EP1245790A1 - Turbine à gaz - Google Patents

Turbine à gaz Download PDF

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Publication number
EP1245790A1
EP1245790A1 EP01107508A EP01107508A EP1245790A1 EP 1245790 A1 EP1245790 A1 EP 1245790A1 EP 01107508 A EP01107508 A EP 01107508A EP 01107508 A EP01107508 A EP 01107508A EP 1245790 A1 EP1245790 A1 EP 1245790A1
Authority
EP
European Patent Office
Prior art keywords
sealing ring
gas turbine
ring
turbine according
groove
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Withdrawn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
EP01107508A
Other languages
German (de)
English (en)
Inventor
Peter Tiemann
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 EP01107508A priority Critical patent/EP1245790A1/fr
Publication of EP1245790A1 publication Critical patent/EP1245790A1/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Withdrawn legal-status Critical Current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
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation

Definitions

  • the invention relates to a gas turbine with a ring Blades in a flared gas channel and with a gap with the free ends of the blades forming ring, in the existing axially adjacent guide parts Joints are sealed in the radial direction.
  • Gas turbines are often used with changing performance requirements operated. This inevitably leads to transient, thermal loads. To despite different heating behavior of the individual components of a gas turbine To ensure operational safety and its good efficiency, are strung together in the axial direction of the turbine Component joints required. Allow these joints the components are unhindered from each other thermally conditional changes in length, but need to prevent unwanted Gas losses must be sealed.
  • the invention is therefore based on the object for gas turbines a seal with joints of the type mentioned create, even with different heating behavior and combined axial and radial movements of adjacent to each other Guide parts can be used reliably.
  • the arrangement according to the invention ensures a reliable Sealing the joints between adjacent guide parts, even if this is due to different heating behavior at different times independently of one another Axialund / or Carry out radial movements.
  • This slides to balance axially parallel displacements of the neighboring parts against each other an axially parallel leg of the sealing ring in an axially parallel groove and when displaced transversely to the turbine axis the other leg in a right angle to Turbine axis extending groove.
  • the turbine following movements of adjacent components to each other both legs of the sealing ring slide in simultaneously the leading grooves.
  • the arrangement according to the invention is therefore also advantageous because a sealing ring required for their application without great effort in any dimensions and from the most varied Materials can be produced.
  • Way disks 2 for multiple rotor blades fixed with blades 3.
  • the blades 3 are provided on their foot 5 with ribs and grooves with which them in a known manner in the disk 2 assigned to them are wedged.
  • the disks 2 and the blades 3 are along channels, not shown, by compressed fresh air cooled, the blade 3 in the direction of flow give hot propellant to this.
  • the rotor blade ring shown with the rotor blades 3 is in the axial direction on both sides of a wreath Guide vanes 4 flanked.
  • the guide vanes 4 are with their radially inner ends in rings 6 and with their radial outer ends clamped in guide parts 7. Joints between one of the rings 6 on the one hand and a disc 2 on the other are due to rubbing lips of sealing rings 12 locked like a labyrinth.
  • the guide parts 7 are over other components not shown in one also not Turbine housing shown secured against rotation anchored.
  • the blade ring with the blades 3 is on his Outside circumference of a ring 8 includes the free ends the blades 3 forms a blade tip gap 9.
  • the joints 10 are formed by L-shaped sealing rings in cross section 11 closed.
  • the sealing rings 11 are for example made from a metallic angle profile by rolling.
  • the legs of the sealing rings 11 are approximately the same length and are at the edges of their free end by a bevel or a Radius defused.
  • the sealing rings 11 lie with play one of its legs in a groove in one of the guide parts 7 and with the other leg in a groove of the ring 8th
  • the disks 2 and the rings 6 form an inner boundary and the guide parts 7 and the ring 8 have an outer boundary a gas channel in which a stream of compressed and heated gas drives the blades 3.
  • the gas channel is circular in cross-section, its cross-section due to the conical shape of the inner and in particular the external limit increases in the direction of the gas flow.
  • FIG. 1 and 2 show an embodiment in which the apex the L-shaped sealing rings 11 facing the gas channel are.
  • the gas channel faces in each case Flanks of the groove longer than the other flanks.
  • the Axially parallel grooves are located in this version arranged in the upstream of the associated joint 10 Component (guide part 7 or ring 8) and the right-angled, that is, radial to the axis 1 grooves lie in the component located downstream of the associated joint 10 (ring 8 or guide part 7). Shield the elongated flanks of the groove largely the sealing ring 11 from the hot gas and extensively support the webs of the sealing ring 11 as long as the Pressure in the gas channel at the respective joint 10 is less than on the other side of the sealing ring 11.
  • Fig. 3 shows an embodiment in which the apex of the Cross-section L-shaped sealing rings 11 facing away from the gas channel are. It is advantageous here to be radial to the turbine axis lying leg of each of the sealing rings 11 upstream, that is lying conically downwards, and the axially parallel leg to be arranged downstream, i.e. conically upwards. expedient are not directly the gas channel in this version limiting flanks of the grooves extended and support the Leg of the sealing ring 11 with a larger area than the flanks of the grooves lying directly on the gas channel.
  • both in the embodiment according to FIG. 2 and in the embodiment 3 are sufficient for accommodation large, in particular sufficiently deep grooves to accommodate the Leg of the sealing rings 11 material thickening on the involved Guide parts 7 and the ring 8 provided and effect additionally a stiffening of this in a manner not shown and way against rotation directly or via other components on Turbine housing secured components.
  • the embodiment according to FIG. 2 is preferred used because the result is a particularly elegant Execution of the components involved.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP01107508A 2001-03-26 2001-03-26 Turbine à gaz Withdrawn EP1245790A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP01107508A EP1245790A1 (fr) 2001-03-26 2001-03-26 Turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP01107508A EP1245790A1 (fr) 2001-03-26 2001-03-26 Turbine à gaz

Publications (1)

Publication Number Publication Date
EP1245790A1 true EP1245790A1 (fr) 2002-10-02

Family

ID=8176940

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01107508A Withdrawn EP1245790A1 (fr) 2001-03-26 2001-03-26 Turbine à gaz

Country Status (1)

Country Link
EP (1) EP1245790A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1645726A1 (fr) 2004-10-11 2006-04-12 Rolls-Royce Plc Dispositif d'étanchéité
WO2014146954A1 (fr) * 2013-03-21 2014-09-25 Siemens Aktiengesellschaft Élément d'étanchéité servant à rendre étanche un interstice
DE102019113530A1 (de) * 2019-05-21 2020-11-26 Rolls-Royce Deutschland Ltd & Co Kg Vorrichtung zur Abdichtung eines Spalts zwischen zwei Bauteilen einer Turbine eines Gasturbinentriebwerks

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3728041A (en) * 1971-10-04 1973-04-17 Gen Electric Fluidic seal for segmented nozzle diaphragm
DE2603867A1 (de) * 1975-12-19 1977-06-23 Bbc Brown Boveri & Cie Dichtring
FR2422037A1 (fr) * 1977-12-13 1979-11-02 Alsthom Atlantique Turbine a gaz
US4177004A (en) 1977-10-31 1979-12-04 General Electric Company Combined turbine shroud and vane support structure
US4184689A (en) * 1978-10-02 1980-01-22 United Technologies Corporation Seal structure for an axial flow rotary machine
US4251986A (en) * 1978-12-05 1981-02-24 General Electric Company Seal vibration-reducing apparatus
US4291905A (en) * 1978-12-22 1981-09-29 The Boeing Company Duct seal
US4330234A (en) * 1979-02-20 1982-05-18 Rolls-Royce Limited Rotor tip clearance control apparatus for a gas turbine engine
GB2102897A (en) * 1981-07-27 1983-02-09 Gen Electric Annular seals

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3728041A (en) * 1971-10-04 1973-04-17 Gen Electric Fluidic seal for segmented nozzle diaphragm
DE2603867A1 (de) * 1975-12-19 1977-06-23 Bbc Brown Boveri & Cie Dichtring
US4177004A (en) 1977-10-31 1979-12-04 General Electric Company Combined turbine shroud and vane support structure
FR2422037A1 (fr) * 1977-12-13 1979-11-02 Alsthom Atlantique Turbine a gaz
US4184689A (en) * 1978-10-02 1980-01-22 United Technologies Corporation Seal structure for an axial flow rotary machine
US4251986A (en) * 1978-12-05 1981-02-24 General Electric Company Seal vibration-reducing apparatus
US4291905A (en) * 1978-12-22 1981-09-29 The Boeing Company Duct seal
US4330234A (en) * 1979-02-20 1982-05-18 Rolls-Royce Limited Rotor tip clearance control apparatus for a gas turbine engine
GB2102897A (en) * 1981-07-27 1983-02-09 Gen Electric Annular seals

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1645726A1 (fr) 2004-10-11 2006-04-12 Rolls-Royce Plc Dispositif d'étanchéité
GB2418966A (en) * 2004-10-11 2006-04-12 Rolls Royce Plc A sealing arrangement for sealing between annular components in a gas turbine engine
GB2418966B (en) * 2004-10-11 2006-11-15 Rolls Royce Plc A sealing arrangement
US7347662B2 (en) 2004-10-11 2008-03-25 Rolls-Royce Plc Sealing arrangement
WO2014146954A1 (fr) * 2013-03-21 2014-09-25 Siemens Aktiengesellschaft Élément d'étanchéité servant à rendre étanche un interstice
DE102019113530A1 (de) * 2019-05-21 2020-11-26 Rolls-Royce Deutschland Ltd & Co Kg Vorrichtung zur Abdichtung eines Spalts zwischen zwei Bauteilen einer Turbine eines Gasturbinentriebwerks
WO2020234007A1 (fr) * 2019-05-21 2020-11-26 Rolls-Royce Deutschland Ltd & Co Kg Dispositif d'etancheification d'un interstice entre deux composants d'une turbine d'un moteur à turbine à gaz

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