EP2410133A1 - Turbine à gaz et procédé d'étanchéification de courants de fuites - Google Patents

Turbine à gaz et procédé d'étanchéification de courants de fuites Download PDF

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Publication number
EP2410133A1
EP2410133A1 EP10170462A EP10170462A EP2410133A1 EP 2410133 A1 EP2410133 A1 EP 2410133A1 EP 10170462 A EP10170462 A EP 10170462A EP 10170462 A EP10170462 A EP 10170462A EP 2410133 A1 EP2410133 A1 EP 2410133A1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
sealing
sealing strip
blade
blades
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Withdrawn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
EP10170462A
Other languages
German (de)
English (en)
Inventor
Gernot Lang
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 EP10170462A priority Critical patent/EP2410133A1/fr
Publication of EP2410133A1 publication Critical patent/EP2410133A1/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Withdrawn legal-status Critical Current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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D11/127—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 a deformable or crushable structure, e.g. honeycomb
    • 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
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/612—Foam

Definitions

  • the invention relates to a gas turbine according to the preamble of claim 1, and to a method for sealing leakage currents according to claims 6 and 7.
  • blades of gas turbines have an airfoil and a shroud formed on the blade tip with radially outwardly facing and aligned in the direction of rotation cutting on. Between shroud and one, the flow channel forming the housing inner wall of the turbine housing, a radial gap is formed.
  • a honeycomb-shaped sealing band is usually fastened to the housing inner wall. This must fill the radial gap so far that the cutting edges of the shrouds at least partially engage in this sealing strip.
  • the rotating blades dig into the sealing band, forming grooves that create a quasi labyrinth-like seal of these blades and the sealing band.
  • Corresponding measures can also be provided laterally on the blade blade for sealing the gap between blades and vanes.
  • the object of the invention is therefore to provide a gas turbine and a method for sealing such leakage currents, which overcome the disadvantages described above.
  • the open-pored metal structure could consist of a material based on nickel or a nickel-cobalt alloy, for example. Both materials are characterized by high oxidation and corrosion resistance even at high temperatures, and are therefore ideally suited for use in gas turbines.
  • the thermal and mechanical properties of these materials can be easily adapted to the requirements as a sealing tape for sealing leakage currents.
  • these sealing tapes according to the invention of such open-pore metal structures in contrast to the known honeycomb-like sealing tapes, easier to manufacture and less prone to mechanical deformation and thus less maintenance-intensive and thus more cost-effective.
  • FIG. 1 schematically a single blade of a blade row of the gas turbine.
  • the rotor blade 10 has an airfoil 11 and a shroud 12 formed on the blade tip, with blades 13 pointing radially outwards and oriented in the direction of rotation.
  • a radial gap 21 is formed, which is filled with a fixed to the housing inner wall 20 sealing tape 30, that the cutting edges 13 of the shrouds 12 at least partially engage in the sealing strip 30.
  • the sealing strip 30 is made of an open-pore metal structure and thus form a seal for leakage currents in the radial gap 21 with the cutting edges 13, which virtually burrow into the sealing strip.
  • FIG. 2 shows a further embodiment, in addition to or independent of the in FIG. 1 illustrated embodiment may be provided in the gas turbine.
  • the blade blade 11 of the blade 11 here at its axial sides in the direction of rotation aligned cutting 13 'on.
  • These cutting edges 13 ' are formed so that they engage in corresponding, arranged on the adjacent vanes 23 sealing strips 30' so that the axial gap between the blade 10 and the guide vane 23 is sealed.
  • additional sealing plates 24 are provided on the guide vane 23, which engage over the cutting edges 13 'in the axial direction and at whose, to the cutting edges 13' directed sides, the sealing strip 30 'is provided.
  • the sealing strip 30 'shown here is made according to the invention of an open-pore metal structure and causes a hot gas infeed can be safely avoided in the Radrete Congress Congress even at low barrier airflows.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP10170462A 2010-07-22 2010-07-22 Turbine à gaz et procédé d'étanchéification de courants de fuites Withdrawn EP2410133A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP10170462A EP2410133A1 (fr) 2010-07-22 2010-07-22 Turbine à gaz et procédé d'étanchéification de courants de fuites

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10170462A EP2410133A1 (fr) 2010-07-22 2010-07-22 Turbine à gaz et procédé d'étanchéification de courants de fuites

Publications (1)

Publication Number Publication Date
EP2410133A1 true EP2410133A1 (fr) 2012-01-25

Family

ID=43242655

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10170462A Withdrawn EP2410133A1 (fr) 2010-07-22 2010-07-22 Turbine à gaz et procédé d'étanchéification de courants de fuites

Country Status (1)

Country Link
EP (1) EP2410133A1 (fr)

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3529905A (en) * 1966-12-12 1970-09-22 Gen Motors Corp Cellular metal and seal
US3547455A (en) * 1969-05-02 1970-12-15 Gen Electric Rotary seal including organic abradable material
US3719365A (en) * 1971-10-18 1973-03-06 Gen Motors Corp Seal structure
EP1146204A2 (fr) * 2000-04-12 2001-10-17 ROLLS-ROYCE plc Joint abradable
EP1152124A1 (fr) * 2000-05-04 2001-11-07 Siemens Aktiengesellschaft Garniture d'étanchéité
US20040022625A1 (en) * 2002-03-15 2004-02-05 Care Ian C. D. Cellular materials
DE10360164A1 (de) * 2003-12-20 2005-07-21 Mtu Aero Engines Gmbh Gasturbinenbauteil
EP1878876A2 (fr) * 2006-07-11 2008-01-16 Rolls-Royce plc Joint abradable pour turbine à gaz et sa méthode de production
DE102008019331A1 (de) * 2008-04-16 2009-10-22 Rolls-Royce Deutschland Ltd & Co Kg Einlaufdichtung für den Kompressor eines Gasturbinentriebwerks
EP2196632A2 (fr) * 2008-12-10 2010-06-16 Rolls-Royce plc Dispositif d'étanchéité dans une turbine à gaz et procédé de fabrication

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3529905A (en) * 1966-12-12 1970-09-22 Gen Motors Corp Cellular metal and seal
US3547455A (en) * 1969-05-02 1970-12-15 Gen Electric Rotary seal including organic abradable material
US3719365A (en) * 1971-10-18 1973-03-06 Gen Motors Corp Seal structure
EP1146204A2 (fr) * 2000-04-12 2001-10-17 ROLLS-ROYCE plc Joint abradable
EP1152124A1 (fr) * 2000-05-04 2001-11-07 Siemens Aktiengesellschaft Garniture d'étanchéité
US20040022625A1 (en) * 2002-03-15 2004-02-05 Care Ian C. D. Cellular materials
DE10360164A1 (de) * 2003-12-20 2005-07-21 Mtu Aero Engines Gmbh Gasturbinenbauteil
EP1878876A2 (fr) * 2006-07-11 2008-01-16 Rolls-Royce plc Joint abradable pour turbine à gaz et sa méthode de production
DE102008019331A1 (de) * 2008-04-16 2009-10-22 Rolls-Royce Deutschland Ltd & Co Kg Einlaufdichtung für den Kompressor eines Gasturbinentriebwerks
EP2196632A2 (fr) * 2008-12-10 2010-06-16 Rolls-Royce plc Dispositif d'étanchéité dans une turbine à gaz et procédé de fabrication

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