EP1820940A1 - Turbomachine ayant un revêtement des aubes de rotor avec un alliage à mémoire de forme, et utilisation d'un alliage à mémoire de forme pour une telle turbomachine. - Google Patents

Turbomachine ayant un revêtement des aubes de rotor avec un alliage à mémoire de forme, et utilisation d'un alliage à mémoire de forme pour une telle turbomachine. Download PDF

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Publication number
EP1820940A1
EP1820940A1 EP06003201A EP06003201A EP1820940A1 EP 1820940 A1 EP1820940 A1 EP 1820940A1 EP 06003201 A EP06003201 A EP 06003201A EP 06003201 A EP06003201 A EP 06003201A EP 1820940 A1 EP1820940 A1 EP 1820940A1
Authority
EP
European Patent Office
Prior art keywords
turbomachine
shape
shape memory
blades
memory alloy
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Withdrawn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
EP06003201A
Other languages
German (de)
English (en)
Inventor
Jörg Dr. Schürhoff
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP06003201A priority Critical patent/EP1820940A1/fr
Publication of EP1820940A1 publication Critical patent/EP1820940A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—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
    • F01D5/28—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
    • F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
    • F05C2201/00—Metals
    • F05C2201/04—Heavy metals
    • F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
    • F05C2201/0466—Nickel
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • 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
    • F05D2230/80—Repairing, retrofitting or upgrading methods
    • 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
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity
    • 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
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/505—Shape memory behaviour
    • 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 invention relates to a turbomachine having vanes and blades.
  • turbomachines are known, for example, as a compressor, steam turbine or gas turbine.
  • the turbomachine has a rotor rotatably mounted about a rotation axis on which the blade is anchored.
  • a stationary component is arranged such that a radial gap is created between the blade tip and the stationary component.
  • the stationary component can be configured, for example, as an inner housing.
  • the inner housing is associated with the guide vane, so that the inner housing is designed as a guide vane carrier.
  • a flow medium flows past the blade substantially along the axis of rotation, the flow medium following its predetermined path through the blade grid formed by the blades and vanes arranged one behind the other.
  • mist droplets form in the medium flow or vapor stream which are captured by the guide vanes, accumulate there and tear off from the outlet edges as drops of water. Due to their high kinetic energy, these water droplets on the rotor blades, in particular on the rotor blade leading edges, lead to surface disruption and droplet impact erosion, so that in some cases cost-intensive edge protection measures have to be taken.
  • the blades in particular the blade inlet edges as possible
  • the blades, or the blade inlet edges are also known to subject the blades, or the blade inlet edges of a surface treatment (hardening).
  • the invention has for its object to improve a turbomachine of the type mentioned with simple means to the effect that the blades are designed much more resistant to Tropfenschlagerosion.
  • the object is achieved in that at least the blades are at least partially coated with a shape memory material.
  • a shape memory material according to the invention is a material which resumes its original shape after deformation.
  • pseudoelasticity is a special form of shape memory effect.
  • imprinted shape changes in the material create a stress-induced austenite / martensite phase transformation, with back-conversion taking place upon release and the material resumes its original shape.
  • the pseudoelasticity can also be called superelasticity.
  • the shape memory material is designed as a nickel-titanium alloy, although of course other alloys such as CuZnAL or CuA1Ni can be used, which also have the shape memory effect.
  • the preferred nickel-titanium alloys have a pseudoelastically reversible elongation of about 6% to 8%, wherein the shape memory material should not be limited to this exemplified region. This effect is available in a certain temperature range, but this can be influenced by the alloy composition.
  • the operating temperatures of low-pressure blades (about 60 ° C to 100 ° C) advantageously allow the use or the use of the shape memory material as a coating for a blade or the blade inlet edge.
  • the drop impact erosion is based on surface disruption by impacting water droplets.
  • the impact energy is converted into reversible pseudoelastic deformation and can thus no longer lead to the disruption of the blade material.
  • the adhesion due to the coating material is also sufficient on titanium blades, wherein in addition the damping and the friction corrosion behavior are improved.
  • nickel-titanium layers provide excellent corrosion resistance through the formation of a dense titanium oxide layer.
  • the blade or the blade inlet edge is preferably coated with a material called Nitinol.
  • the entire blade is coated with the shape memory material, wherein it is possible to coat only the blade edges or the blade inlet edges with the shape memory material or the pseudoelastic material, preferably with nitinol.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP06003201A 2006-02-16 2006-02-16 Turbomachine ayant un revêtement des aubes de rotor avec un alliage à mémoire de forme, et utilisation d'un alliage à mémoire de forme pour une telle turbomachine. Withdrawn EP1820940A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06003201A EP1820940A1 (fr) 2006-02-16 2006-02-16 Turbomachine ayant un revêtement des aubes de rotor avec un alliage à mémoire de forme, et utilisation d'un alliage à mémoire de forme pour une telle turbomachine.

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06003201A EP1820940A1 (fr) 2006-02-16 2006-02-16 Turbomachine ayant un revêtement des aubes de rotor avec un alliage à mémoire de forme, et utilisation d'un alliage à mémoire de forme pour une telle turbomachine.

Publications (1)

Publication Number Publication Date
EP1820940A1 true EP1820940A1 (fr) 2007-08-22

Family

ID=36716952

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06003201A Withdrawn EP1820940A1 (fr) 2006-02-16 2006-02-16 Turbomachine ayant un revêtement des aubes de rotor avec un alliage à mémoire de forme, et utilisation d'un alliage à mémoire de forme pour une telle turbomachine.

Country Status (1)

Country Link
EP (1) EP1820940A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2226469A1 (fr) * 2009-03-04 2010-09-08 Siemens Aktiengesellschaft Composants de turbine dotés d'une couche de protection
WO2011036045A1 (fr) * 2009-09-25 2011-03-31 Siemens Aktiengesellschaft Aube pour une utilisation dans des flux diphasiques et procédé de production d'une telle aube
EP2304184A2 (fr) * 2008-07-18 2011-04-06 MTU Aero Engines AG Turbine à gaz et procédé de modification de la forme aérodynamique d'une aube de turbine à gaz

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2112261A1 (de) * 1971-03-13 1972-09-14 Battelle Institut E V Kuehlerventilator
DE19909899A1 (de) * 1999-03-06 2000-09-07 Abb Research Ltd Schaufeln mit veränderbarer Profilgeometrie
EP1577422A1 (fr) * 2004-03-16 2005-09-21 General Electric Company Structures de protection résistantes à l'érosion et à l'abrasion pour composants de moteur à turbine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2112261A1 (de) * 1971-03-13 1972-09-14 Battelle Institut E V Kuehlerventilator
DE19909899A1 (de) * 1999-03-06 2000-09-07 Abb Research Ltd Schaufeln mit veränderbarer Profilgeometrie
EP1577422A1 (fr) * 2004-03-16 2005-09-21 General Electric Company Structures de protection résistantes à l'érosion et à l'abrasion pour composants de moteur à turbine

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2304184A2 (fr) * 2008-07-18 2011-04-06 MTU Aero Engines AG Turbine à gaz et procédé de modification de la forme aérodynamique d'une aube de turbine à gaz
EP2226469A1 (fr) * 2009-03-04 2010-09-08 Siemens Aktiengesellschaft Composants de turbine dotés d'une couche de protection
WO2011036045A1 (fr) * 2009-09-25 2011-03-31 Siemens Aktiengesellschaft Aube pour une utilisation dans des flux diphasiques et procédé de production d'une telle aube

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