EP1715140A1 - Turbinenschaufel mit einer Deckplatte und einer auf der Deckplatte aufgebrachte Schutzschicht - Google Patents

Turbinenschaufel mit einer Deckplatte und einer auf der Deckplatte aufgebrachte Schutzschicht Download PDF

Info

Publication number
EP1715140A1
EP1715140A1 EP05008811A EP05008811A EP1715140A1 EP 1715140 A1 EP1715140 A1 EP 1715140A1 EP 05008811 A EP05008811 A EP 05008811A EP 05008811 A EP05008811 A EP 05008811A EP 1715140 A1 EP1715140 A1 EP 1715140A1
Authority
EP
European Patent Office
Prior art keywords
turbine
blade
cover plate
blades
protective layer
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Withdrawn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
EP05008811A
Other languages
German (de)
English (en)
French (fr)
Inventor
Albert Dr. Schrey
Gerhard Schwass
Armin Dr. De Lazzer
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 EP05008811A priority Critical patent/EP1715140A1/de
Priority to PCT/EP2006/050337 priority patent/WO2006111427A1/de
Priority to EP06703576A priority patent/EP1871991A1/de
Priority to CN200680013189.1A priority patent/CN101163862B/zh
Priority to US11/918,809 priority patent/US8021120B2/en
Priority to JP2008507029A priority patent/JP4874329B2/ja
Publication of EP1715140A1 publication Critical patent/EP1715140A1/de
Withdrawn legal-status Critical Current

Links

Images

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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • 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
    • F05C2201/0463—Cobalt
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • 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
    • 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
    • F05D2230/312—Layer deposition by plasma spraying
    • 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
    • F05D2230/313—Layer deposition by physical vapour 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
    • F05D2230/90—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
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/226—Carbides
    • 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
    • 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
    • F05D2300/2284—Nitrides of titanium
    • 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
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making

Definitions

  • the invention relates to a turbine blade with a cover plate formed on the blade leaf and a steam turbine provided with a number of such turbine blades.
  • the turbine blades of steam turbines are often provided with a top plate integrally formed on the airfoil.
  • the turbine blades combined in each case into rows of barrels or guide vanes are arranged on the rotor or on the housing of the steam turbine in such a way that the entirety of the cover plates of a row of blades protruding laterally beyond the airfoil forms a circumferential ring, a so-called cover band.
  • the cover plates of a blade row associated turbine blades are usually wedged or jammed during installation in such a way that can be dispensed with further fasteners or connecting elements between the individual cover plates.
  • the coupling of the turbine blades in the annular shroud effectively suppresses vibrations or distortions of individual turbine blades occurring as a result of high dynamic stress.
  • Each of a cover band combined cover plates of a blade row are designed to minimize the secondary flow over the blade tips or the shroud over time caused gap and edge losses.
  • the smallest possible gap width between the shroud and the opposite housing or rotor is sought, especially in full load operation of the steam turbine.
  • scratching during operation should be avoided as much as possible.
  • z. B. when starting or during load changes, but there is a risk comparatively large, caused by different thermal expansion relative changes in length of the involved components, so that in exceptional cases, however, must be expected to tarnish.
  • sealing tapes used.
  • the rotating and stationary parts approach each other closer than planned, the comparatively thin sealing bands first come into contact with the opposing component, with the surfaces of the two contact partners grinding each other in a usually localized wear region.
  • the invention is therefore based on the object to provide a turbine blade of the type mentioned above, which is designed with a high efficiency for a particularly reliable and safe operation. Furthermore, a steam turbine equipped with such turbine blades should be specified.
  • the object is achieved according to the invention by applying to the surface of the cover plate facing away from the blade of the turbine blade a protective layer of an alternative material.
  • the invention is based on the consideration that a steam turbine to achieve a high efficiency for operation with so-called "high steam parameters" should be designed.
  • a loading of the turbine blades should be done with the highest possible temperature steam.
  • steam temperatures of over 500 ° C up to about 700 ° C are desired.
  • the turbine blades, but also the flow channel for the steam forming housing components should be made of high temperature resistant material.
  • the material for producing the respective blade body should meet the highest requirements for mechanical stability and crack resistance at the high operating temperatures designed for this purpose.
  • the material should also be relatively easy to process at the same time (eg by casting). Furthermore, in order to avoid flow losses, the respective radial gap between the shroud connecting the blade tips of a blade row and the turbine components (ie the turbine housing in the case of a blade shroud or the rotor in the case of a guide shroud cover) should have the smallest possible width.
  • the invention is further based on the consideration that the quality of such emergency running properties is determined by the friction behavior between the respective contact surfaces.
  • the quality of such emergency running properties is determined by the friction behavior between the respective contact surfaces.
  • the blade body of the turbine blade comprising the airfoil blade and the cover plate, which is particularly heavily loaded, is advantageously made of a one-component workpiece.
  • heat-resistant material for the cover plate or the entire blade body for example, steel, in particular steel with 10% to 13% chromium content, could be used.
  • a particularly heat and corrosion resistant material which is suitable for steam temperatures of up to 700 ° C is preferably used as a base material for the blade body, a nickel-based alloy or a cobalt-based alloy.
  • the protective layer applied to the surface of the respective cover plate is formed by a so-called cobalt-based armor alloy.
  • the composition of the alloy is specifically oriented to a high heat resistance and wear resistance and the provision of an advantageous friction behavior in interaction with the respective (potential) friction partner, ie in particular a metallic sealing strip opposite the respective shroud. It is regarded as advantageous in this case if the two contact surfaces in the case of brushing with the removal of relatively small metallic dust particles abrade each other, without resulting in the material transfer or the outbreak of larger portions.
  • the microscopically fine grinding dust is simply entrained with the steam flowing through the turbine and transported away from the flow channel.
  • the composition of the protective layer forming armor alloy must be matched to the material of the opposing sealing bands.
  • Co cobalt
  • Ni nickel
  • Fe iron
  • Cr chromium
  • Mn manganese
  • carbon C
  • Si Silicon
  • W tungsten
  • Such armor alloys are also known under the registered trademark of the Deloro Stellite Company "Stellite". Particularly preferred in the context of the new concept is the use of the material class "Stellite No. 6".
  • the hard alloy used for arming the shroud is applied to the shroud surface by a cladding process applied and thus materially connected to the base material.
  • the coating material by applying weld beads in one or more layers with z. B. a gas, arc or inert gas welding applied to the workpiece surface.
  • the so-called plasma powder build-up welding or laser beam buildup welding can be used.
  • the applied surfacing alloys are added as wire, rod, powder or paste depending on the chosen method. Due to their generally smooth and flat surface, the cover plates or shrouds of turbine blades can be coated particularly well in this way.
  • the protective layer thus produced has a significant thickness of preferably about 1 mm or more.
  • a comparatively long life of the protective layer is ensured, which in principle survives the complete removal of the opposite sealing tape, without the base material of the cover plates is damaged.
  • a hard material layer is provided as a protective layer on the surface of the cover plate facing away from the airfoil.
  • materials which are natural for the person skilled in the art and which do not have to be subjected to heat after-treatment for hardening are referred to as natural-hard materials.
  • the use of such hard materials has the advantage that the wear of a protective layer produced therefrom is comparatively low even after prolonged use, and that in the case of a contact instead the comparatively softer sealing strip on the cover plate opposite housing or rotor of the steam turbine is processed , So only from time to time the sealing tape must be renewed.
  • Hard materials with covalent, ionic or metallic bonding are known.
  • a prominent representative of covalently bonded hard materials and the hardest naturally occurring mineral is diamond.
  • the hard materials with ionic bond for example, alumina or chromium oxide, but also counted ceramics.
  • the coating provided for protecting the respective cover plate or cover band is preferably made of a metallic hard material.
  • a metallic hard material With regard to their friction behavior and due to their mechanical and thermal stability, the carbides and nitrides formed by the elements of the transition metals are preferred.
  • chromium carbide or titanium nitride or boron nitride is provided.
  • the plasma coatings, flame spraying or PVD (Physical Vapor Deposition) generated by preferably also on an industrial scale hard coatings are characterized by a good adhesion to the metallic substrate of the cover plate and high purity and thus by particularly well-defined and unadulterated surface properties.
  • the thickness of such hard material thin layers is usually in the micron range.
  • the protective layer could each be applied individually to the cover plates of the turbine blades before they are mounted on the rotor or on the housing of the steam turbine.
  • a hard material thin film such as by a PVD process or by plasma spraying or the like
  • Stellitieren an armor by build-up welding
  • an abrasive layer is applied to the hard material layer.
  • the metallic sealing tape can first in this abrasive, d. H. incorporate soft layer before it comes into contact with the underlying hard material layer.
  • the sealing tape is not damaged on contact with the abrasive layer, but retains its original dimensions and sealing effect.
  • the surface contour of the abrasive layer adapts to the overlying or sliding sealing tape (the abrasive layer "gives as needed"), the radial clearance between the rotating and stationary parts of the steam turbine can be kept deliberately small, resulting in a high efficiency contributes.
  • the indicated turbine blade is preferably part of a steam turbine. But it could also be used in a gas turbine.
  • a number of such turbine blades are combined to form a row of blades, wherein the cover plates of the turbine blades associated with a blade row are each shaped and arranged in relation to one another in such a way that they form a circumferential covering strip coated with a protective layer of an alternative material.
  • the coated surface of the associated blade shroud is advantageously opposite a number of circumferentially disposed on the inside of the turbine housing Sealing tapes provided.
  • such sealing strips are advantageously arranged opposite the coated surface of the guide blade cover strip on the outside of the turbine shaft.
  • such a sealing band comprises a number of ring-shaped bent or formed strips, which are made of a high heat-resistant, cold-workable steel, in particular of a martensitic or austenitic steel or a nickel-based material.
  • sealing tapes instead of in a corresponding receiving guts caulked (ie solidified with Stemm material in their seat) or directly inserted (“rolled") sealing tapes also on the shroud opposite turbine component (rotor or housing or a sub-segment thereof) molded or turned-sealing ribs provided be. If necessary, the sealing bands or sealing ribs can also be designed to run in a spiral around the circumference.
  • the advantages achieved by the invention are, in particular, that the degrees of freedom obtained by applying a protective layer to the respective cover plate are selectively exploited with regard to choice of material and surface structuring for an advantageous effect on the frictional behavior against a possibly occurring with the cover plate in contact sealing tape.
  • the radial games between the rotating and the fixed part of the steam turbine can be made smaller, since there are relatively favorable emergency running properties in contact. As a result, better efficiencies can be realized than by sufficiently large radial clearances or a generous safety distance contact is avoided under all circumstances.
  • the relevant for the stability of the annular shroud structure shroud base material is protected by the applied protective or separating layer against friction and / or corrosion-related wear. If the protective layer has sufficient hardness, abrasion phenomena can largely be relocated on one side to the sealing strip, which can be renewed from time to time in a comparatively simple manner.
  • FIG. 1 shows a steam turbine 2 with a number of rotatable blades 6 connected to the turbine shaft 4.
  • the rotor blades 6 are each arranged in a ring-shaped manner on the turbine shaft 4 and thus form a number of rotor blade rows.
  • the steam turbine 2 comprises a number of fixed vanes 8, which are also fixed in a ring shape with the formation of rows of vanes on a turbine housing 10 of the steam turbine 2.
  • the limited by the turbine shaft 4 and the turbine housing 10 flow channel 12 of the steam turbine 2 is traversed in a direction parallel to the central axis 14 main flow direction of a vaporous working medium M, the input side heated to a temperature of about 540 ° C and under a high pressure of z , B.
  • the guide vanes 8 serve to guide the flow of the working medium M between in each case two rows of rotor blades or rotor blade rings viewed in the flow direction of the working medium M.
  • a successive pair of a ring of vanes 8 or a row of vanes and a ring of blades 6 or a blade row is also referred to as a turbine stage.
  • FIG. 2 shows a detail of a cross section through the steam turbine 2 that is perpendicular to the central axis 14 and on which a number of turbine blades 16 -in this case a number of rotor blades 6 -can be seen.
  • the annularly mounted on the turbine shaft 4 blades 6 have at their head-side, ie radially outward End in each case an integrally formed on the profiled airfoil 18 and laterally projecting cover plate 20.
  • the cover plates 20 each two adjacent blades 6 touch each other.
  • the cover plates 20 are in fact clamped against one another during assembly of the rotor blades 6 on the turbine shaft 4 such that a closed annular composite, a so-called shroud 22, is formed.
  • the radial gap 24 between the circular outer circumference of the shroud 22 and the opposite inside of the turbine housing 10 on the one hand kept as small as possible in order to minimize the gap losses (by the secondary flow of the working medium M on the blade tips or on the shroud 22 away).
  • the radial gap 24 is dimensioned so broad that certain fluctuations in the radii or deviations from the circular shape, which usually occur during operation of the steam turbine 2, or which are caused by mechanical influences, do not lead to a rubbing on of the rotating shroud 22.
  • the guide vanes 8 of the steam turbine 2 can also have cover plates 20 integrally formed on the respective airfoil 18, which in their entirety form a cover strip 20 assigned to the respective guide blade row, in this case a guide blade cover strip which is analogous (but not closer here) ) is separated from the turbine shaft 4 by a radial gap 24.
  • the efficiency of the steam turbine 2 is optimized by the specification of a particularly small radial clearance, which, however, also increases the probability of grazing.
  • the turbine blades 16 of the steam turbine 2 are specifically designed to provide favorable emergency running properties. This will be explained with reference to the rotor blade 6 shown by way of example in FIG. 3 in a detailed representation. All relevant considerations can also be easily transferred to the guide vanes 8 of the steam turbine 2.
  • the turbine blade 16 schematically illustrated in FIG. 3, which is embodied as a rotor blade 6, has a cover plate 20 formed on the blade 18, the blade body comprising the blade 18 and the cover plate 20 being made of a single-component workpiece to achieve high mechanical stability and temperature resistance made of a nickel-based alloy.
  • the cover plate is provided on its side facing away from the blade 18, ie the turbine housing 10 of the steam turbine 2 side facing with a plasma spray applied by means of protective layer 28 made of chromium carbide.
  • a sealing band 30 composed of a plurality of ring segments is arranged circumferentially on the inside of the turbine housing 10.
  • the sealing strip 30 temporarily comes into contact with one of the cover plates 20 or with the cover strip 22 formed by the entirety of the cover plates 20 of a row of blades, then the base material of the respective cover plate 20 protected by the protective layer 28 from wear. Due to the comparatively high hardness of the protective layer 28 formed from a hard material (here in the exemplary embodiment of chromium carbide), the sealing strip 30 is processed in a targeted and reliable manner in the first place when touching each other, so that it does not penetrate into the actual cover plate 20 or the shroud surface can penetrate.
  • a hard material here in the exemplary embodiment of chromium carbide
  • the radial gap 24 between the double-coated shroud 22 and the sealing strip 30 opposite it is designed so small that adjusts the configuration shown in FIG 4 during operation of the steam turbine 2, in which the sealing strip 30 already in the abrasive layer 32nd but generally does not contact the underlying hard material protective layer 28.
  • the protective layer 28 made of a hard material still protects the shroud 22 in the event of larger fluctuations in the gap distance and thereby ensures acceptable emergency running properties.
  • the cover plate 20 or the cover strip 22 formed by all the cover plates 20 of the guide vane row has a gradation adapted to a grading of the opposite turbine shaft 4, so that a labyrinthine angled sub-channel 34 of the flow channel 12 is formed therebetween.
  • the sub-channel 34 is sealed by the circumferentially arranged on the turbine shaft 4 sealing strips 30, wherein in each case during the operation of the steam turbine 2 in its width fluctuating radial gap 24 remains.
  • the cover plate 20 or cover band 22 made of a highly heat-resistant material is made of an alternative material, as in the previous examples, with a protective layer 28 matched to the sealing strip material with regard to its friction and wear properties overdrawn.
  • the protective layer 28 could again be made of a hard material. In the present case, however, it is a layer of stellite applied to each of the steps constituting the steps by build-up welding, originally approximately 1.0 mm thick, but slightly reduced by post-processing.
  • a gradation could also be provided in the case of a blade cover strip, or the grading could have a contour that deviates from FIG.
  • a plurality of sealing rings or sealing strips 30 spaced apart in the axial direction of the steam turbine 2 could also be combined to form a group of sealing strips 30 which lie opposite the respective shroud 22 and thus realize a multiple sealing.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)
EP05008811A 2005-04-21 2005-04-21 Turbinenschaufel mit einer Deckplatte und einer auf der Deckplatte aufgebrachte Schutzschicht Withdrawn EP1715140A1 (de)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP05008811A EP1715140A1 (de) 2005-04-21 2005-04-21 Turbinenschaufel mit einer Deckplatte und einer auf der Deckplatte aufgebrachte Schutzschicht
PCT/EP2006/050337 WO2006111427A1 (de) 2005-04-21 2006-01-20 Turbinenschaufel mit einer deckplatte und einer auf der deckplatte aufgebrachte schutzschicht
EP06703576A EP1871991A1 (de) 2005-04-21 2006-01-20 Turbinenschaufel mit einer deckplatte und einer auf der deckplatte aufgebrachte schutzschicht
CN200680013189.1A CN101163862B (zh) 2005-04-21 2006-01-20 具有盖板及设置在该盖板上的保护层的涡轮叶片
US11/918,809 US8021120B2 (en) 2005-04-21 2006-01-20 Turbine blade with a cover plate and a protective layer applied to the cover plate
JP2008507029A JP4874329B2 (ja) 2005-04-21 2006-01-20 カバープレートとこのカバープレートに被着された保護層とを備えたタービン翼

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP05008811A EP1715140A1 (de) 2005-04-21 2005-04-21 Turbinenschaufel mit einer Deckplatte und einer auf der Deckplatte aufgebrachte Schutzschicht

Publications (1)

Publication Number Publication Date
EP1715140A1 true EP1715140A1 (de) 2006-10-25

Family

ID=34935569

Family Applications (2)

Application Number Title Priority Date Filing Date
EP05008811A Withdrawn EP1715140A1 (de) 2005-04-21 2005-04-21 Turbinenschaufel mit einer Deckplatte und einer auf der Deckplatte aufgebrachte Schutzschicht
EP06703576A Withdrawn EP1871991A1 (de) 2005-04-21 2006-01-20 Turbinenschaufel mit einer deckplatte und einer auf der deckplatte aufgebrachte schutzschicht

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP06703576A Withdrawn EP1871991A1 (de) 2005-04-21 2006-01-20 Turbinenschaufel mit einer deckplatte und einer auf der deckplatte aufgebrachte schutzschicht

Country Status (5)

Country Link
US (1) US8021120B2 (enExample)
EP (2) EP1715140A1 (enExample)
JP (1) JP4874329B2 (enExample)
CN (1) CN101163862B (enExample)
WO (1) WO2006111427A1 (enExample)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015052467A1 (en) * 2013-10-11 2015-04-16 Reaction Engines Limited Turbine blades
WO2015120994A1 (de) * 2014-02-11 2015-08-20 Siemens Aktiengesellschaft Verbesserte verschleissbeständigkeit eines hochtemperaturbauteils durch kobaltbeschichtung

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8708658B2 (en) * 2007-04-12 2014-04-29 United Technologies Corporation Local application of a protective coating on a shrouded gas turbine engine component
KR101115761B1 (ko) * 2008-12-26 2012-06-12 주식회사 포스코 표면 탈탄이 억제된 강재 및 제조방법
DE102010049398A1 (de) * 2009-11-02 2011-05-05 Alstom Technology Ltd. Verschleiss- und oxidationsbeständige Turbinenschaufel
CN101922312B (zh) * 2010-03-24 2013-11-06 北京航空航天大学 一种叶轮机械径向间隙泄漏损失的控制方法
US8579581B2 (en) * 2010-09-15 2013-11-12 General Electric Company Abradable bucket shroud
US8753093B2 (en) * 2010-10-19 2014-06-17 General Electric Company Bonded turbine bucket tip shroud and related method
EP2549063A1 (en) * 2011-07-21 2013-01-23 Siemens Aktiengesellschaft Heat shield element for a gas turbine
US20130034423A1 (en) * 2011-08-01 2013-02-07 General Electric Company System and method for passively controlling clearance in a gas turbine engine
CN104508251B (zh) * 2012-04-27 2016-08-24 通用电气公司 用于燃气涡轮发动机的护罩组件和密封件
RU2015117053A (ru) * 2012-11-06 2016-12-27 Сименс Энерджи, Инк. Венец лопатки турбины с абразивным покрытием
DE102013212252A1 (de) * 2013-06-26 2014-12-31 Siemens Aktiengesellschaft Turbine und Verfahren zur Anstreiferkennung
US20150093237A1 (en) * 2013-09-30 2015-04-02 General Electric Company Ceramic matrix composite component, turbine system and fabrication process
WO2015068227A1 (ja) * 2013-11-06 2015-05-14 川崎重工業株式会社 タービン翼およびその製造方法
US10662788B2 (en) * 2018-02-02 2020-05-26 Raytheon Technologies Corporation Wear resistant turbine blade tip
US11203942B2 (en) 2018-03-14 2021-12-21 Raytheon Technologies Corporation Wear resistant airfoil tip
US11346232B2 (en) * 2018-04-23 2022-05-31 Rolls-Royce Corporation Turbine blade with abradable tip
FR3090427B1 (fr) * 2018-12-21 2023-11-10 Safran Procede de fabrication d’un noyau
WO2022107734A1 (ja) * 2020-11-20 2022-05-27 川崎重工業株式会社 ガスタービンエンジンの回転部構成部材およびその製造方法
WO2023202900A1 (de) * 2022-04-21 2023-10-26 Siemens Energy Global GmbH & Co. KG Dichtungsanordnung

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1470032A (fr) * 1965-02-24 1967-02-17 Gen Electric Joint rotatif d'étanchéité
US20020109303A1 (en) * 2000-12-16 2002-08-15 Reinhard Fried Device for reducing the sealing gap between a rotating component and a stationary component inside a rotary turbo-engine through which a flow passes axially
EP1312760A2 (en) * 2001-11-09 2003-05-21 Mitsubishi Heavy Industries, Ltd. Turbine shroud and blade tip arrangemnet with abrasive surface and manufacturing method therefor
US20030107181A1 (en) * 2000-05-04 2003-06-12 Kai Wieghardt System for sealing off a gap
US20030183529A1 (en) * 2001-02-28 2003-10-02 Minoru Ohara Wear-resistant coating and method for applying it
EP1391537A1 (en) * 2001-05-31 2004-02-25 Mitsubishi Heavy Industries, Ltd. Coating forming method and coating forming material, and abrasive coating forming sheet

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3339933A (en) * 1965-02-24 1967-09-05 Gen Electric Rotary seal
FI45933C (fi) 1972-03-22 1976-12-03 Salakarin Oikeudenomistajat Liukumista estävä laite pyörää ja sentapaista varten.
US4291448A (en) * 1977-12-12 1981-09-29 Turbine Components Corporation Method of restoring the shrouds of turbine blades
US4285108A (en) * 1979-02-23 1981-08-25 United Technologies Corporation Apparatus and method for refinishing turbine blade airseals
US4822248A (en) * 1987-04-15 1989-04-18 Metallurgical Industries, Inc. Rebuilt shrouded turbine blade and method of rebuilding the same
JPH07109162B2 (ja) * 1988-07-07 1995-11-22 ユニオン・カーバイド・コーポレーション 回転式ラビリンスシール部材用耐摩耗性、研削性レーザ彫刻セラミック乃至金属炭化物表面
US5358379A (en) * 1993-10-27 1994-10-25 Westinghouse Electric Corporation Gas turbine vane
KR101004236B1 (ko) * 2002-10-09 2010-12-24 미츠비시덴키 가부시키가이샤 회전체 및 그 코팅방법

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1470032A (fr) * 1965-02-24 1967-02-17 Gen Electric Joint rotatif d'étanchéité
US20030107181A1 (en) * 2000-05-04 2003-06-12 Kai Wieghardt System for sealing off a gap
US20020109303A1 (en) * 2000-12-16 2002-08-15 Reinhard Fried Device for reducing the sealing gap between a rotating component and a stationary component inside a rotary turbo-engine through which a flow passes axially
US20030183529A1 (en) * 2001-02-28 2003-10-02 Minoru Ohara Wear-resistant coating and method for applying it
EP1391537A1 (en) * 2001-05-31 2004-02-25 Mitsubishi Heavy Industries, Ltd. Coating forming method and coating forming material, and abrasive coating forming sheet
EP1312760A2 (en) * 2001-11-09 2003-05-21 Mitsubishi Heavy Industries, Ltd. Turbine shroud and blade tip arrangemnet with abrasive surface and manufacturing method therefor

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015052467A1 (en) * 2013-10-11 2015-04-16 Reaction Engines Limited Turbine blades
WO2015120994A1 (de) * 2014-02-11 2015-08-20 Siemens Aktiengesellschaft Verbesserte verschleissbeständigkeit eines hochtemperaturbauteils durch kobaltbeschichtung
RU2655397C2 (ru) * 2014-02-11 2018-05-28 Сименс Акциенгезелльшафт Улучшенная износостойкость высокотемпературной конструкционной детали, придаваемая кобальтовым покрытием
US10100651B2 (en) 2014-02-11 2018-10-16 Siemens Aktiengesellschaft Wear resistance of a high-temperature component imparted by a cobalt coating

Also Published As

Publication number Publication date
US8021120B2 (en) 2011-09-20
WO2006111427A1 (de) 2006-10-26
JP4874329B2 (ja) 2012-02-15
EP1871991A1 (de) 2008-01-02
US20090022583A1 (en) 2009-01-22
CN101163862A (zh) 2008-04-16
JP2008538399A (ja) 2008-10-23
CN101163862B (zh) 2011-10-05

Similar Documents

Publication Publication Date Title
EP1715140A1 (de) Turbinenschaufel mit einer Deckplatte und einer auf der Deckplatte aufgebrachte Schutzschicht
EP0341455B1 (de) Folienzwischenlage zur Fügung von reibkorrosionsgefährdeten Maschinenbauteilen
DE69218980T2 (de) Turbinenschaufelverschleissschutzsystem mit mehrschichtiger Beilage
DE3326535C2 (enExample)
CA2754263C (en) Gas turbine blade and method of protecting same
EP1375696B1 (de) Schichtsystem für die Rotor-/Statordichtung einer Strömungsmaschine
EP2966269A1 (de) Verschleissschutzanordnung für eine strömungsmaschine, verfahren und verdichter
DE102010049398A1 (de) Verschleiss- und oxidationsbeständige Turbinenschaufel
EP2122009A1 (de) Vorrichtung zum schutz von bauteilen mit brennbarer titanlegierung vor titanfeuer und verfahren zu deren herstellung
EP2696033B1 (de) Schaufelelement einer Strömungsmachine mit duktiler Ausgleichsschicht, zugehörige Strömungsmachine, Verfahren zur Herstellung des Schaufelelements und der Strömungsmachine
WO2000037713A1 (de) Verschleissschutzschicht
DE102009049018A1 (de) Bauteil für eine Hochtemperaturdampfturbine sowie Hochtemperaturdampfturbine
EP1462617B1 (de) Schaufelanordnung für eine axiale Turbomaschine
DE602006000108T2 (de) Verfahren zur Reparatur einer Reibungsfläche einer verstellbaren Schaufel einer Turbomaschine
EP3246430B1 (de) Verfahren zur herstellung von schaufeln oder schaufelanordnungen einer strömungsmaschine mit erosionschutzschichten und entsprechend hergestelltes bauteil
WO2004007787A1 (de) Schichtsystem
EP2275220A1 (de) Verfahren zur Panzerung von Bauteilen aus einem TiAl-Basiswerkstoff, sowie entsprechende Bauteile
EP2737103A1 (de) Verfahren zum aufbringen einer verschleissschutzschicht auf eine strömungsmaschinenkomponente
DE102011000793A1 (de) Selbstschärfendes Bohrwerkzeug
DE102010048147B4 (de) Schichtsystem zur Rotor-/Statordichtung einer Strömungsmaschine und Verfahren zum Herstellen eines derartigen Schichtsystems
DE102009030398A1 (de) Verfahren zum Herstellen und/oder Reparieren einer Schaufel für eine Strömungsmaschine
DE3212214C2 (de) Kolbenring und Verfahren zu dessen Herstellung
EP2784268A1 (de) Eine Turbinenschaufelaussendichtung bestehend aus jeweils einer keramischen abrasiven Schicht auf dem Stator und dem Rotor.
DE102005038221A1 (de) Verfahren zum Aufarbeiten eines Rotors einer Reibungsbremse und ein damit aufgearbeiteter Rotor
EP3546703A1 (de) Turbinenlaufschaufel für eine gasturbine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR LV MK YU

AKX Designation fees paid
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20070426

REG Reference to a national code

Ref country code: DE

Ref legal event code: 8566