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GB1358798A - Sealing element for a turbo-machine - Google Patents

Sealing element for a turbo-machine

Info

Publication number
GB1358798A
GB1358798A GB2312472A GB2312472A GB1358798A GB 1358798 A GB1358798 A GB 1358798A GB 2312472 A GB2312472 A GB 2312472A GB 2312472 A GB2312472 A GB 2312472A GB 1358798 A GB1358798 A GB 1358798A
Authority
GB
United Kingdom
Prior art keywords
layers
sealing
turbine
grooves
sets
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.)
Expired
Application number
GB2312472A
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.)
Brown Boveri Sulzer Turbomaschinen AG
Original Assignee
Brown Boveri Sulzer Turbomaschinen 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 Brown Boveri Sulzer Turbomaschinen AG filed Critical Brown Boveri Sulzer Turbomaschinen AG
Publication of GB1358798A publication Critical patent/GB1358798A/en
Expired legal-status Critical Current

Links

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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1358798 Turbine sealing BROWN BOVERI-SULZER TURBOMASCHINEN A G 17 May 1972 23124/72 Heading FIT An arrangement for sealing circumferentially and axially extending intersecting gaps 8 in a turbine, e.g. those defined between blade roots 4 and intermediate segments 7 on a rotor, comprises two sets of packing strips 16, 16' inserted in grooves 12 in roots 4 and segments 7. Set 16 comprises at least two layers 17, 18 whose ends are longitudinally staggered so that at each intersection 14 one of the layers is continuous. Set 16' comprises two similarly arranged layers 19, 20 which slidably inter-engage with layers 17, 18 of set 16 by means of cut-outs 26 and lobes 27 at the intersections of the two sets. Clearance 23 is such that it approaches zero at turbine working temperature. To further improve sealing, deformable inserts 30 may be provided at the bottoms of grooves 12. The sealing arrangement is applicable also to guide vanes.
GB2312472A 1972-06-09 1972-05-17 Sealing element for a turbo-machine Expired GB1358798A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7220828A FR2188054B1 (en) 1972-06-09 1972-06-09

Publications (1)

Publication Number Publication Date
GB1358798A true GB1358798A (en) 1974-07-10

Family

ID=9099951

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2312472A Expired GB1358798A (en) 1972-06-09 1972-05-17 Sealing element for a turbo-machine

Country Status (2)

Country Link
FR (1) FR2188054B1 (en)
GB (1) GB1358798A (en)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0058532A3 (en) * 1981-02-17 1983-04-27 Mitsubishi Jukogyo Kabushiki Kaisha Axial flow turbine nozzle
US4465432A (en) * 1981-12-09 1984-08-14 S.N.E.C.M.A. System for mounting and attaching turbine and compressor prismatic rooted blades and mounting process
EP0147354A1 (en) * 1983-12-05 1985-07-03 United Technologies Corporation Intersecting feather seals and construction thereof
GB2221724A (en) * 1988-08-11 1990-02-14 Rolls Royce Plc Bladed rotor assembly and sealing wire therefor
EP0469826A3 (en) * 1990-07-30 1993-06-09 General Electric Company Seal assembly for segmented turbine engine structures
EP0874132A3 (en) * 1997-04-24 2000-03-22 United Technologies Corporation Fan blade interplatform seal
GB2387416A (en) * 2002-03-01 2003-10-15 Alstom Gap seal in a gas turbine
GB2463036A (en) * 2008-08-29 2010-03-03 Rolls Royce Plc Blade platform and insert arrangement for gas turbine
GB2467582B (en) * 2009-02-10 2011-07-06 Rolls Royce Plc Vibration damper assembly
US8105024B2 (en) 2007-09-24 2012-01-31 Alstom Technology Ltd Seal in gas turbine
AU2011340576B2 (en) * 2010-12-09 2015-09-24 General Electric Technology Gmbh Fluid flow machine especially gas turbine penetrated axially by a hot gas stream
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2799667A1 (en) * 2013-04-29 2014-11-05 Alstom Technology Ltd Sealing arrangement of a gas turbine with a cooling air system

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0058532A3 (en) * 1981-02-17 1983-04-27 Mitsubishi Jukogyo Kabushiki Kaisha Axial flow turbine nozzle
US4465432A (en) * 1981-12-09 1984-08-14 S.N.E.C.M.A. System for mounting and attaching turbine and compressor prismatic rooted blades and mounting process
EP0147354A1 (en) * 1983-12-05 1985-07-03 United Technologies Corporation Intersecting feather seals and construction thereof
GB2221724A (en) * 1988-08-11 1990-02-14 Rolls Royce Plc Bladed rotor assembly and sealing wire therefor
EP0469826A3 (en) * 1990-07-30 1993-06-09 General Electric Company Seal assembly for segmented turbine engine structures
EP0874132A3 (en) * 1997-04-24 2000-03-22 United Technologies Corporation Fan blade interplatform seal
GB2387416B (en) * 2002-03-01 2005-11-23 Alstom Gap seal in a gas turbine
US6857848B2 (en) 2002-03-01 2005-02-22 Alstom Technology Ltd Gap seal in a gas turbine
GB2387416A (en) * 2002-03-01 2003-10-15 Alstom Gap seal in a gas turbine
US8105024B2 (en) 2007-09-24 2012-01-31 Alstom Technology Ltd Seal in gas turbine
GB2463036A (en) * 2008-08-29 2010-03-03 Rolls Royce Plc Blade platform and insert arrangement for gas turbine
GB2463036B (en) * 2008-08-29 2011-04-20 Rolls Royce Plc A blade arrangement
US8333563B2 (en) 2008-08-29 2012-12-18 Rolls-Royce Plc Blade arrangement
GB2467582B (en) * 2009-02-10 2011-07-06 Rolls Royce Plc Vibration damper assembly
AU2011340576B2 (en) * 2010-12-09 2015-09-24 General Electric Technology Gmbh Fluid flow machine especially gas turbine penetrated axially by a hot gas stream
US9657641B2 (en) 2010-12-09 2017-05-23 General Electric Company Fluid flow machine especially gas turbine penetrated axially by a hot gas stream
EP2649279B1 (en) * 2010-12-09 2018-02-21 General Electric Technology GmbH Fluid flow machine especially gas turbine penetrated axially by a hot gas stream
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same

Also Published As

Publication number Publication date
FR2188054A1 (en) 1974-01-18
FR2188054B1 (en) 1976-08-06

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]