EP2226469A1 - Composants de turbine dotés d'une couche de protection - Google Patents

Composants de turbine dotés d'une couche de protection Download PDF

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Publication number
EP2226469A1
EP2226469A1 EP09003103A EP09003103A EP2226469A1 EP 2226469 A1 EP2226469 A1 EP 2226469A1 EP 09003103 A EP09003103 A EP 09003103A EP 09003103 A EP09003103 A EP 09003103A EP 2226469 A1 EP2226469 A1 EP 2226469A1
Authority
EP
European Patent Office
Prior art keywords
pseudoplastic
turbine component
temperature
deformation
phase
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Withdrawn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
EP09003103A
Other languages
German (de)
English (en)
Inventor
Susanne Dr. Gollerthan
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
Priority to EP09003103A priority Critical patent/EP2226469A1/fr
Publication of EP2226469A1 publication Critical patent/EP2226469A1/fr
Withdrawn legal-status Critical Current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
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/006—Resulting in heat recoverable alloys with a memory effect
    • 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
    • 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
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium
    • 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 turbine component for a turbomachine.
  • turbomachine is to be understood, for example, as a compressor, a steam turbine or a gas turbine.
  • Turbomachines have a rotatably mounted about a rotational axis rotor, are anchored to the blades.
  • 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 a guide vane, so that the inner housing is designed as a guide vane carrier.
  • a flow medium flows past the blades substantially along the axis of rotation, with the flow medium following its predetermined path through the blade lattice formed by the blades and vanes disposed one behind the other.
  • mist droplets form in the 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 disruptions and drop impact erosion, so that in some cases cost-intensive edge protection measures have to be taken.
  • the invention has for its object to improve a turbomachine of the type mentioned by simple means to the effect that the blades are designed much more resistant to Tropfenschlagerosion.
  • the object is achieved in that the turbine component is formed with a layer of pseudoplastic material.
  • the invention utilizes a pseudoplastic instead of a pseudoelastic material as known in the art.
  • the pseudoplastic as well as the pseudoelastic material is also referred to as a shape memory alloy and belongs to the group of functional materials and, as such, is capable of returning to its original shape after deformation far beyond the elastic range.
  • the ability of memory of the shape memory alloys is based on a diffusionless phase transformation, which can take place in a certain temperature or voltage range. In the shape memory alloys almost no volume changes take place during the phase transformation. The reason is that the new crystal structures can be formed as a result of pure shear deformations. In addition to the memory effect, which is associated with a phase transformation, also appears another deformation mechanism in appearance, which can be described as follows.
  • martensite phase So-called unit cells are present below a characteristic temperature in a twin arrangement, which is also referred to as martensite phase.
  • This martensite phase can easily be deformed by aligning the individual twin crystals in a preferred direction.
  • pseudoplasticity If such a deformed material is heated above a limit temperature, this leads to a phase transformation of the martensite phase into an austenite. Since the similarity of macroscopic dimensions of austenite is similar to that of the twin martensite, the pseudoplastic deformed material assumes its original shape.
  • materials are therefore used as a layer on a turbine component, which show a pseudoplastic behavior.
  • the pseudoplastic behavior shows the effect described above. This means that in particular a martensitic phase exists.
  • the pseudoplastic material is selected such that the temperatures and forces encountered are such that no first order phase transition occurs, thereby providing a pseudoelastic material.
  • the pseudoplastic material is present in a martensite phase.
  • This martensite phase has a martensitic structure at a given application temperature.
  • the pseudoplastic material has unit cells in a twin arrangement.
  • This twin arrangement is mechanically deformed due to a force effect.
  • This deformation is initially a permanent deformation.
  • the force is applied, for example, by the appearance of drops.
  • a NiTi alloy is used as pseudoplastic material.
  • a NiTi alloy is a binary system and has the property that, depending on the nickel content, an alloy is either martensitic or austenitic at a given temperature.
  • Nickel-titanium alloys which are exclusively martensitic at a given temperature are used with the invention.
  • the austenite start temperature is at least 80%.
  • the binary NiTi alloy has a nickel content of about 49.8wt%. By adding hafnium, palladium or even zirconium, it is possible to shift the transformation temperature into this range even for alloys with a slightly higher nickel content ( ⁇ 51wt%).
  • the turbine component is a guide or moving blade.
  • the drop impact erosion is based on surface disruption by impacting water droplets.
  • the impact energy is converted into a pseudoplastic deformation and thus can no longer lead to the disintegration of the blade material.
  • a nickel-titanium alloy is particularly suitable for this, because in addition to the good properties of a nickel-titanium alloy on particularly good Corrosion resistance and because a nickel-titanium alloy shows a very high resistance to cracking and crack growth.
  • a further advantage of the pseudoplastic layer is that the surface disruption is greatly reduced, since the turbine component surface deforms accordingly pseudoplastic deformation upon impact of a water droplet depending on the impact angle and thereby buffers a major part of the kinetic energy by folding the grid.
  • the crack sensitivity of the pseudoplastic layer to a hard layer is hardly increased.
  • nickel-titanium alloys are particularly suitable in terms of compatibility and adhesion in titanium turbine component material.
  • FIG. 1 In the FIG. 1 is shown in a schematic way how a drop impact erosion comes about.
  • a turbine guide vane 1 is supplied with steam 2, which comprises individual mist droplets. These mist droplets accumulate on the vane surface and subsequently tear off the trailing edge 5 of the vane 1 as water droplets 6. Due to their high kinetic energy, these water drops 6 lead to the rotor blades 7, in particular to the guide blade leading edges 8, to surface distortions and drop hit erosion.
  • C TR is the absolute velocity of the water droplet 6
  • W TR is the relative velocity of the water droplet 6
  • u is the peripheral velocity of the rotor blades 7.
  • the turbine vane 1 as well as the rotor blade 7 as an embodiment of a turbine component is designed with a layer of pseudoplastic material.
  • the pseudoplastic material used is a material which is in a martensite phase. This martensitic state is up to a given application temperature, which depends on the composition of the pseudoplastic material.
  • FIG. 2 Fig. 3 is a graphic representation of the conversion processes in the pseudoplastic material. With ⁇ + and ⁇ - different martensite variants are shown.
  • the basic structure of the martensite phase can consist of twelve possible martensite variants.
  • the pseudoplastic material after cooling, consists of a high temperature austenitic phase stability field, a microstructure consisting of up to twelve randomly oriented acicular martensite variants.
  • the formation of these variants which are statistically distributed in Figure (a) and may also be referred to as twin structures, represents a self-accepting process that minimizes the internal stresses created by the lattice shear associated with the phase transition.
  • Figure (b) shows the deformation behavior of the pseudoplastic material. The structure is disturbed by the action of an external force 9.
  • the external force 9 arises, for example, due to the impact of a drop of water 6 striking the pseudoplastic layer. If the pseudoplastic material is subjected to a mechanical stress by this external force 9, then such variants begin to grow, which are oriented favorably to the externally applied stress. These variants grow at the expense of others Variants that are unfavorably oriented to the external acting tension. It finds here a reorientation of the affected grid areas, what in FIG. 2 is shown and does not designate a phase transition in the conventional sense. The deformation of the pseudoplastic material resulting from this reorientation is permanent and can be completely reversed by heating into the stability field of the high temperature phase.
  • the pseudoplastic layer formed on the turbine component has such a structure Figure 2 and is therefore in a martensite phase.
  • the unit cells of the pseudoplastic material are present in a twin arrangement, as shown in the FIG. 2 Figure (a) can be seen.
  • the pseudoplastic material is a martensitic nickel-titanium alloy whose material properties are dependent on the nickel content.
  • the deformation process of the pseudoplastic material is shown in individual steps.
  • structure 10 which is similar to the twin structure FIG. 2 Figure (a)
  • the martensitic material is present in a twin structure 11.
  • a deformation of the twin structure 11 to a deformation structure 13.
  • the outer geometry of the deformation structure 13 is maintained in the state 14, in which the mechanical load 12 is no longer present and therefore can be spoken of a mechanical discharge 15.
  • the state 14 may be converted to an austenitic structure 16 by suitable heating above a threshold temperature A s . Due to the similarity of the macroscopic dimensions of the austenitic structure 16 with those of the martensitic twin structure 11, the pseudoplastic deformed material resumes its original shape at. In contrast to the microstructure, the shape remains unchanged when temperature reduction 18 results in the phase transformation of austenite into martensite.
  • the strain is 19 on the X-axis, 20 on the Y-axis and 21 on the Z-axis.
  • the curve 22 shows how the voltage 20 behaves as a function of the strain 19 and the temperature 21. From the starting point 23, the tension 20 is increased, which leads to an expansion 19 of the material. The ratios are linear here, as can be seen from the representation in the coordinate system. If the external mechanical load 12 is no longer present, ie a mechanical discharge 15 takes place, which drops to the value 0, a residual strain 24 is present. This means that the material is plastically deformed. This plastic deformation can be reversed by a heating 17, ie a temperature increase, if the temperature reaches and exceeds the limit temperature A s . At the second limit temperature A f , the residual strain 24 has decreased to the value 0. A temperature decrease 18, ie a lowering of the temperature to the value 0, leads again to the twin structure 11, which has a martensitic structure.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP09003103A 2009-03-04 2009-03-04 Composants de turbine dotés d'une couche de protection Withdrawn EP2226469A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09003103A EP2226469A1 (fr) 2009-03-04 2009-03-04 Composants de turbine dotés d'une couche de protection

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09003103A EP2226469A1 (fr) 2009-03-04 2009-03-04 Composants de turbine dotés d'une couche de protection

Publications (1)

Publication Number Publication Date
EP2226469A1 true EP2226469A1 (fr) 2010-09-08

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EP09003103A Withdrawn EP2226469A1 (fr) 2009-03-04 2009-03-04 Composants de turbine dotés d'une couche de protection

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EP (1) EP2226469A1 (fr)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2354290A (en) * 1999-09-18 2001-03-21 Rolls Royce Plc Gas turbine cooling air flow control using shaped memory metal valve
US20040051219A1 (en) * 2002-09-13 2004-03-18 Yang Sherwin Method for vibration damping using superelastic alloys
EP1557552A1 (fr) * 2004-01-20 2005-07-27 General Electric Company Moteur à turbine à gaz et procédé d'assemblage et d'exploitation d'un tel moteur à turbine à gaz
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
EP1686243A2 (fr) * 2005-01-26 2006-08-02 General Electric Company Stator de turbine avec des alliages à mémoire de forme et pilotage de jeu des aubes
EP1820940A1 (fr) * 2006-02-16 2007-08-22 Siemens Aktiengesellschaft 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.

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2354290A (en) * 1999-09-18 2001-03-21 Rolls Royce Plc Gas turbine cooling air flow control using shaped memory metal valve
US20040051219A1 (en) * 2002-09-13 2004-03-18 Yang Sherwin Method for vibration damping using superelastic alloys
EP1557552A1 (fr) * 2004-01-20 2005-07-27 General Electric Company Moteur à turbine à gaz et procédé d'assemblage et d'exploitation d'un tel moteur à turbine à gaz
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
EP1686243A2 (fr) * 2005-01-26 2006-08-02 General Electric Company Stator de turbine avec des alliages à mémoire de forme et pilotage de jeu des aubes
EP1820940A1 (fr) * 2006-02-16 2007-08-22 Siemens Aktiengesellschaft 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.

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