine blade on their vibration characteristics. In this test, the turbine blade is clamped at the foot and excited by mechanical impulse to vibrate. Then the vibration response of the turbine blade and in particular its blade is detected. If the vibration response of the turbine blade does not meet the predetermined frequency values at natural frequency, this is to be rejected or manipulated by suitable measures such that it meets the requirements of the natural frequency and thus is suitable for operation. To turbine blades, which are not provided solely for use in the gas turbine due to their vibration property, the supply still supply, is for example from the EP 1 985 803 A1 known to introduce a recess in the tip of the airfoil, whereby the mass of the turbine blade at her free, swingable end can be reduced. By reducing the mass of the turbine blade, the vibration characteristic is positively influenced. Its natural frequency can be shifted to higher values by removing the mass.

Daneben ist aus der EP 0 537 922 A1 bekannt, in die Schaufelplattform einer Turbinenlaufschaufel ein rohrförmigen Dämpfer einzusetzen. Dieser kann unter Fliehkraft sich geringfügig herausschieben und so zur Anlage an einer Plattform einer Nachbarschaufel gelangen, um während des Betriebs Schaufelzu-Schaufel-Schwingungen zu dämpfen.Besides that is from the EP 0 537 922 A1 known to insert a tubular damper in the blade platform of a turbine blade. This can slightly push out under centrifugal force and thus come to rest on a platform of a neighboring bucket to dampen blade-to-bucket 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, dessen Laufschaufelblätter besonders robust gegen eine vom Heißgas herbeigeführte Schwingungsanregung sind.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 to provide a blade ring, the blades are particularly robust against 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 6 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 6.

Die Erfindung geht von der Erkenntnis aus, dass das Einbringen 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. Selbstverständlich ließen sich auch beide Maßnahmen miteinander kombinieren.The invention is based on the recognition that the introduction of the recesses for setting the natural frequency need not be made solely on the blade. 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. Of course, both measures could be combined.

Die Vorteile beider Maßnahmen sind, dass sie weder die strukturmechanische Integrität des Schaufelblatts verändern noch deren Aerodynamik verschlechtern. Dies ermöglicht das Erreichen der vorbestimmten Lebendauer und Leistungswerte des Schaufelgrundkörpers bzw. der schlussendlich daraus entstehenden Turbinenlaufschaufel.The advantages of both measures are that they neither change the structure-mechanical integrity of the airfoil nor worsen their aerodynamics. This makes it possible to achieve the predetermined life and performance 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 Plattformunterseite der Turbinenschaufel vorgesehen ist.Thus, the invention proposes that the blade root body on the blade root and / or on the underside of the platform has a region whose shape and / or dimensions are selected 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 in the width of a ridge provided on the platform underside of the turbine bucket.

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 strukturmechanische Integrität des Grundkörpers signifikant verschlechtert. Mithin werden diejenigen Flächenträgheitsmomente und die diejenige Steifigkeit der Turbinenlaufschaufel verändert, die die Lebensdauer der Turbinenschaufel ohnehin nicht begrenzen. Damit bleibt die vorbestimmte Lebensdauer der Turbinenlaufschaufel unbeeinflusst.Preferably, the areas are located where the measures described above can be carried out without significantly deteriorating the structural mechanical integrity of the base body required for the relevant mechanical load occurring during operation. Thus, those moments of inertia and that rigidity of the turbine blade are changed, which in any case does not limit the life of the turbine blade. This leaves the predetermined service life of the turbine blade unaffected.

Bevorzugt liegt der betreffende Bereich bzw. liegen die betreffenden Bereiche außerhalb derjenigen Flächen des Grundkörpers, die von einem Heißgas überströmbar sind. Damit lässt sich das Verfahren auch nach dem Beschichten von Turbinenlaufschaufeln mit einer Erosions- und/oder Wärmedämmschicht anwenden.Preferably, the area in question or lie the respective areas outside of those areas of the body, which are overflowed by 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 Turbinenschaufeln 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 Fertigungsschritte, die ebenso die Schwingungseigenschaften des Grundkörpers bzw. der Turbinenlaufschaufel verändern können, zumindest weitgehend 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 manufacturing steps, which can also change the vibration characteristics of the main body or the turbine blade, are at least largely avoided.

Weiter bevorzugt kann das Verfahren auch vor dem beschichten des Grundkörpers durchgeführt werden, wenn vorausbestimmbar ist, um welchen (mittleren) Wert der erfasste Wert des Parameters aufgrund der dann nachträglich aufgebrachten Beschichtung 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 Aufwendungen für Ausschuss frühzeitig vermieden werden.More preferably, the method can also be carried out before coating the base body, if it can be predicted by what (average) value the detected value of the parameter changes due to the then subsequently applied coating. Then already in an earlier stage of the manufacturing process, the aforementioned measures can be carried out 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. Hereby expenses for 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 vorgesehen ist, dass sie ohne weitere Bearbeitung an einem Rotor einer Turbine befestigt werden kann. Im Unterschied dazu wird unter dem Grundkörper einer Turbinenlaufschaufel ein Turbinenlaufschaufelrohling 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. In this case, a turbine blade is understood to mean that which is finished and provided for being able to be attached to a rotor of a turbine without further processing. In contrast, the basic body of a turbine blade is understood to mean a turbine blade blank which is still in the middle of the manufacturing process, at the end of which the finished turbine blade is located. 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 beschreiben.The invention will be explained with reference to a drawing, wherein identical reference numerals describe the same acting components.

Es zeigen:

  • FIG 1 ein Ablaufdiagramm mit den unterschiedlichen Herstellungsschritten eines erfindungsgemäßen Verfahren zum Herstellen eines Grundkörpers einer Turbinenlaufschaufel,
  • FIG 2 ein Ablaufdiagramm mit weiteren Herstellungsschritten und
  • FIG 3 eine perspektivische Ansicht auf eine Unterseite eines Grundkörpers einer Turbinenlaufschaufel.
Show it:
  • FIG. 1 1 is a flowchart with the different production steps of a method according to the invention for producing a base body of a turbine blade,
  • FIG. 2 a flowchart with further manufacturing steps and
  • FIG. 3 a perspective view of an underside of a main body of a turbine blade.

Das erfindungsgemäße Verfahren 10 ist in FIG 1 dargestellt. Das Verfahren 10 zum Herstellen eines Grundkörpers 30 (Fig. 3) einer Turbinenlaufschaufel umfasst in einem ersten Schritt 12 das Bereitstellen des Grundkörpers 30 der Turbinenlaufschaufel. Der Grundkörper 30 umfasst entlang einer virtuellen Längsachse 31 aufeinander folgend einen Schaufelfuß 32, eine Plattform 34 und ein Schaufelblatt 36.The inventive method 10 is in FIG. 1 shown. The method 10 for producing a basic body 30 (FIG. Fig. 3 ) of a turbine blade comprises in a first step 12 the provision of the main body 30 of the turbine 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 ebenflächigen 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 Eigenfrequenzen 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 natural 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 Herstellungsschritt 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 Länge 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 Turbinenlaufschaufel unter Fliehkraft, was auf die Schwingungseigenschaft der Turbinenlaufschaufel günstig auswirkt.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, vibration-changing measures are carried out according to the invention 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 length L of the blade root 32 can be shortened by a few hundredths of a millimeter to a level which is below the otherwise prescribed setpoint 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 blade under centrifugal force, which has a favorable effect on the vibration property of the turbine blade.

Im Zweifelsfall werden die zweiten, dritten und vierten Schritte 14, 16 ,18 als Serie wiederholt ausgeführt, um die Eignung des Grundkörpers 30 zu überprüfen. Erst wenn die untersuchte Turbinenlaufschaufeln den Anforderungen hinsichtlich der Schwingungseigenschaft genügt, wird diese dem weiteren Herstellungsprozess übergeben.If in doubt, the second, third and fourth steps 14, 16, 18 are repeatedly executed as a series in order to check the suitability of the main body 30. Only when the investigated turbine blades meet the requirements with regard to the vibration characteristic is it passed on to the further production process.

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 MCrAlY. Alternativ kann auch eine zwei- oder mehrlagige 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. 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 Plattform 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 Anforderungen genügt. In diesem Falle ist der Grundkörper für eine kommerzielle Nutzung nicht geeignet.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 MCrAlY type. Alternatively, it is also possible to provide a two-layer or multi-layer protective layer comprising, as a bondcoat, a layer of the MCrAlY type 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 on 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 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 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.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.

Mittels der stirnseitig in den Schaufelfuß 32 angeordneten Ausnehmung 50 erfolgt eine Frequenzverschiebung der Eigenfrequenz. Die Gestalt der Ausnehmungen 50 ist beliebig.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 dazwischen durchzuführende Herstellungsschritte 13 und 19. Ergänzt wurde einerseits der Herstellungsschritt 13, in welchem der Grundkörper 30 zumindest weitestgehend auf Maß gefertigt wird. Mit anderen Worten: in diesem Herstellungsschritt werden die gußtoleranzbehafteten Maße des Grundkörpers 30 auf die planmäßigen Sollwerte, die ihrerseits ebenso toleranzbehaftet sein können, gebracht. Fig. 2 shows a second flowchart for another embodiment of a manufacturing process. According to the further exemplary embodiment, the manufacturing method comprises the previously mentioned steps 12, 14, 16, 18, supplemented by production steps 13 and 19 to be carried out partially therebetween. On the one hand, the production step 13 in which the main body 30 is made to size as far as possible was supplemented. In other words: in this production step, the dimensions of the main body 30 that are subject to the greasing tolerances are brought to the planned nominal values, which in turn can also be subject to tolerances.

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 Grundköper 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 Ausschussquote bei der Herstellung von Turbinenlaufschaufeln reduziert 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 can reduce the reject rate in the manufacture of turbine blades.

Claims (4)

  1. Method (10, 20) for producing a base body (30) or a turbine rotor blade (40), comprising at least the successive steps of
    a) providing the base body (30), which comprises, following one another along a longitudinal axis (31), a blade root (32), a blade platform (34) and a blade airfoil (36),
    b) sensing a value of at least one parameter of the base body (30), at least one of the parameters representing a vibrational property of the base body (30),
    c) comparing the sensed value with a predetermined target interval,
    d) if the sensed value lies outside the target interval, reducing the mass of the base body (30),
    characterized
    in that the reduction of the mass takes place at 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.
  2. Method (10, 20) according to Claim 1,
    in which the region (49) concerned or the regions (49) concerned lies or lie outside those regions of the base body (30) that can be flowed over by a hot gas.
  3. Method (10, 20) according to Claim 1 or 2,
    in which, before carrying out step b), at least most of the dimensions of the base body (30) are brought to their target size.
  4. Rotor turbine ring for a rotor of an axially flowed-through turbine,
    with a number of turbine rotor blades, the base bodies (30) of which are produced by a method according to one of Claims 1 to 3.
EP16812708.2A 2015-12-28 2016-12-08 Method for producing a base part of a turbine blade Active EP3362648B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP15202827.0A EP3187685A1 (en) 2015-12-28 2015-12-28 Method for producing a base part of a turbine blade
PCT/EP2016/080179 WO2017114644A1 (en) 2015-12-28 2016-12-08 Method for producing a base body of a turbine blade

Publications (2)

Publication Number Publication Date
EP3362648A1 EP3362648A1 (en) 2018-08-22
EP3362648B1 true EP3362648B1 (en) 2019-10-23

Family

ID=55027506

Family Applications (2)

Application Number Title Priority Date Filing Date
EP15202827.0A Withdrawn EP3187685A1 (en) 2015-12-28 2015-12-28 Method for producing a base part of a turbine blade
EP16812708.2A Active EP3362648B1 (en) 2015-12-28 2016-12-08 Method for producing a base part of a turbine blade

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP15202827.0A Withdrawn EP3187685A1 (en) 2015-12-28 2015-12-28 Method for producing a base part of a turbine blade

Country Status (5)

Country Link
US (1) US10669857B2 (en)
EP (2) EP3187685A1 (en)
JP (1) JP6586242B2 (en)
CN (1) CN108474254B (en)
WO (1) WO2017114644A1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20240271537A1 (en) * 2023-02-14 2024-08-15 Raytheon Technologies Corporation Machinable coating for damping

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5215442A (en) * 1991-10-04 1993-06-01 General Electric Company Turbine blade platform damper
US6390775B1 (en) 2000-12-27 2002-05-21 General Electric Company Gas turbine blade with platform undercut
US6786696B2 (en) 2002-05-06 2004-09-07 General Electric Company Root notched turbine blade
US6814543B2 (en) * 2002-12-30 2004-11-09 General Electric Company Method and apparatus for bucket natural frequency tuning
FR2851285B1 (en) 2003-02-13 2007-03-16 Snecma Moteurs REALIZATION OF TURBINES FOR TURBOMACHINES HAVING DIFFERENT ADJUSTED RESONANCE FREQUENCIES AND METHOD FOR ADJUSTING THE RESONANCE FREQUENCY OF A TURBINE BLADE
DE102005006414A1 (en) * 2005-02-12 2006-08-24 Mtu Aero Engines Gmbh A method of machining an integrally bladed rotor
EP1905950A1 (en) * 2006-09-21 2008-04-02 Siemens Aktiengesellschaft Turbine blade
EP1985803A1 (en) * 2007-04-23 2008-10-29 Siemens Aktiengesellschaft Process for manufacturing coated turbine blades
CA2761208C (en) * 2010-12-08 2019-03-05 Pratt & Whitney Canada Corp. Blade disk arrangement for blade frequency tuning
EP2762678A1 (en) * 2013-02-05 2014-08-06 Siemens Aktiengesellschaft Method for misaligning a rotor blade grid
WO2015157381A1 (en) * 2014-04-10 2015-10-15 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

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
CN108474254B (en) 2020-04-24
JP2019500545A (en) 2019-01-10
US20190338645A1 (en) 2019-11-07
EP3362648A1 (en) 2018-08-22
WO2017114644A1 (en) 2017-07-06
EP3187685A1 (en) 2017-07-05
CN108474254A (en) 2018-08-31
US10669857B2 (en) 2020-06-02
JP6586242B2 (en) 2019-10-02

Similar Documents

Publication Publication Date Title
DE102015219530A1 (en) Blade for a turbomachine, turbofan engine and a method for producing a blade
EP2137381B1 (en) Method for producing coated turbine blades
EP3274558B1 (en) Method for profiling a turbine blade and corresponding blade
EP2725193B1 (en) Method for detuning the blades in a gas turbine engine and corresponding gas turbine engine.
EP2067567B1 (en) Method for manufacturing of integrally bladed rotors for compressors and turbines
EP1245785B1 (en) Turbine airfoil manufacturing method
EP3473431A1 (en) Turbomachine and blade and rotor for a turbomachine
WO2005080754A2 (en) Method for producing adapted flow surfaces
EP2787182A1 (en) Guide blade for a fluid flow engine, guide blade grid and method for the production of a guide blade or a guide blade grid
DE102009033618A1 (en) Method for frequency detuning of rotor body of rotor of gas turbine, involves providing rotor raw body that is made of base material
DE102016217093A1 (en) Coupling pin and turbine with coupling pin
EP2805017B1 (en) Guide blade assembly for an axial flow machine and method for laying the guide blade assembly
EP3362648B1 (en) Method for producing a base part of a turbine blade
WO2005008032A1 (en) Lightweight blade for gas turbine and method for making same
WO2010026005A1 (en) Turbine rotor blade having an adapted natural frequency by means of an insert
DE69205119T2 (en) Process for improving the resilience of a rotating body.
EP2912272B1 (en) Method for misaligning a rotor blade grid
EP3460187A1 (en) Blade for a turbomachine
EP3445947A1 (en) Method for optimizing a natural frequency of a rotor blade, and rotor blade
DE102009053247A1 (en) Method for changing natural frequency of blade for flow machine, particularly for thermal gas turbine, involves applying material on upper surface area of blade by additive manufacturing process
WO2008055471A2 (en) Vane for a compressor or a turbine of an aircraft engine, aircraft engine comprising such a vane, and method for coating a vane of an aircraft engine
DE102014110315A1 (en) A blade positioning
EP3590632B1 (en) Blade assembly for a gas turbine and method for producing said assembly
WO2018069552A1 (en) Integrally cast turbomachine assembly, and method for producing a turbomachine assembly
WO2020165096A1 (en) Rotor blade for a thermal rotary machine and method for producing such a rotor blade

Legal Events

Date Code Title Description
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: UNKNOWN

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20180515

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)
REG Reference to a national code

Ref country code: DE

Ref legal event code: R079

Ref document number: 502016007269

Country of ref document: DE

Free format text: PREVIOUS MAIN CLASS: F01D0005120000

Ipc: F01D0005260000

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 5/26 20060101AFI20190430BHEP

Ipc: F01D 5/30 20060101ALI20190430BHEP

Ipc: F01D 5/02 20060101ALI20190430BHEP

INTG Intention to grant announced

Effective date: 20190522

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502016007269

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1193851

Country of ref document: AT

Kind code of ref document: T

Effective date: 20191115

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: SIEMENS SCHWEIZ AG, CH

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20191023

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200224

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191023

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200123

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191023

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191023

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191023

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191023

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191023

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200124

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200123

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191023

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200224

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191023

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191023

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502016007269

Country of ref document: DE

PG2D Information on lapse in contracting state deleted

Ref country code: IS

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191023

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191023

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191023

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191023

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191023

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200223

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20191231

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191023

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191023

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191023

26N No opposition filed

Effective date: 20200724

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20191208

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20191208

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191023

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20191231

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502016007269

Country of ref document: DE

Owner name: SIEMENS ENERGY GLOBAL GMBH & CO. KG, DE

Free format text: FORMER OWNER: SIEMENS AKTIENGESELLSCHAFT, 80333 MUENCHEN, DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191023

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20161208

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191023

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20201208

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201208

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191023

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191023

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1193851

Country of ref document: AT

Kind code of ref document: T

Effective date: 20211208

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20211208

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20231221

Year of fee payment: 8

Ref country code: FR

Payment date: 20231226

Year of fee payment: 8

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20231227

Year of fee payment: 8

Ref country code: CH

Payment date: 20240102

Year of fee payment: 8