EP2354454A1 - Turbinenschaufel mit variabel Oxidationsbeständiger Beschichtung - Google Patents

Turbinenschaufel mit variabel Oxidationsbeständiger Beschichtung Download PDF

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Publication number
EP2354454A1
EP2354454A1 EP10152433A EP10152433A EP2354454A1 EP 2354454 A1 EP2354454 A1 EP 2354454A1 EP 10152433 A EP10152433 A EP 10152433A EP 10152433 A EP10152433 A EP 10152433A EP 2354454 A1 EP2354454 A1 EP 2354454A1
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EP
European Patent Office
Prior art keywords
region
resistant coating
coating
oxidation resistant
turbine blade
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.)
Withdrawn
Application number
EP10152433A
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English (en)
French (fr)
Inventor
Geoffrey Marchant
Mick Whitehurst
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
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Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP10152433A priority Critical patent/EP2354454A1/de
Publication of EP2354454A1 publication Critical patent/EP2354454A1/de
Withdrawn legal-status Critical Current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
    • 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
    • F05D2260/95—Preventing corrosion
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/14—Noble metals, i.e. Ag, Au, platinum group metals
    • 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
    • F05D2300/14—Noble metals, i.e. Ag, Au, platinum group metals
    • F05D2300/143—Platinum group metals, i.e. Os, Ir, Pt, Ru, Rh, Pd
    • 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
    • F05D2300/15—Rare earth metals, i.e. Sc, Y, lanthanides
    • 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

Definitions

  • the present invention relates to a turbine blade with a platform section and an airfoil section extending from the platform section where the airfoil section comprises an oxidation resistant coating.
  • the turbine blades are exposed to hot combustion gases which can oxidise the unprotected base material of the turbine blades. Hence, the blades are coated by an oxidation resistant coating to increase their lifetime.
  • cooling air is used to cool the blades during operation of the gas turbine. Unfortunately the amount of cooling air which can be utilized in some regions of a turbine blade is limited so that these regions experience the highest temperatures of the blade during operation.
  • turbine blades are coated with an aluminide coating or with a so called MCrAlY-coating where M stands for nickel (Ni), cobalt (Co) or Iron (Fe) and Y stands for Yttrium or another rare earth metal.
  • M nickel
  • Co cobalt
  • Fe Iron
  • Y Yttrium or another rare earth metal.
  • These kinds of coatings are used to increase oxidation resistance of the blade.
  • Turbine blades with an oxidation resistant coating are, for example, disclosed in US 2002/0170176 A1 and WO 2007/140805 A1 .
  • the turbine blade disclosed in US 2002/0170176 A1 may also comprise a thermal barrier coating above the oxidation resistant coating to reduce the heat experienced by the oxidation resistant coating. This thermal barrier coating may be applied to selected areas of the airfoil usually the tip and regions in proximity of the tip.
  • An inventive turbine blade comprises an airfoil section where the airfoil section includes a first region and at least a second region.
  • the exterior of the airfoil section comprises an oxidation resistant coating.
  • the first region is coated with an oxidation resistant coating that has a higher oxidation resistance than the oxidation resistance coating of the second region.
  • an inventive turbine blade may comprise a platform section as well as an airfoil section extending from the platform section and including a blade tip.
  • the airfoil section then further includes a tip region extending from the blade tip towards the platform section as first region and an intermediate airfoil region extending from the tip region to the platform section as second region.
  • the tip region is then coated with an oxidation resistant coating that has a higher oxidation resistance than the oxidation resistant coating of the intermediate airfoil region.
  • the airfoils of the state of the art turbine blades are coated with the same kind of oxidation resistant coating in all regions.
  • an additional thermal barrier coating may be applied onto the oxidation resistant coating in these regions.
  • applying a thermal barrier coating is elaborate and expensive.
  • the invention offers a less cost intensive and less elaborate way of providing adequate oxidation resistance of the airfoil.
  • Forming an oxidation resistant coating having a higher oxidation resistance in the first region than in the second region allows for adapting the oxidation resistance of the different airfoil regions to the actual needs.
  • a lower quality oxidation resistant coating than, e.g., at the blade tip can be used in, e.g., the intermediate airfoil region so that the costs for coating the airfoil section are reduced since the major part of the airfoil section can be coated with a relatively low cost, simple coating like, for example, a simple aluminide coating while a more oxidation resistant coating like, for example, a platinum aluminide coating is only used where it is really needed.
  • the invention overcomes the need to use an expensive high quality coating on the whole blade or the need to use an additional coating in some regions.
  • the oxidation resistant coating of the second region may comprise aluminium.
  • it may be, as already mentioned, a simple aluminide coating.
  • Such a coating is relatively cheap and relatively easy to apply, e.g., by a chemical vapour deposition (CVD) process or a physical vapour deposition (PVD) process.
  • CVD chemical vapour deposition
  • PVD physical vapour deposition
  • the oxidation resistant coating of the first region may, in particular, be a modification of the oxidation resistant coating of the second region by use of an additive effecting the higher oxidation resistance.
  • the additive may be a precious material, i. e. ruthenium (Ru), rhodium (Rh), palladium (Pd), silver (Ag), osmium (Os), iridium (Ir), platinum (Pt), or gold (Au).
  • the additive may be a rare earth metal, such as e.g. Hafnium (Hf) and Yttrium (Y).
  • an additive to increase oxidation resistance of the coating allows for applying an oxidation resistant coating to the first region which is similar to the less oxidation resistant coating of the second region. This means that typically the same kind of coating process can be used for the first region as for the second region where only the source material of the process is changed.
  • the oxidation resistant coating of the second region is a simple aluminide coating and the additive comprises platinum.
  • the oxidation resistant coating of the first region will be a platinum aluminide coating.
  • These two coatings can be used in a range of operating temperatures of gas turbines and are straight forward to apply, for example by a chemical vapour deposition process.
  • the oxidation resistant coating of the first region and the oxidation resistant coating of the second region can be in the form of CVD-coatings.
  • other coatings e.g., different MCrAlY-coatings could be used in the first and second regions of the airfoil.
  • other coating techniques could be used in the coating process, e.g., thermal spraying.
  • the tip region which is coated with the oxidation resistant coating having increased oxidation resistance as compared to the oxidation resistant coating of the intermediate airfoil section preferably extends towards the platform section over a length of not more than 40 mm, in particular not more than 20 mm and preferably not more than 10 mm in order to restrict the oxidation resistant coating with the high oxidation resistance only to the region where it is necessary.
  • the tip region should extend towards the platform section over a length of at least 2 mm, preferably at least 5 mm in order to avoid the region with the oxidation resistant coating having a high oxidation resistance to be too small.
  • the tip region extends from the blade tip towards the platform section over a length of 5 to 10 mm it can be assured that the hottest region during operation of the gas turbine is suitably protected by the oxidation resistant coating with the high oxidation existence.
  • FIG. 1 schematically shows an example of the inventive turbine blade for illustration purposes.
  • the turbine blade is shroudless and comprises a platform section 1, an airfoil section 3 extending from the platform section 1 and a root section 5 extending from the platform section 1 in a direction opposite to the direction in which the airfoil section 3 extends.
  • the end of the airfoil section 3 which is furthest from the platform section 1 is formed by a tip 7.
  • a tip region 9 - which may be shroudless - extends from the tip 7 towards the platform section 1 over a length d which is, in the present embodiment, at least 2 mm and at most 20 mm, preferably over a length d of 5 to 10 mm. However, embodiments with a length larger than 20 mm are also possible.
  • the region between the tip region 9 and the platform section 1 is referred to as intermediate airfoil region 11 throughout this description.
  • the turbine blade comprises an oxidation resistant coating which is applied to the exterior of the airfoil section 3 and, in the present embodiment, also to the exterior of the platform section 1. While the coatings of the intermediate airfoil region 11 and the platform section 1 are the same, the coating of the tip region 9 differs from the coating of the intermediate airfoil section 11.
  • the coating of the tip region 9 is a coating having a higher oxidation resistance than the coating in the intermediate airfoil region 9 and, if present, the coating of the platform section 1.
  • the intermediate airfoil region 11 and the platform section 1 are coated with a simple aluminide coating which can be, e.g., applied by the chemical deposition process.
  • aluminide coating like, for example pack coating or PVD, can also be used.
  • the coating of the tip region 9 differs from the coating of the intermediate airfoil region 11 and the platform section 1 in that it is a platinum aluminide coating rather than a simple aluminide coating. Due to the platinum used as additive to the coating material the coating has a higher oxidation resistance than a simple aluminide coating. Hence, the airfoil is coated with an oxidation resistant coating having a high oxidation resistance in the airfoil region 9 which experiences the hottest temperatures during operation of a gas turbine, namely the tip region 9, while the other regions, which only experience lower temperatures than the tip region 9, are coated with a less oxidation resistant coating which is, however, sufficient in those cooler regions. Like the simple aluminide coating the platinum aluminide coating can be applied with a chemical vapour deposition process. However, other deposition processes, like pack coating or PVD, are generally possible.
  • MCrAlY-coatings As an alternative to the aluminide and platinum aluminide coating it would also be possible to apply different MCrAlY-coatings to the tip region 9 and the intermediate airfoil region 11. For example, a MCrAlY-coating having a higher chromium content could be used in the intermediate airfoil region while a MCrAlY having a higher aluminium content could be used in the tip region.
  • the MCrAlY coatings could be applied by use of a thermal spray process, like high velocity oxygen fuel spraying (HVOF) or plasma spraying. Moreover, it is generally possible, but not necessary, to apply a thermal barrier coating onto the oxidation resistant coating.
  • HVOF high velocity oxygen fuel spraying
  • plasma spraying it is generally possible, but not necessary, to apply a thermal barrier coating onto the oxidation resistant coating.
  • the present invention uses a high oxidation resistant coating only at the blade tip and adjacent areas while the remainder of the blade is coated with a cheaper, less oxidation resistant coating. This allows the blade to have an improved oxidation life at the hot tip region while adding only a small cost to the component as compared to use of the high oxidation resistant coating on the whole blade.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
EP10152433A 2010-02-02 2010-02-02 Turbinenschaufel mit variabel Oxidationsbeständiger Beschichtung Withdrawn EP2354454A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP10152433A EP2354454A1 (de) 2010-02-02 2010-02-02 Turbinenschaufel mit variabel Oxidationsbeständiger Beschichtung

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10152433A EP2354454A1 (de) 2010-02-02 2010-02-02 Turbinenschaufel mit variabel Oxidationsbeständiger Beschichtung

Publications (1)

Publication Number Publication Date
EP2354454A1 true EP2354454A1 (de) 2011-08-10

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2781617A1 (de) 2013-03-19 2014-09-24 Alstom Technology Ltd Verfahren zum Beschichten einer Komponente einer Turbomaschine und beschichtete Komponente für eine Turbomaschine
EP2857546A1 (de) * 2013-10-02 2015-04-08 Siemens Aktiengesellschaft Komponente einer Turbomaschine und Verfahren zum Beschichten einer Turbomaschinenkomponente
WO2015077163A1 (en) * 2013-11-19 2015-05-28 United Technologies Corporation Article having variable composition coating

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0139396A1 (de) * 1983-08-29 1985-05-02 Westinghouse Electric Corporation Turbinenschaufel mit, an verschiedenen Stellen, verschiedener Schutzschicht
EP0844368A2 (de) * 1996-11-26 1998-05-27 United Technologies Corporation Teilbeschichtung von Gasturbinenschaufeln zur Erhöhung der Dauerfestigkeit
EP1076158A1 (de) * 1999-08-11 2001-02-14 General Electric Company Bauteil einer Gasturbine mit positionsabhängigen Schutzbeschichtungen
US20020170176A1 (en) 2001-05-15 2002-11-21 Rigney Joseph David Turbine airfoil process sequencing for optimized tip performance
EP1327702A1 (de) * 2002-01-10 2003-07-16 ALSTOM (Switzerland) Ltd MCrAlY-Haftschicht und Verfahren zur Herstellung einer MCrAlY-Haftschichtbeschichtung
EP1627936A2 (de) * 2004-08-20 2006-02-22 General Electric Company Mit einer lokalisierten Festbeschichtung gesicherter Artikel
WO2007140805A1 (en) 2006-06-08 2007-12-13 Siemens Aktiengesellschaft Coated turbine component and method of coating a turbine component

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0139396A1 (de) * 1983-08-29 1985-05-02 Westinghouse Electric Corporation Turbinenschaufel mit, an verschiedenen Stellen, verschiedener Schutzschicht
EP0844368A2 (de) * 1996-11-26 1998-05-27 United Technologies Corporation Teilbeschichtung von Gasturbinenschaufeln zur Erhöhung der Dauerfestigkeit
EP1076158A1 (de) * 1999-08-11 2001-02-14 General Electric Company Bauteil einer Gasturbine mit positionsabhängigen Schutzbeschichtungen
US20020170176A1 (en) 2001-05-15 2002-11-21 Rigney Joseph David Turbine airfoil process sequencing for optimized tip performance
EP1327702A1 (de) * 2002-01-10 2003-07-16 ALSTOM (Switzerland) Ltd MCrAlY-Haftschicht und Verfahren zur Herstellung einer MCrAlY-Haftschichtbeschichtung
EP1627936A2 (de) * 2004-08-20 2006-02-22 General Electric Company Mit einer lokalisierten Festbeschichtung gesicherter Artikel
WO2007140805A1 (en) 2006-06-08 2007-12-13 Siemens Aktiengesellschaft Coated turbine component and method of coating a turbine component

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2781617A1 (de) 2013-03-19 2014-09-24 Alstom Technology Ltd Verfahren zum Beschichten einer Komponente einer Turbomaschine und beschichtete Komponente für eine Turbomaschine
EP2781616A1 (de) 2013-03-19 2014-09-24 ALSTOM Technology Ltd Verfahren zum Beschichten einer Komponente einer Turbomaschine und beschichtete Komponente für eine Turbomaschine
US9850566B2 (en) 2013-03-19 2017-12-26 Ansaldo Energia Ip Uk Limited Method for coating a component of a turbomachine and coated component for a turbomachine
EP2857546A1 (de) * 2013-10-02 2015-04-08 Siemens Aktiengesellschaft Komponente einer Turbomaschine und Verfahren zum Beschichten einer Turbomaschinenkomponente
WO2015049086A1 (en) * 2013-10-02 2015-04-09 Siemens Aktiengesellschaft A turbo machine component and a method of coating a turbo machine component
WO2015077163A1 (en) * 2013-11-19 2015-05-28 United Technologies Corporation Article having variable composition coating
US11261742B2 (en) 2013-11-19 2022-03-01 Raytheon Technologies Corporation Article having variable composition coating
US11834963B2 (en) 2013-11-19 2023-12-05 Rtx Corporation Article having variable composition coating

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