EP2372093A1 - Forme du joint d'étanchéité sur la plateforme d'une aube de turbine - Google Patents

Forme du joint d'étanchéité sur la plateforme d'une aube de turbine Download PDF

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Publication number
EP2372093A1
EP2372093A1 EP11159847A EP11159847A EP2372093A1 EP 2372093 A1 EP2372093 A1 EP 2372093A1 EP 11159847 A EP11159847 A EP 11159847A EP 11159847 A EP11159847 A EP 11159847A EP 2372093 A1 EP2372093 A1 EP 2372093A1
Authority
EP
European Patent Office
Prior art keywords
distance
shroud
side edge
longitudinal axis
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.)
Granted
Application number
EP11159847A
Other languages
German (de)
English (en)
Other versions
EP2372093B1 (fr
Inventor
Andre Saxer
Igor Tsypkaykin
Ulrich Rathmann
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP2372093A1 publication Critical patent/EP2372093A1/fr
Application granted granted Critical
Publication of EP2372093B1 publication Critical patent/EP2372093B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/22—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
    • 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
    • F01D11/125—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 with a reinforcing structure
    • 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
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape

Definitions

  • the invention relates to a device on a shroud provided on a turbine blade tip, with a radially to the axis of rotation about which the turbine blade is rotatably disposed, the shroud locally superior, ridge-like trained sealing structure having an oriented in the direction of rotation of the turbine blade longitudinal extent, itself has tapered with increasing radial distance to the shroud and one of the turbine blade radially facing away, flat-shaped end face.
  • Turbine blades are mostly provided with a shroud at their turbine blade tips which provides a vibration reducing effect on the respective turbine blade and thus contributes to extending the life of the turbine blade.
  • at least one of the end-side shroud surface in the radial direction to the rotation axis frontally superior, rib-like sealing structure is provided, which extends in the direction of rotation to the rotational movement of the turbine blades along the shroud.
  • Such sealing structures serve primarily to reduce leakage flow that forms along the flow channel between the turbine blade tips and the stationary turbine housing and that does not contribute to the power gain of the turbine.
  • the foregoing sealing structures are based on abrasive materials and, by rotating the turbine blades and due to their radial superiority to the shrouds, into a turbine wall blade tip radially opposed abradable wall structure on the turbine housing, which is typically formed in a honeycomb structure, forming a circumferential direction extending, groove-shaped recess to be ground in such a way that although the end-side shroud surface includes a minimal gap with the wall structure, however, the rib-like sealing element protrudes almost accurately into the self-machined by the sealing element groove-shaped recess. In axial projection thus concludes each blade tip with its, engaging in the groove-shaped recess sealing structure for a flowing axially through the turbine gaseous working fluid largely gas-tight.
  • a cross-sectional shape axially that is, provided transversely to the circumferential direction, locally magnifying cutting structure, which has on both axially opposite flanks of the sealing structure in the direction of rotation facing cutting surfaces.
  • the axially projecting from the sealing structure cutting surfaces assets within the usually designed as a honeycomb structure abreibbaren turbine housing wall in comparison to the rest of the axial sealing structure width founded on the axial sealing structure width, so that the sealing structure can not fit over its entire length to the groove-shaped recess fit and thus by the resulting intermediate gap between the sealing structure and groove-shaped recess can form a metered adjustable leakage current.
  • the rib-like sealing structure provided on the shroud in the radial direction along the turbine blade usually does not coincide with the radial center of gravity of the turbine blade, whereby additional load moments occur, especially at high speeds and high process temperatures, in the connection area between the shroud and the turbine blade increased creep rates and ultimately lead to material failure.
  • FIG. 6 of the cited document shows a radial plan view of the rib-like sealing structure relative to the shroud, which has a V-shaped taper with increasing radial distance from the shroud in cross-section and which has a respective raised cutting surface on the mutually facing side flanks , which occupy different staggered positions in the longitudinal extension of the rib-shaped structure.
  • the invention has for its object to reduce the problem described above in the creation of larger-sized turbine blades and to optimize the area of the shroud with a sealing structure provided thereon, both in terms of their capacity and in terms of mass reduction.
  • it is necessary to look for measures by which reduces the operational stresses and strains occurring in the turbine blade tip area and thus ultimately the turbine blade life can be significantly increased.
  • S 45 mm to 200 mm a ⁇ 1 ⁇ a ⁇ 2 and 1 / 16 S ⁇ a ⁇ 1 .
  • the axial width of the sealing structure in the circumferential direction before the above central broadening measures only 1/62 S ⁇ f3
  • the improved cutting effect results from the cutting edges e1 and e2 facing in the direction of rotation, which have transition regions between the narrow rib area in the fifth surface section with a web width f3 and the axially significantly wider third surface section serve axial rib width f2.
  • the coating process is preferably carried out by means of a galvanic deposition, a plasma deposition, a spray deposition or by means of a welding or soldering operation.
  • FIG. 2 is a perspective view of the shroud D of a not further illustrated turbine blade shown for qualitative illustration of the solution formed sealing structure.
  • the sealing structure DS according to the invention is preferably connected in one piece with the shroud D and rises above the shroud D with side edges 1 'to 10' corresponding to the side edges 1 to 10 bordering the end face St.
  • the cutting edge surfaces e1 'and e2' associated with the cutting edges e1 and e2 are provided with the surface hardening layer (11) for improving the cutting action.
  • the cut surface 10 ' may also be provided with a corresponding surface hard layer (11). In a particularly advantageous manner, however, all side edge surface with a corresponding Coating, so in particular the end face St, be provided with the surface-hard layer.
  • a longitudinal extent S which corresponds to the oriented in the direction of rotation U shroud length.
  • a plurality of sealing structures DS formed in accordance with the invention can be arranged on the surface of a shroud D, so that they are preferably arranged next to one another in the circumferential direction.
  • the location corresponds to the in FIG. 1 Illustrated longitudinal axis L through the end face St of the solution formed according to rib-like sealing structure at the same time also the radial center of gravity plane of the turbine blade.
  • FIG. 3 is a cross-sectional view taken along in FIG FIG. 2 indicated section plane A shown.
  • the side edges 6 'and 7' each with the orthogonal to the shroud surface include an angle ⁇ , ⁇ , which may typically be in the range between 0.1 ° and 45 °. The same angle of inclination also applies to the side flanks 8 'and 9'.
  • FIG. 4 is a cross-sectional view represented by a cutting contour.
  • a cutting contour it is necessary to provide the entire surface of the cutting contour with a hard surface layer 11. At the very least, it is necessary to coat those surface area of the cutting contour with the surface-hardened layer 11 which comes into engagement with the abradable material on the turbine housing wall.
  • an effective layer thickness Z of 0.1 mm to 4.5 mm on the cutting surface, which has at least one penetration depth P1, with which the cutting contour in the abradable material is able to penetrate.
  • the cutting depth P1 is about 0.5 mm to 15 mm.
  • the layer is thinned over a further region P2 which extends between P1 + 0.5 mm to 15 mm.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP11159847.0A 2010-03-31 2011-03-25 Forme du joint d'étanchéité sur la plateforme d'une aube de turbine Active EP2372093B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH00476/10A CH702980A1 (de) 2010-03-31 2010-03-31 Dichtstruktur an einem Deckband einer Turbinenlaufschaufel.

Publications (2)

Publication Number Publication Date
EP2372093A1 true EP2372093A1 (fr) 2011-10-05
EP2372093B1 EP2372093B1 (fr) 2013-12-11

Family

ID=42335021

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11159847.0A Active EP2372093B1 (fr) 2010-03-31 2011-03-25 Forme du joint d'étanchéité sur la plateforme d'une aube de turbine

Country Status (3)

Country Link
US (1) US9441489B2 (fr)
EP (1) EP2372093B1 (fr)
CH (1) CH702980A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2604797A1 (fr) * 2011-12-13 2013-06-19 MTU Aero Engines GmbH Aube de rotor dotée d'un agencement de nervures ayant un revêtement abrasif
DE102012220326A1 (de) * 2012-11-08 2014-05-22 Bosch Mahle Turbo Systems Gmbh & Co. Kg Strömungsmaschine
FR3077093A1 (fr) * 2018-01-19 2019-07-26 Safran Aircraft Engines Aube equilibree d'une roue mobile d'une turbomachine
JP2021110291A (ja) * 2020-01-10 2021-08-02 三菱重工業株式会社 動翼、及び軸流回転機械

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2564727A1 (fr) * 2011-08-27 2013-03-06 Braun GmbH Dispositif de rognage de filament doté d'un bord tranchant résistant à l'abrasion et procédé de rognage de filaments
US9598973B2 (en) 2012-11-28 2017-03-21 General Electric Company Seal systems for use in turbomachines and methods of fabricating the same
US9903210B2 (en) * 2013-05-21 2018-02-27 Siemens Energy, Inc. Turbine blade tip shroud
US9464530B2 (en) * 2014-02-20 2016-10-11 General Electric Company Turbine bucket and method for balancing a tip shroud of a turbine bucket
DE102016211337A1 (de) * 2016-06-24 2017-12-28 MTU Aero Engines AG Verdickter radial äußerer Ringbereich eines Dichtfins
US20180230819A1 (en) * 2017-02-14 2018-08-16 General Electric Company Turbine blade having tip shroud rail features
US10294801B2 (en) * 2017-07-25 2019-05-21 United Technologies Corporation Rotor blade having anti-wear surface

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19904229A1 (de) * 1999-02-03 2000-08-10 Asea Brown Boveri Gekühlte Turbinenschaufel
US20040208743A1 (en) * 2003-04-18 2004-10-21 Urban John Paul Center-located cutter teeth on shrouded turbine blades
EP1507064A2 (fr) * 2003-08-13 2005-02-16 General Electric Company Epaisseur du flanc de raccordement avec la plateforme d'extrémité dans les aubes rotoriques d'une turbine
EP1507066A2 (fr) 2003-08-12 2005-02-16 General Electric Company Dépouille centrale pour aubes de turbine avec bande de couverture intégrée
US20050129519A1 (en) * 2003-12-12 2005-06-16 General Elecric Company Center located cutter teeth on shrouded turbine blades
US20050191182A1 (en) * 2004-02-26 2005-09-01 Richard Seleski Turbine blade shroud cutter tip
DE102008023424A1 (de) * 2007-05-24 2008-11-27 General Electric Company Verfahren für die mittige Anordnung von Zähnen auf Turbinenschaufeln mit Deckband
DE102008044419A1 (de) * 2007-08-22 2009-02-26 General Electric Co. Kantenprofil eines Deckbands für eine Turbinenlaufschaufel
DE102008037521A1 (de) * 2007-11-08 2009-05-14 General Electric Co. Z-Nutgestalt für eine Turbinenschaufel
US20090263248A1 (en) * 2008-04-22 2009-10-22 General Electric Company Shape for a turbine bucket tip shroud

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2256434A (en) * 1991-06-04 1992-12-09 Rolls Royce Plc Abrasive medium
US7066713B2 (en) * 2004-01-31 2006-06-27 United Technologies Corporation Rotor blade for a rotary machine

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19904229A1 (de) * 1999-02-03 2000-08-10 Asea Brown Boveri Gekühlte Turbinenschaufel
US20040208743A1 (en) * 2003-04-18 2004-10-21 Urban John Paul Center-located cutter teeth on shrouded turbine blades
EP1507066A2 (fr) 2003-08-12 2005-02-16 General Electric Company Dépouille centrale pour aubes de turbine avec bande de couverture intégrée
EP1507064A2 (fr) * 2003-08-13 2005-02-16 General Electric Company Epaisseur du flanc de raccordement avec la plateforme d'extrémité dans les aubes rotoriques d'une turbine
US20050129519A1 (en) * 2003-12-12 2005-06-16 General Elecric Company Center located cutter teeth on shrouded turbine blades
US20050191182A1 (en) * 2004-02-26 2005-09-01 Richard Seleski Turbine blade shroud cutter tip
DE102008023424A1 (de) * 2007-05-24 2008-11-27 General Electric Company Verfahren für die mittige Anordnung von Zähnen auf Turbinenschaufeln mit Deckband
DE102008044419A1 (de) * 2007-08-22 2009-02-26 General Electric Co. Kantenprofil eines Deckbands für eine Turbinenlaufschaufel
DE102008037521A1 (de) * 2007-11-08 2009-05-14 General Electric Co. Z-Nutgestalt für eine Turbinenschaufel
US20090263248A1 (en) * 2008-04-22 2009-10-22 General Electric Company Shape for a turbine bucket tip shroud

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2604797A1 (fr) * 2011-12-13 2013-06-19 MTU Aero Engines GmbH Aube de rotor dotée d'un agencement de nervures ayant un revêtement abrasif
US9797264B2 (en) 2011-12-13 2017-10-24 Mtu Aero Engines Gmbh Rotating blade having a rib arrangement with a coating
DE102012220326A1 (de) * 2012-11-08 2014-05-22 Bosch Mahle Turbo Systems Gmbh & Co. Kg Strömungsmaschine
FR3077093A1 (fr) * 2018-01-19 2019-07-26 Safran Aircraft Engines Aube equilibree d'une roue mobile d'une turbomachine
JP2021110291A (ja) * 2020-01-10 2021-08-02 三菱重工業株式会社 動翼、及び軸流回転機械

Also Published As

Publication number Publication date
CH702980A1 (de) 2011-10-14
US20110243714A1 (en) 2011-10-06
EP2372093B1 (fr) 2013-12-11
US9441489B2 (en) 2016-09-13

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