EP1284337B1 - Method for machining a coated gas turbine blade - Google Patents

Method for machining a coated gas turbine blade Download PDF

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Publication number
EP1284337B1
EP1284337B1 EP02405661A EP02405661A EP1284337B1 EP 1284337 B1 EP1284337 B1 EP 1284337B1 EP 02405661 A EP02405661 A EP 02405661A EP 02405661 A EP02405661 A EP 02405661A EP 1284337 B1 EP1284337 B1 EP 1284337B1
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EP
European Patent Office
Prior art keywords
roughness
turbine blade
gas turbine
protective layer
ceramic
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.)
Expired - Lifetime
Application number
EP02405661A
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German (de)
French (fr)
Other versions
EP1284337A1 (en
Inventor
Gordon Anderson
Reinhard Fried
Michael Lötzerich
Markus Oehl
Stefan Schlechtriem
Jörg Stengele
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General Electric Technology GmbH
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Alstom Technology AG
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Publication of EP1284337A1 publication Critical patent/EP1284337A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • 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
    • F05D2230/90—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
    • F05D2250/00—Geometry
    • F05D2250/60—Structure; Surface texture
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/60—Structure; Surface texture
    • F05D2250/62—Structure; Surface texture smooth or fine
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/60—Structure; Surface texture
    • F05D2250/62—Structure; Surface texture smooth or fine
    • F05D2250/621—Structure; Surface texture smooth or fine polished
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F05D2300/2118—Zirconium oxides
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12451—Macroscopically anomalous interface between layers
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24355—Continuous and nonuniform or irregular surface on layer or component [e.g., roofing, etc.]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24942—Structurally defined web or sheet [e.g., overall dimension, etc.] including components having same physical characteristic in differing degree
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/31—Surface property or characteristic of web, sheet or block

Definitions

  • the invention relates to a method for processing a ceramic Protective layer coated gas turbine part according to the preamble of the independent Claim. Such a procedure is over US-A-4,576,874.
  • a first protective layer of the turbine blade consists of a metallic one Alloy such as MCrAlY, where M is Ni, Co or Fe. This kind of metallic Coating serves as protection against oxidation.
  • a second, rougher coating from MCrAlY is applied to it with other coating parameters. This layer is also called "bond-coating".
  • Such coatings are numerous from the prior art and for example from US-A-3,528,861 or US-A-4,585,481.
  • TBC Thermal Barrier Coating
  • Ceramic coatings and methods for Coating are for example from the documents EP-A2-441 095, EP-A1-937,787, US-A-5,972,424, US-A-4,055,705, US-A-4,248,940, US-A-4,321,311, US-A-4,676,994, US-A-5,894,053.
  • the applied protective layers have in usually a relatively high surface roughness. This surface roughness but influences the heat transfer in a positive way, so that the base material is subjected to thermal stress with increasing roughness. To avoid this is a method for smoothing the surface, for example, from Scripture EP-A2-1 088 908 known. On the other hand, however, a polished one influences Surface the flow behavior and in particular the separation behavior negative.
  • EP-A1-1 081 332 discloses a turbine blade which is characterized that a strip with increased roughness is attached downstream. These Measure has a positive effect on the detachment behavior.
  • US-A-4,576,874 discloses a process for applying a ceramic protective layer.
  • WO97 / 21907 discloses a turbine blade suitable for use in the wet steam region is provided by Vorend- and final stages of steam turbines and a Erosion wear is caused by impacting water droplets and in the area the inlet edges and parts of the airfoil is treated so that a Reduction of erosion wear results.
  • a particularly advantageous possibility To reduce the erosive effect is that the blade in the area of its leading edge and its blade back or in at least a portion of which has a surface roughness which is opposite to the Surface roughness of the front of the airfoil is significantly enhanced.
  • this object is achieved in a method according to the claim 1 solved by the roughness of the already applied reduced ceramic layer on the base material at least a first place and at least a second place the original roughness of ceramic layer is maintained.
  • the gas turbine section is a turbine blade coated with Y stabilized Zr oxide.
  • the roughness can only at least one downstream point of the Turbine blade are maintained while the remaining surface of the turbine blade smoothed.
  • the heat transfer is thus advantageously reduced, so that the heat transfer is deteriorated here, and with the same cooling performance improves the base material is cooled.
  • the ceramic Protective layer rough, so that there is some turbulence generated and the flow longer. The efficiency of the entire system is through this simple Measures advantageously increased.
  • FIG. 1 schematically shows a section through a turbine blade 1 of FIG Gas turbine.
  • the turbine blade 1 is on the surface 2 with a ceramic Protective layer 3 has been coated.
  • the ceramic protective layer 3 (Engl Barrier Coating, TBC), which is Y stabilized Zr oxide, serves as Protection against the turbine blade 1 flowing around hot gas 4, whose streamlines are visible in the figure 1.
  • Such ceramic coatings and methods of coating are, for example from the documents EP-A2-441 095, EP-A1-937,787, US-A-5,972,424, U.S. Patent Nos. 4,055,705; 4,248,940; 321,311; 4,676,994; 5,894,053 known. It is known that the applied protective layer has a certain surface roughness having.
  • the average roughness (R a , average roughness) at the first location 5 can be reduced to a maximum of 1/3 of the original average roughness.
  • the roughness R T will thus reduce, for example, from about 50 ⁇ m to 20 ⁇ m.
  • Such a smoothing of the TBC surface lowers the heat transfer coefficient by 20% to 30%. This therefore brings a significantly improved protection of the base material 1 used before the hot gases 4 at these points. 5
  • the roughness of the ceramic Protective layer 3 at least one downstream location 6, at which the detachment the hot gas flow takes place be maintained.
  • the detachment area 7 becomes thus overall smaller in comparison with a completely smooth surface, because at the risk of detachment 6 a certain turbulence, the detachment counteracts, is preserved.
  • the remaining ceramic protective layer 3 is smoothed for the purpose of a deteriorated heat transfer, ie reduced to a maximum of 1/3 of the original roughness.
  • On the smooth ground parts of the surface of the heat transfer is thus advantageously reduced, so that the heat transfer is further deteriorated here, and thus - with the same cooling performance - the base material is cooled improved.
  • the digits are 6 but not connected, but independently. This measure further serves to positively influence the detachment behavior. Between these places 6 becomes roughness for the purpose of deteriorated heat transfer again completely reduced.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Description

TECHNISCHES GEBIETTECHNICAL AREA

Die Erfindung betrifft ein Verfahren zur Bearbeitung eines mit einer keramischen Schutzschicht beschichteten Gasturbinenteils gemäss dem Oberbegriff des unabhängigen Patentanspruchs. Ein solches Verfahren ist aus US-A-4,576,874 bekannt.The invention relates to a method for processing a ceramic Protective layer coated gas turbine part according to the preamble of the independent Claim. Such a procedure is over US-A-4,576,874.

STAND DER TECHNIKSTATE OF THE ART

Es ist allgemein und zahlreich bekannt, Turbinenschaufeln, also Leit- oder Laufschaufeln von Gasturbinen, mit einer oder mehreren Schutzschichten zu versehen, um die Turbinenschaufel vor den thermischen und mechanischen Belastungen, vor Oxidation oder anderen, schädlichen Einflüssen während des Betriebes zu schützen und die Lebensdauer der Turbinenschaufel auf diese Weise zu verlängern. Dabei besteht eine erste Schutzschicht der Turbinenschaufel in der Regel aus einer metallischen Legierung wie MCrAIY, wobei M für Ni, Co oder Fe steht. Diese Art der metallischen Beschichtung dient als Schutz vor Oxidation. Eine zweite, rauhere Beschichtung aus MCrAlY wird mit anderen Beschichtungsparametern darauf aufgetragen. Diese Schicht wird auch als "bond-coating" bezeichnet. Solche Beschichtungen sind zahlreich aus dem Stand der Technik und beispielsweise aus US-A-3,528,861 oder US-A-4,585,481 bekannt.It is common and well known, turbine blades, so guide or moving blades of gas turbines to be provided with one or more protective layers, around the turbine blade before the thermal and mechanical loads, before Oxidation or other harmful effects during operation and extend the life of the turbine blade in this way. there As a rule, a first protective layer of the turbine blade consists of a metallic one Alloy such as MCrAlY, where M is Ni, Co or Fe. This kind of metallic Coating serves as protection against oxidation. A second, rougher coating from MCrAlY is applied to it with other coating parameters. This layer is also called "bond-coating". Such coatings are numerous from the prior art and for example from US-A-3,528,861 or US-A-4,585,481.

Zudem wird eine weitere Schutzschicht aus TBC (Thermal Barrier Coating), welche aus einem keramischen Material (Y stabilisiertes Zr-Oxid) besteht und als thermischer Schutz dient, aufgebracht. Keramische Beschichtungen und Methoden zur Beschichtung sind beispielsweise aus den Schriften EP-A2-441 095, EP-A1-937,787, US-A-5,972,424, US-A-4,055,705, US-A-4,248,940, US-A-4,321,311, US-A-4,676,994, US-A-5,894,053 bekannt. Die aufgetragenen Schutzschichten haben in der Regel eine relativ hohe Oberflächenrauhigkeit. Diese Oberflächenrauhigkeit beeinflusst aber den Wärmeübergang auf positive Weise, so dass das Grundmaterial mit zunehmender Rauhigkeit thermisch verstärkt belastet wird. Um dies zu vermeiden ist ein Verfahren zur Glättung der Oberfläche beispielsweise aus der Schrift EP-A2-1 088 908 bekannt. Auf der anderen Seite beeinflusst aber eine geschliffene Oberfläche das Strömungsverhalten und insbesondere das Ablöseverhalten negativ.In addition, another protective layer of TBC (Thermal Barrier Coating), which consists of a ceramic material (Y stabilized Zr oxide) and as a thermal Protection serves, upset. Ceramic coatings and methods for Coating are for example from the documents EP-A2-441 095, EP-A1-937,787, US-A-5,972,424, US-A-4,055,705, US-A-4,248,940, US-A-4,321,311, US-A-4,676,994, US-A-5,894,053. The applied protective layers have in usually a relatively high surface roughness. This surface roughness but influences the heat transfer in a positive way, so that the base material is subjected to thermal stress with increasing roughness. To avoid this is a method for smoothing the surface, for example, from Scripture EP-A2-1 088 908 known. On the other hand, however, a polished one influences Surface the flow behavior and in particular the separation behavior negative.

EP-A1-1 081 332 offenbart eine Turbinenschaufel, die sich dadurch auszeichnet, dass ein Streifen mit einer erhöhten Rauhigkeit abstromseitig angebracht ist. Diese Massnahme wirkt sich positiv auf das Ablöseverhalten aus.EP-A1-1 081 332 discloses a turbine blade which is characterized that a strip with increased roughness is attached downstream. These Measure has a positive effect on the detachment behavior.

US-A-4,576,874 offenbart einen Prozess zum Aufbringen einer keramischen Schutzschicht.US-A-4,576,874 discloses a process for applying a ceramic protective layer.

W097/21907 offenbart eine Turbinenschaufel, die für den Einsatz im Nassdampfbereich von Vorend- und Endstufen von Dampfturbinen vorgesehen ist und einem Erosionsverschleiss durch aufschlagende Wassertröpfchen unterliegt und im Bereich der Eintrittskanten und Teilen des Schaufelblatts so behandelt ist, dass sich eine Herabsetzung des Erosionsverschleisses ergibt. Eine besonders vorteilhafte Möglichkeit zur Verminderung der erosiven Wirkung besteht darin, dass das Schaufelblatt im Bereich seiner Eintrittskante und seines Schaufelrückens oder in mindestens einem Teilbereich davon eine Oberflächenrauhigkeit aufweist, die gegenüber der Oberflächenrauhigkeit der Vorderseite des Schaufelblattes deutlich verstärkt ist.WO97 / 21907 discloses a turbine blade suitable for use in the wet steam region is provided by Vorend- and final stages of steam turbines and a Erosion wear is caused by impacting water droplets and in the area the inlet edges and parts of the airfoil is treated so that a Reduction of erosion wear results. A particularly advantageous possibility To reduce the erosive effect is that the blade in the area of its leading edge and its blade back or in at least a portion of which has a surface roughness which is opposite to the Surface roughness of the front of the airfoil is significantly enhanced.

DARSTELLUNG DER ERFINDUNGPRESENTATION OF THE INVENTION

Es ist Aufgabe der Erfindung, ein Verfahren zu schaffen, mit dem der Wärmeübergang von einem mit einer keramischen Schutzschicht beschichteten Gasturbinenteil, um welches ein Heissgas strömt, zu dem Heissgas verschlechtert wird, so dass ein verbesserter Schutz des Grundmaterials des Gasturbinenteils erreicht wird und gleichzeitig das Strömungsverhaltensverhalten um das Gasturbinenteil und damit der Wirkungsgrad der gesamten Anlage positiv beeinflusst wird.It is an object of the invention to provide a method by which the heat transfer of a ceramic protective layer coated gas turbine part, around which a hot gas flows, is deteriorated to the hot gas, so that a improved protection of the base material of the gas turbine part is achieved and at the same time the flow behavior around the gas turbine part and thus the Efficiency of the entire system is positively influenced.

Erfindungsgemäss wird diese Aufgabe bei einem Verfahren gemäss dem Anspruch 1 dadurch gelöst, dass die Rauhigkeit der bereits aufgetragenen keramischen Schicht auf dem Grundmaterial an mindestens einer ersten Stelle reduziert wird und an mindestens einer zweiten Stelle die ursprüngliche Rauhigkeit der keramischen Schicht beibehalten wird.According to the invention, this object is achieved in a method according to the claim 1 solved by the roughness of the already applied reduced ceramic layer on the base material at least a first place and at least a second place the original roughness of ceramic layer is maintained.

Es besteht prinzipiell die Möglichkeit, die Rauhigkeit durch Schleifen, Sandstrahlen, Polieren, Trowalisieren, Bürsten oder auf andere, geeignete Arten, welche aus dem Stand der Technik bekannt sind, zu reduzieren.There is in principle the possibility of the roughness by grinding, sandblasting, Polishing, Trowalisieren, brushes or other, suitable types, which from the State of the art are known to reduce.

In einer besonderen Ausführungsform handelt es sich bei dem Gasturbinenteil um eine Turbinenschaufel, welche mit Y stabilisiertem Zr-Oxid beschichtet ist.In a particular embodiment, the gas turbine section is a turbine blade coated with Y stabilized Zr oxide.

Um das Ablöseverhalten an der Oberfläche der Turbinenschaufel positiv zu beeinflussen, kann die Rauhigkeit an nur mindestens einer stromabgelegenen Stelle der Turbinenschaufel beibehalten werden, während die restliche Oberfläche der Turbinenschaufel glatt geschliffen wird. An den glatt geschliffenen Teilen der Oberfläche wird der Wärmeübergang damit vorteilhaft reduziert, so dass der Wärmeübergang hier verschlechtert wird, und bei gleicher Kühlleistung das Grundmaterial verbessert gekühlt wird. An den Stellen jedoch, an denen Ablösung droht, bleibt die keramische Schutzschicht rauh, so dass dort eine gewisse Turbulenz erzeugt wird und die Strömung länger anliegt. Der Wirkungsgrad der gesamten Anlage wird durch diese einfache Massnahmen vorteilhaft erhöht.To positively influence the detachment behavior on the surface of the turbine blade, The roughness can only at least one downstream point of the Turbine blade are maintained while the remaining surface of the turbine blade smoothed. On the smoothed parts of the surface the heat transfer is thus advantageously reduced, so that the heat transfer is deteriorated here, and with the same cooling performance improves the base material is cooled. However, at the points where detachment threatens, remains the ceramic Protective layer rough, so that there is some turbulence generated and the flow longer. The efficiency of the entire system is through this simple Measures advantageously increased.

KURZE BESCHREIBUNG DER ZEICHNUNGENBRIEF DESCRIPTION OF THE DRAWINGS

Die Erfindung ist anhand der beiliegenden Figuren näher erläutert, wobei

Fig. 1
einen Schnitt durch eine Turbinenschaufel zeigt, welche nach dem erfindungsgemässen Verfahren bearbeitet wurde und
Fig. 2
einen Schnitt durch eine zweite Ausführungsform einer Turbinenschaufel zeigt, welche nach dem erfindungsgemässen Verfahren bearbeitet wurde.
The invention is explained in more detail with reference to the accompanying figures, wherein
Fig. 1
shows a section through a turbine blade, which has been processed by the inventive method and
Fig. 2
shows a section through a second embodiment of a turbine blade, which has been processed by the inventive method.

Es werden nur die für die Erfindung wesentlichen Elemente dargestellt. Gleiche Elemente in unterschiedlichen Figuren sind gleich bezeichnet. Strömungsrichtungen werden durch Pfeile dargestellt.Only the elements essential to the invention are shown. Same Elements in different figures are labeled the same. flow directions are represented by arrows.

WEG ZUR AUSFÜHRUNG DER ERFINDUNGWAY FOR CARRYING OUT THE INVENTION

Die Figur 1 zeigt schematisch einen Schnitt durch eine Turbinenschaufel 1 einer Gasturbine. Die Turbinenschaufel 1 ist an der Oberfläche 2 mit einer keramischen Schutzschicht 3 beschichtet worden. Die keramische Schutzschicht 3 (engl. Thermal Barrier Coating, TBC), bei der es sich um Y stabilisiertes Zr-Oxid handelt, dient als Schutz vor dem die Turbinenschaufel 1 umströmenden Heissgas 4, dessen Stromlinien in der Figur 1 sichtbar sind.FIG. 1 schematically shows a section through a turbine blade 1 of FIG Gas turbine. The turbine blade 1 is on the surface 2 with a ceramic Protective layer 3 has been coated. The ceramic protective layer 3 (Engl Barrier Coating, TBC), which is Y stabilized Zr oxide, serves as Protection against the turbine blade 1 flowing around hot gas 4, whose streamlines are visible in the figure 1.

Derartige keramische Beschichtungen und Verfahren zur Beschichtung sind beispielsweise aus den Schriften EP-A2-441 095, EP-A1-937,787, US-A-5,972,424, US-A-4,055,705, US-A-4,248,940, US-A-321, 311, US-A-4,676,994, US-A-5,894,053 bekannt. Es dabei bekannt, dass die aufgetragene Schutzschicht eine gewisse Oberflächenrauhigkeit aufweist.Such ceramic coatings and methods of coating are, for example from the documents EP-A2-441 095, EP-A1-937,787, US-A-5,972,424, U.S. Patent Nos. 4,055,705; 4,248,940; 321,311; 4,676,994; 5,894,053 known. It is known that the applied protective layer has a certain surface roughness having.

Erfindungsgemäss wird daher vorgeschlagen, die Rauhigkeit der bereits aufgetragenen keramischen Schicht 3 an mindestens einer ersten Stelle 5 an der Oberfläche zu reduzieren, während die Rauhigkeit an mindestens einer zweiten Stelle 6 wie nach dem Beschichtungsvorgang erhalten bleibt. Beispielsweise kann also die Durchschnittsrauhigkeit (Ra, average roughness) an der ersten Stelle 5 auf maximal 1/3 der ursprünglichen Durchschnittsrauhigkeit reduziert werden. Die Rauhigkeit RT wird sich damit beispielsweise von etwa 50 µm auf 20 µm reduzieren. Eine solche Glättung der TBC Oberfläche senkt die Wärmeübergangszahl um 20% bis 30%. Dies bringt also einen deutlich verbesserten Schutz des eingesetzten Grundmaterials 1 vor den Heissgasen 4 an diesen Stellen 5.According to the invention, it is therefore proposed to reduce the roughness of the already applied ceramic layer 3 at at least a first location 5 on the surface, while the roughness is maintained at at least one second location 6 as after the coating process. For example, the average roughness (R a , average roughness) at the first location 5 can be reduced to a maximum of 1/3 of the original average roughness. The roughness R T will thus reduce, for example, from about 50 μm to 20 μm. Such a smoothing of the TBC surface lowers the heat transfer coefficient by 20% to 30%. This therefore brings a significantly improved protection of the base material 1 used before the hot gases 4 at these points. 5

Es besteht prinzipiell die Möglichkeit, die Rauhigkeit durch Schleifen, Sandstrahlen, Polieren, Trowalisieren, Bürsten oder auf andere, geeignete Arten, welche aus dem Stand der Technik bekannt sind, zu reduzieren. Zu Schleifen besonders geeignet sind Siliziumkarbid oder Diamanten, welche mit einer Kunststoffbindung auf Bändern oder Scheiben befestigt sind.There is in principle the possibility of the roughness by grinding, sandblasting, Polishing, Trowalisieren, brushes or other, suitable types, which from the State of the art are known to reduce. Especially suitable for grinding are silicon carbide or diamonds, which with a plastic bond on tapes or discs are attached.

In einer ersten Ausführungsform (Fig. 1) kann die Rauhigkeit der keramischen Schutzschicht 3 an mindestens einer stromabgelegenen Stelle 6, an der die Ablösung der Heissgasströmung stattfindet, beibehalten werden. Das Ablösegebiet 7 wird somit insgesamt kleiner ausfallen im Vergleich mit einer gänzlich geglätteten Oberfläche, da an der ablösegefährdeten Stelle 6 eine gewisse Turbulenz, die der Ablösung entgegenwirkt, erhalten bleibt.In a first embodiment (Fig. 1), the roughness of the ceramic Protective layer 3 at least one downstream location 6, at which the detachment the hot gas flow takes place, be maintained. The detachment area 7 becomes thus overall smaller in comparison with a completely smooth surface, because at the risk of detachment 6 a certain turbulence, the detachment counteracts, is preserved.

Die restliche keramische Schutzschicht 3 wird zum Zwecke eines verschlechterten Wärmeübergangs glattschliffen, d.h. auf maximal 1/3 der ursprünglichen Rauheit reduziert. Dies bedeutet für die Praxis, dass die Durchschnittsrauhigkeit Ra kleiner als 5 µm ist. An den glatt geschliffenen Teilen der Oberfläche wird der Wärmeübergang damit vorteilhaft reduziert, so dass der Wärmeübergang hier weiter verschlechtert wird, und somit - bei gleicher Kühlleistung - das Grundmaterial verbessert gekühlt wird.The remaining ceramic protective layer 3 is smoothed for the purpose of a deteriorated heat transfer, ie reduced to a maximum of 1/3 of the original roughness. This means in practice that the average roughness R a is less than 5 μm. On the smooth ground parts of the surface of the heat transfer is thus advantageously reduced, so that the heat transfer is further deteriorated here, and thus - with the same cooling performance - the base material is cooled improved.

Der Wirkungsgrad der gesamten Anlage wird durch diese einfachen Massnahmen vorteilhaft erhöht.The efficiency of the entire system is determined by these simple measures advantageously increased.

In der zweiten Ausführungsform der Turbinenschaufel 1 gemäss der Figur 2 wird die Rauhigkeit der keramischen Schutzschicht 3 an verschiedenen Stellen 6 an der stromabgelegenen Seite der Turbinenschaufel 1 beibehalten. Die Stellen 6 sind jedoch nicht zusammenhängend, sondern unabhängig voneinander. Diese Massnahme dient weiter dazu, das Ablöseverhalten positiv zu beeinflussen. Zwischen diesen Stellen 6 wird zum Zwecke des verschlechterten Wärmeübergangs die Rauhigkeit wiederum ganz reduziert.In the second embodiment of the turbine blade 1 according to the figure 2, the Roughness of the ceramic protective layer 3 at various points 6 at the maintained downstream side of the turbine blade 1. The digits are 6 but not connected, but independently. This measure further serves to positively influence the detachment behavior. Between these places 6 becomes roughness for the purpose of deteriorated heat transfer again completely reduced.

Die Erfindung ist nicht auf die beschriebene Ausführungsbeispiele reduziert, sondern bezieht sich allgemein auf das durch die nachfolgenden Ansprüche definierte Verfahren.The invention is not reduced to the described embodiments, but generally refers to the method defined by the following claims.

BEZUGSZEICHENLISTELIST OF REFERENCE NUMBERS

11
Turbinenschaufel, GasturbinenteilTurbine blade, gas turbine part
22
Oberfläche der Turbinenschaufel 1Surface of the turbine blade 1
33
Keramische SchutzschichtCeramic protective layer
44
Heissgashot gas
55
Stellen der Schutzschicht (3), bearbeitetMake the protective layer (3), edited
66
Stellen der Schutzschicht (3), unbearbeitetMake the protective layer (3), unprocessed
77
Ablösegebietseparation region

Claims (5)

  1. Process for treating a ceramic protective layer (3) which is applied to the surface (2) of a gas turbine part (1), the ceramic protective layer (3) having a certain roughness after it has been applied to the gas turbine part (1), characterized in that the roughness of the ceramic layer (3) which has already been applied to the base material (1) is reduced at at least one first location (5), and the original roughness of the ceramic layer (3) is retained at at least one second location (6).
  2. Treating process according to Claim 1, characterized in that the roughness of the applied ceramic layer (3) is reduced at the first location (5) to at most 1/3 of the original average roughness.
  3. Treating process according to one of Claims 1 or 2, characterized in that the gas turbine part (1) is a turbine blade or vane (1), and the roughness is retained only at at least one location (6) on the turbine blade or vane (1) which is remote from the flow and is at risk of detachment, while the roughness is reduced on the remaining surface area (2) of the turbine blade or vane (1).
  4. Treating process according to Claim 3, characterized in that the gas turbine part (1) is coated with Y-stabilized Zr oxide.
  5. Treating process according to one of the preceding claims, characterized in that the roughness is reduced by grinding, sand-blasting, polishing, smoothing, brushing or in some other suitable way.
EP02405661A 2001-08-14 2002-07-30 Method for machining a coated gas turbine blade Expired - Lifetime EP1284337B1 (en)

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