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DE102009058853A1 - Turbine blade for gas turbine, comprises airfoil, shaft part that is formed adjacent to airfoil, and blade attaching area, where shaft part is provided between interior rim profile and blade attaching area - Google Patents

Turbine blade for gas turbine, comprises airfoil, shaft part that is formed adjacent to airfoil, and blade attaching area, where shaft part is provided between interior rim profile and blade attaching area Download PDF

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Publication number
DE102009058853A1
DE102009058853A1 DE200910058853 DE102009058853A DE102009058853A1 DE 102009058853 A1 DE102009058853 A1 DE 102009058853A1 DE 200910058853 DE200910058853 DE 200910058853 DE 102009058853 A DE102009058853 A DE 102009058853A DE 102009058853 A1 DE102009058853 A1 DE 102009058853A1
Authority
DE
Germany
Prior art keywords
shaft part
blade
airfoil
attaching area
turbine
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.)
Ceased
Application number
DE200910058853
Other languages
German (de)
Inventor
Richard 12305 Whitton
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Priority to DE200910058853 priority Critical patent/DE102009058853A1/en
Publication of DE102009058853A1 publication Critical patent/DE102009058853A1/en
Ceased legal-status Critical Current

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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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/12—Light metals
    • F05D2300/121—Aluminium
    • 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
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/228—Nitrides
    • F05D2300/2281—Nitrides of aluminium
    • 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

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The turbine blade comprises an airfoil (1), a shaft part (2) that is formed adjacent to the airfoil, and a blade attaching area (3). The shaft part is provided between an interior rim profile (4) and the blade attaching area with an aluminum coating and a ceramic coating is applied on the aluminum coating. The ceramic coating is applied a boron silica glass coating.

Description

Die Erfindung bezieht sich auf eine Turbinenschaufel einer Gasturbine, insbesondere eine Turbinenschaufel, welche im Bereich einer Hochdruckturbine in der ersten Stufe eingesetzt wird.The invention relates to a turbine blade of a gas turbine, in particular a turbine blade, which is used in the region of a high-pressure turbine in the first stage.

Turbinenschaufeln der beschriebenen Art sind, bedingt durch die chemische Zusammensetzung der Gase und die auftretenden Temperaturen, stark korrosionsgefährdet.Turbine blades of the type described are due to the chemical composition of the gases and the temperatures occurring, highly susceptible to corrosion.

Aus dem Stand der Technik ist es bekannt, zumindest den Schaftteil einer Turbinenschaufel zwischen einer Plattform eines Innenkranzprofils und dem Schaufelbefestigungsbereich mit einem Aluminid zu beschichten. Derartige Beschichtungen sind jedoch nicht unter allen Betriebsbedingungen ausreichend, um die Turbinenschaufel während ihrer gesamten Lebensdauer ausreichend zu schützen.From the prior art, it is known to coat at least the shaft portion of a turbine blade between a platform of an inner ring profile and the blade attachment area with an aluminide. However, such coatings are not sufficient under all operating conditions to adequately protect the turbine blade throughout its life.

Bei dickeren Aluminid-Schichten, welche eine längere Lebensdauer haben, treten Risse und Brüche auf. Weiterhin kann die Aluminid-Beschichtung in das Grundmaterial vordringen.For thicker aluminide layers, which have a longer life, cracks and breaks occur. Furthermore, the aluminide coating can penetrate into the base material.

Bei den aus dem Stand der Technik bekannten Aluminid-Beschichtungen des Schaftteils sollen diese gegen Heißkorrosion schützen, welche als ”Typ 2 Sulphidation” bekannt ist.In the known from the prior art aluminide coatings of the shaft part to protect these against hot corrosion, which is known as "Type 2 Sulphidation".

Der Erfindung liegt die Aufgabe zugrunde, eine Turbinenschaufel der eingangs genannten Art zu schaffen, welche bei einfachem Aufbau und einfacher, kostengünstiger Herstellbarkeit korrosionsgeschützt ist und eine hohe Lebensdauer aufweist.The invention has for its object to provide a turbine blade of the type mentioned above, which is corrosion-protected with a simple structure and simple, cost-effective manufacturability and has a long service life.

Erfindungsgemäß wird die Aufgabe durch die Merkmalskombination des Anspruchs 1 gelöst, die Unteransprüche zeigen weitere vorteilhafte Ausgestaltungen der Erfindung.According to the invention the object is achieved by the combination of features of claim 1, the dependent claims show further advantageous embodiments of the invention.

Erfindungsgemäß ist somit vorgesehen, eine zusätzliche Beschichtung über die Aluminid-Beschichtung aufzubringen, um die Aluminid-Beschichtung zu schützen. Die Aluminid-Beschichtung selbst verhindert oder verzögert die Korrosion des Grundmaterials, die ansonsten zu Haarrissen und letztendlich einem Totalversagen der Turbinenschaufel führen würde.The invention thus contemplates applying an additional coating over the aluminide coating to protect the aluminide coating. The aluminide coating itself prevents or delays the corrosion of the base material, which would otherwise result in hairline cracks and ultimately a total failure of the turbine blade.

Durch die erfindungsgemäß aufgebrachte zusätzliche Keramikbeschichtung wird die Aluminid-Beschichtung zusätzlich geschützt.The additional ceramic coating applied according to the invention additionally protects the aluminide coating.

Die Keramik-Beschichtung ist bevorzugterweise als Borsilikatglas-Beschichtung ausgebildet. Die Dicke der Beschichtungen ist abhängig von verschiedenen Faktoren, beispielsweise der Schaufellegierung, der Schaufeltemperatur und der thermischen Dehnung der zu schützenden Flächen. Bei einer Nickel-Legierung ergibt sich beispielsweise eine Schichtdicke von 0,020 bis 0,080 mm. Ein bevorzugter Wert liegt bei 0,010 bis 0,050 mm. Die Dicke der zusätzlich aufgebrachten Schicht ist auch abhängig von dem prozentualen Aluminium-Gehalt der darunterliegenden Aluminid-Beschichtung.The ceramic coating is preferably formed as a borosilicate glass coating. The thickness of the coatings depends on various factors, for example the blade alloy, the blade temperature and the thermal expansion of the surfaces to be protected. In the case of a nickel alloy, for example, a layer thickness of 0.020 to 0.080 mm results. A preferred value is 0.010 to 0.050 mm. The thickness of the additional coating also depends on the percentage of aluminum in the underlying aluminide coating.

Als Beispiel für eine derartige Beschichtung kann das Material PL134/R2 der Firma Indestructible Paint Co. genannt werden.As an example of such a coating, the material PL134 / R2 of the company Indestructible Paint Co. may be mentioned.

Bevorzugt wird die Schaufel am Schaftteil, welcher sich zwischen einem Innenkranzprofil und einem Schaufelbefestigungsbereich erstreckt, beschichtet. Abhängig von den jeweiligen Gegebenheiten kann auch eine Beschichtung des Schaufelblattes selbst mit der Keramikbeschichtung vorteilhaft sein.The blade is preferably coated on the shaft part, which extends between an inner rim profile and a blade attachment area. Depending on the particular circumstances, it may also be advantageous to coat the airfoil itself with the ceramic coating.

Im Folgenden wird die Erfindung anhand eines Ausführungsbeispiels in Verbindung mit der Zeichnung beschrieben. Dabei zeigt:In the following the invention will be described by means of an embodiment in conjunction with the drawing. Showing:

1 eine vereinfachte Seitenansicht einer erfindungsgemäßen Turbinenschaufel. 1 a simplified side view of a turbine blade according to the invention.

Die Turbinenschaufel umfasst ein in üblicher Weise ausgebildetes Schaufelblatt 1, an welches sich ein Schaftteil 2 anschließt.The turbine blade comprises a conventionally formed airfoil 1 , to which a shaft part 2 followed.

Das Schaufelblatt 1 kann mit einer Aluminisierung oder einer Platinbeschichtung versehen sein.The blade 1 may be provided with an aluminization or a platinum coating.

Der Schaftteil 2, welcher sich zwischen einem Innenkranzprofil 4 und einem Schaufelbefestigungsbereich 3 erstreckt, bildet einen Mitteltemperaturbereich der Turbinenschaufel, welcher benachbart zu dem Heißgasbereich des Schaufelblatts 1 angeordnet ist.The shaft part 2 which is located between an inner ring profile 4 and a blade attachment area 3 extends, forms a mean temperature range of the turbine blade, which adjacent to the hot gas region of the airfoil 1 is arranged.

Der Schaufelbefestigungsbereich 3 kann in Form eines Tannenbaumfußes ausgebildet sein.The blade attachment area 3 can be designed in the form of a fir tree foot.

Erfindungsgemäß ist der Schaftteil 2 mit einer Aluminisierung versehen, auf welche zusätzlich eine darüber liegende Keramikbeschichtung aufgebracht ist.According to the invention, the shaft part 2 provided with an aluminization on which an overlying ceramic coating is additionally applied.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Schaufelblattairfoil
22
Schaftteilshank part
33
SchaufelbefestigungsbereichBlade attachment area
44
InnenkranzprofilInterior cornice

Claims (3)

Turbinenschaufel einer Gasturbine mit einem Schaufelblatt (1), einem an das Schaufelblatt (1) anschließenden Schaftteil (2) sowie mit einem Schaufelbefestigungsbereich (3), wobei der Schaftteil (2) zwischen einem Innenkranzprofil (4) und dem Schaufelbefestigungsbereich (3) mit einer Aluminid-Beschichtung versehen ist und auf dieser Aluminid-Beschichtung eine Keramik-Beschichtung aufgebracht ist.Turbine blade of a gas turbine with an airfoil ( 1 ), one to the airfoil ( 1 ) subsequent shaft part ( 2 ) as well as with a Bucket attachment area ( 3 ), wherein the shaft part ( 2 ) between an inner rim profile ( 4 ) and the blade attachment area (FIG. 3 ) is provided with an aluminide coating and on this aluminide coating, a ceramic coating is applied. Turbinenschaufel nach Anspruch 1, dadurch gekennzeichnet, dass als Keramik-Beschichtung eine Borsilikatglas-Beschichtung aufgebracht ist.Turbine blade according to claim 1, characterized in that a borosilicate glass coating is applied as the ceramic coating. Turbinenschaufel nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass diese eine Hochdruckturbinenschaufel ist.Turbine blade according to claim 1 or 2, characterized in that it is a high-pressure turbine blade.
DE200910058853 2009-12-18 2009-12-18 Turbine blade for gas turbine, comprises airfoil, shaft part that is formed adjacent to airfoil, and blade attaching area, where shaft part is provided between interior rim profile and blade attaching area Ceased DE102009058853A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE200910058853 DE102009058853A1 (en) 2009-12-18 2009-12-18 Turbine blade for gas turbine, comprises airfoil, shaft part that is formed adjacent to airfoil, and blade attaching area, where shaft part is provided between interior rim profile and blade attaching area

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE200910058853 DE102009058853A1 (en) 2009-12-18 2009-12-18 Turbine blade for gas turbine, comprises airfoil, shaft part that is formed adjacent to airfoil, and blade attaching area, where shaft part is provided between interior rim profile and blade attaching area

Publications (1)

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DE102009058853A1 true DE102009058853A1 (en) 2011-06-22

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10047614B2 (en) * 2014-10-09 2018-08-14 Rolls-Royce Corporation Coating system including alternating layers of amorphous silica and amorphous silicon nitride

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2715290A1 (en) * 1976-04-05 1977-10-13 Brunswick Corp CERAMIC-METAL LAMINATES AND THE PROCESS FOR THEIR PRODUCTION
US6066405A (en) * 1995-12-22 2000-05-23 General Electric Company Nickel-base superalloy having an optimized platinum-aluminide coating
DE102005050661A1 (en) * 2005-10-20 2007-05-16 Forschungszentrum Juelich Gmbh Multi-layer thermal barrier coating systems and methods of manufacture

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2715290A1 (en) * 1976-04-05 1977-10-13 Brunswick Corp CERAMIC-METAL LAMINATES AND THE PROCESS FOR THEIR PRODUCTION
US6066405A (en) * 1995-12-22 2000-05-23 General Electric Company Nickel-base superalloy having an optimized platinum-aluminide coating
DE102005050661A1 (en) * 2005-10-20 2007-05-16 Forschungszentrum Juelich Gmbh Multi-layer thermal barrier coating systems and methods of manufacture

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10047614B2 (en) * 2014-10-09 2018-08-14 Rolls-Royce Corporation Coating system including alternating layers of amorphous silica and amorphous silicon nitride

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Effective date: 20131001