EP1852573A2 - Système de joint d'étanchéité pour turbine à gaz - Google Patents

Système de joint d'étanchéité pour turbine à gaz Download PDF

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Publication number
EP1852573A2
EP1852573A2 EP07107277A EP07107277A EP1852573A2 EP 1852573 A2 EP1852573 A2 EP 1852573A2 EP 07107277 A EP07107277 A EP 07107277A EP 07107277 A EP07107277 A EP 07107277A EP 1852573 A2 EP1852573 A2 EP 1852573A2
Authority
EP
European Patent Office
Prior art keywords
seal assembly
stator member
gas turbine
moveable
turbine engine
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Withdrawn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
EP07107277A
Other languages
German (de)
English (en)
Inventor
Christopher Charles Glynn
William Lee Herron
Joseph C. Albers
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 Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP1852573A2 publication Critical patent/EP1852573A2/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Withdrawn legal-status Critical Current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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • F01D25/183—Sealing means

Definitions

  • This invention relates generally to gas turbine engines and more specifically to seal assemblies used with gas turbine engines.
  • Seal assemblies control fluid leakage in the engine by restricting fluid flow from areas of higher pressure to areas of lower pressure.
  • the seal assemblies may be positioned between an engine stationary member and a rotating member within the engine.
  • seals facilitate compensating for transient variations that may exist in gaps defined between components.
  • Fluid leakage through gas turbine engine seal assemblies may significantly increase fuel consumption and adversely affect engine efficiency. Additionally, fluid leakage may cause damage to other components and/or increase overall engine maintenance costs. Because of the location of the seal assemblies, and/or the operating environment, at least some known seal assemblies may deteriorate over time.
  • seal assemblies such as the seal assembly described in U.S. Patent No. 5,284,347 , for example, use aspirating air to control leakage.
  • the aspirating air prevents the rotating member from contacting the stationary member to facilitate accommodating transient variations in the gap defined between the rotating and stationary members with little or no deterioration of the seal over the life of the seal assembly.
  • seal assemblies may be complex to install in the engine, and the weight of such assemblies may adversely affect engine performance.
  • the operating efficiency of such seal assemblies may be contingent on the tolerances between the rotating and stationary members.
  • a method of assembling a seal assembly within a gas turbine engine includes coupling a stationary stator member to a gas turbine engine comprising a rotating member, and coupling a primary seal assembly and a secondary seal assembly to the stationary stator member, wherein the primary seal assembly includes a moveable stator member including at least one keyed slot and at least one biasing member.
  • the biasing member includes at least one key that is slidably coupled within the at least one keyed slot to facilitate aligning the primary seal assembly and the secondary seal assembly with respect to the gas turbine engine.
  • the seal assembly facilitates sealing between the stationary stator member and the rotating member.
  • a seal assembly for a gas turbine engine including a stationary stator member and a rotating member
  • the seal assembly includes a primary seal assembly and a secondary seal assembly.
  • the primary seal assembly includes a moveable stator member including at least one keyed slot, and at least one biasing member.
  • the biasing member includes at least one key slidably coupled within the at least one keyed slot to facilitate aligning the primary seal assembly and the secondary seal assembly with respect to the gas turbine engine.
  • a gas turbine engine including a stationary stator member, a rotating member, and a seal assembly.
  • the seal assembly including a primary seal assembly and a secondary seal assembly.
  • the primary seal assembly includes a moveable stator member including at least one keyed slot, and at least one biasing member.
  • the biasing member includes at least one key.
  • the at least one key is slidably coupled within the at least one keyed slot to facilitate aligning the primary seal assembly and the secondary seal assembly with respect to the gas turbine engine.
  • the seal assembly facilitates sealing between the stationary stator member and the rotating member.
  • Figure 1 is a schematic illustration of a gas turbine engine 10 including a fan assembly 12, a compressor 14, and a combustor 16.
  • compressor 14 is a high-pressure compressor.
  • Engine 10 also includes a high-pressure turbine 18, and a low-pressure turbine 20.
  • engine 10 is a CFM 56 engine commercially available from General Electric Company, Cincinnati, Ohio.
  • Airflow from fan assembly 12 drives turbines 18 and 20, and turbine 20 drives fan assembly 12.
  • FIG 2 is a cross-sectional view of an exemplary seal assembly 100 that may be used within gas turbine engine 10.
  • gas turbine engine 10 includes stationary stator member 102 coupled to frame 103 and a rotating member 104.
  • Frame 103 is a stationary circumferential member positioned around an axis of rotation (not shown in Figure 2).
  • frame 103 is part of the casing of gas turbine engine 10.
  • stationary stator member 102 is a stationary circumferential member positioned around the axis of rotation of gas turbine engine 10.
  • stationary stator member 102 is bolted to frame 103.
  • rotating member 104 is a rotor that is rotatably coupled within engine 10 to rotate about the axis of rotation.
  • seal assembly 100 includes a primary seal assembly 106 and a secondary seal assembly 108 that are each substantially concentrically aligned with respect to the axis of rotation of gas turbine engine 10.
  • a moveable stator member 110 includes a primary seal assembly 106.
  • Moveable stator member 110 also includes at least one keyed slot 118.
  • moveable stator member 110 includes at least three keyed slots 118.
  • Moveable stator member 110 is also a circumferential member positioned around the axis of rotation of gas turbine engine 10.
  • moveable stator member 110 is positioned within stationary stator member 102.
  • Primary seal assembly 106 also includes at least one biasing member 114.
  • primary seal assembly 106 includes at least three biasing members 114.
  • Biasing member 114 includes at least one key 116, a biasing mechanism 120, and a housing 122.
  • housing 122 is bolted to stationary stator member 102 such that housing 122 is stationary.
  • stationary stator member 102 includes at least three housings 122 spaced along the circumference of stationary stator member 102.
  • Biasing mechanism 120 is contained within housing 122, and key 116 extends radially outward from housing 122. Key 116 is integrally formed with housing 122.
  • biasing mechanism 120 is a spring and housing 122 is a spring cartridge.
  • Moveable stator member 110 includes a keyed slot 118.
  • keyed slot 118 is machined within moveable stator member 110.
  • moveable stator member 110 includes a number of keyed slots 118 equal to the number of keys 116.
  • keyed slot 118 extends a distance and is sized to receive a portion of key 116 therein.
  • key 116 is slidably coupled within keyed slot 118 such that during operation, key 116, as will be described in more detail below, is moveable along a portion of the distance of keyed slot 118.
  • Key 116 moves within keyed slot 118 allowing moveable stator member 110 to move.
  • key 116 facilitates aligning primary seal assembly 106 and secondary seal assembly 108 with respect to gas turbine engine 10.
  • Moveable stator member 110 also includes a sealing face 124 and a plurality of teeth 126 that extend outward from sealing face 124.
  • sealing face 124 is substantially parallel to a rotating member surface 125 of rotating member 104. More specifically, sealing face 124 is a distance 123 away from rotating member 104.
  • Moveable stator member 110 also includes an opening 127 defined therein, and positioned within sealing face 124 such that opening 127 extends through sealing face 124.
  • opening 127 is oriented substantially perpendicular to rotating member surface 125. As described below in more detail, opening 127 facilitates preventing contact between plurality of teeth 126 and rotating member 104.
  • Moveable stator member 110 further includes a plurality of radial openings 134 extending through moveable stator member 110.
  • radial openings 134 are substantially parallel to rotating member surface 125. Additionally, in the exemplary embodiment, radial openings 134 cross between openings 127.
  • Moveable stator member 110 also includes a yoke 130 that is sized to receive at least a portion of secondary seal assembly 108 therein. More specifically, secondary seal assembly 108 includes a seal 128 that is received within yoke 130. In the exemplary embodiment, seal 128 is a piston ring seal. In an alternative embodiment, seal 128 may be retained by stationary stator member 102.
  • cooling air and/or fluids flow through gas turbine engine 10.
  • high pressure air flows forward to aft through engine 10.
  • a portion of the highly compressed air discharged from high pressure compressor 14 is directed towards seal assembly 100 for use as cooling fluid.
  • Seal assembly 100 facilitates substantially controlling fluid flow from a region of higher pressure 137 to a region of lower pressure 140 within gas turbine engine 10. The pressure differential between higher pressure region 137 and lower pressure region 140 initiates flow through seal assembly 100.
  • Biasing mechanism 120 biases moveable stator member 110 away from rotating member 104.
  • Moveable stator member 110 slides forward and aft relative to housing 122, stationary stator member 102, and frame 103.
  • a portion of the high pressure air will flow into a region 138 defined between stationary stator member 102 and moveable stator member 110.
  • the high pressure air exerts a pressure on moveable stator member 110 causing moveable stator member 110 to move, against and to overcome biasing force exerted by biasing mechanism 120, within keyed slot 118, and towards rotating member 104.
  • key 116 translates within keyed slot 118 such that keyed slot 118 limits the amount of travel of moveable stator member 110 and prevents rotational, circumferential and/or radial, movement of moveable stator member 110 with respect to stationary stator member 102, housing 122, and frame 103.
  • Keyed slot 118 also facilitates aligning primary seal and secondary seal assemblies 106 and 108 with respect to gas turbine engine 10.
  • opening 127 is a plurality of feed openings. Opening 127 forms a high pressure film or air bearing between opening 127 and rotating member surface 125. The air bearing prevents moveable stator member 110 from contacting rotating member 104.
  • biasing force of biasing mechanism 120 pushes against moveable stator member 110 moving moveable stator member 110 and holding moveable stator member 110 away from rotating member 104 to prevent contact between members 104 and 110.
  • stationary stator member 102 is coupled to frame 103 of gas turbine engine 10 near rotating member 104.
  • Housing 122 is coupled to stationary stator member 102.
  • Moveable stator member 110 is coupled to and positioned within stationary stator member 102.
  • Keyed slot 118 is positioned at least partially within key 116 and moves within keyed slot 118.
  • Biasing mechanism 120 is coupled and positioned within housing 122.
  • the above-described seal assembly includes a primary seal assembly that includes a moveable stator member and a secondary seal assembly.
  • the moveable stator member facilitates reducing leakage between the rotating member and the stationary engine frame. As a result, the engine operates more efficiently.
  • the above-described seal assembly includes significantly fewer components than some known seal assemblies. With fewer components, such a seal is less expensive to install, is easier to produce than known seal assemblies, reduces the amount and cost of maintenance, is more reliable than known seal assemblies, and is lighter weight. Weight of seal assemblies may adversely affect engine performance.
  • seal assembly is not limited to use with the specific embodiments described herein, but rather, the seal assembly can be utilized independently and separately from other components described herein. Moreover, the invention is not limited to the embodiments of the seal assembly described above in detail. Rather, other variations of a seal assembly may be utilized within the spirit and scope of the claims.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
  • Sealing Devices (AREA)
EP07107277A 2006-05-01 2007-05-01 Système de joint d'étanchéité pour turbine à gaz Withdrawn EP1852573A2 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/416,430 US20070253809A1 (en) 2006-05-01 2006-05-01 Methods and apparatus for assembling gas turbine engines

Publications (1)

Publication Number Publication Date
EP1852573A2 true EP1852573A2 (fr) 2007-11-07

Family

ID=38137546

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07107277A Withdrawn EP1852573A2 (fr) 2006-05-01 2007-05-01 Système de joint d'étanchéité pour turbine à gaz

Country Status (6)

Country Link
US (1) US20070253809A1 (fr)
EP (1) EP1852573A2 (fr)
JP (1) JP2007298033A (fr)
CN (1) CN101074610A (fr)
CA (1) CA2585497A1 (fr)
RU (1) RU2007116056A (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2053201A2 (fr) 2007-10-26 2009-04-29 United Technologies Corporation Ensemble hydrostatique de joint d'étanchéité et ensemble compresseur et moteur à turbine à gaz correspondants
EP2025876A3 (fr) * 2007-08-17 2011-05-18 United Technologies Corporation Joint de turbine et joint de sécurité associé d'un moteur à turbine à gaz et ensemble turbine associé
EP2025877A3 (fr) * 2007-08-17 2011-05-25 United Technologies Corporation Joint hydrostatique d'un moteur à turbine à gaz et ensemble turbine associé
EP2025875A3 (fr) * 2007-08-17 2011-05-25 United Technologies Corporation Joint de turbine et joint de sécurité d'un moteur à turbine à gaz et ensemble turbine associé
US8105021B2 (en) 2007-08-20 2012-01-31 United Technologies Corp. Gas turbine engine systems involving hydrostatic face seals with integrated back-up seals
US8109716B2 (en) 2007-08-17 2012-02-07 United Technologies Corp. Gas turbine engine systems involving hydrostatic face seals with anti-fouling provisioning
EP3118461A1 (fr) * 2015-07-17 2017-01-18 Rolls-Royce plc Moteur à turbine à gaz

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2825849A1 (fr) 2011-12-29 2013-07-04 Elliott Company Ensemble carter d'admission de detendeur de gaz chaud et procede
US9045984B2 (en) 2012-05-31 2015-06-02 United Technologies Corporation Stator vane mistake proofing
US10344602B2 (en) 2016-04-18 2019-07-09 General Electric Company Gas turbine engine transition duct and turbine center frame
GB2553565B (en) * 2016-09-09 2019-04-10 Rolls Royce Plc Air riding seal arrangement
FR3062679B1 (fr) * 2017-02-07 2019-04-19 Safran Aircraft Engines Virole de reduction de la surpression au voisinage du joint amont d'une enceinte de palier de turboreacteur
US10359117B2 (en) 2017-03-06 2019-07-23 General Electric Company Aspirating face seal with non-coiled retraction springs
US10329938B2 (en) * 2017-05-31 2019-06-25 General Electric Company Aspirating face seal starter tooth abradable pocket
US10458267B2 (en) * 2017-09-20 2019-10-29 General Electric Company Seal assembly for counter rotating turbine assembly
US10711629B2 (en) 2017-09-20 2020-07-14 Generl Electric Company Method of clearance control for an interdigitated turbine engine
US10968762B2 (en) * 2018-11-19 2021-04-06 General Electric Company Seal assembly for a turbo machine
US10900570B2 (en) 2018-11-27 2021-01-26 General Electric Company Aspirating face seal assembly for a rotary machine
US10895324B2 (en) * 2018-11-27 2021-01-19 General Electric Company Aspirating face seal assembly for a rotary machine
GB201904727D0 (en) * 2019-04-04 2019-05-22 Rolls Royce Plc Seal assembly
EP3783249B1 (fr) * 2019-08-23 2023-07-12 Raytheon Technologies Corporation Joint d'étanchéité sans contact ayant un agencement axial
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly
CN116696491B (zh) * 2022-03-03 2026-04-03 通用电气公司 用于涡轮发动机的密封组件和相关方法
US20230407762A1 (en) * 2022-06-15 2023-12-21 General Electric Company Dampers for seal assemblies

Citations (1)

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US5284347A (en) 1991-03-25 1994-02-08 General Electric Company Gas bearing sealing means

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US3383033A (en) * 1966-04-27 1968-05-14 Gen Electric Sealing means for axial flow compressor discharge
US4375891A (en) * 1980-05-10 1983-03-08 Rolls-Royce Limited Seal between a turbine rotor of a gas turbine engine and associated static structure of the engine
US4477088A (en) * 1982-12-20 1984-10-16 United Technologies Corporation Face seal means with back-up seal
US4916892A (en) * 1988-05-06 1990-04-17 General Electric Company High pressure seal
US5174584A (en) * 1991-07-15 1992-12-29 General Electric Company Fluid bearing face seal for gas turbine engines
CA2076120A1 (fr) * 1991-09-11 1993-03-12 Adam Nelson Pope Systeme et methode permettant d'ameliorer le refroidissement d'un moteur
US5593165A (en) * 1994-09-20 1997-01-14 Allison Engine Company, Inc. Circumferential flow channel for carbon seal runner cooling
US5769604A (en) * 1995-05-04 1998-06-23 Eg&G Sealol, Inc. Face seal device having high angular compliance
US6145840A (en) * 1995-06-02 2000-11-14 Stein Seal Company Radial flow seals for rotating shafts which deliberately induce turbulent flow along the seal gap
US5975537A (en) * 1997-07-01 1999-11-02 General Electric Company Rotor and stator assembly configured as an aspirating face seal
US6758477B2 (en) * 2002-03-26 2004-07-06 General Electric Company Aspirating face seal with axially biasing one piece annular spring
US6676369B2 (en) * 2002-03-26 2004-01-13 General Electric Company Aspirating face seal with axially extending seal teeth
US6719296B2 (en) * 2002-07-12 2004-04-13 General Electric Company Seal for a rotating member
US6932567B2 (en) * 2002-12-19 2005-08-23 General Electric Company Method and apparatus for controlling fluid leakage through gas turbine engines

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Publication number Priority date Publication date Assignee Title
US5284347A (en) 1991-03-25 1994-02-08 General Electric Company Gas bearing sealing means

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2025876A3 (fr) * 2007-08-17 2011-05-18 United Technologies Corporation Joint de turbine et joint de sécurité associé d'un moteur à turbine à gaz et ensemble turbine associé
EP2025877A3 (fr) * 2007-08-17 2011-05-25 United Technologies Corporation Joint hydrostatique d'un moteur à turbine à gaz et ensemble turbine associé
EP2025875A3 (fr) * 2007-08-17 2011-05-25 United Technologies Corporation Joint de turbine et joint de sécurité d'un moteur à turbine à gaz et ensemble turbine associé
US8109717B2 (en) 2007-08-17 2012-02-07 United Technologies Corp. Gas turbine engine systems involving hydrostatic face seals with integrated back-up seals
US8109716B2 (en) 2007-08-17 2012-02-07 United Technologies Corp. Gas turbine engine systems involving hydrostatic face seals with anti-fouling provisioning
US8105021B2 (en) 2007-08-20 2012-01-31 United Technologies Corp. Gas turbine engine systems involving hydrostatic face seals with integrated back-up seals
EP2053201A2 (fr) 2007-10-26 2009-04-29 United Technologies Corporation Ensemble hydrostatique de joint d'étanchéité et ensemble compresseur et moteur à turbine à gaz correspondants
EP2053201A3 (fr) * 2007-10-26 2012-01-18 United Technologies Corporation Ensemble hydrostatique de joint d'étanchéité et ensemble compresseur et moteur à turbine à gaz correspondants
EP3118461A1 (fr) * 2015-07-17 2017-01-18 Rolls-Royce plc Moteur à turbine à gaz
US10487688B2 (en) 2015-07-17 2019-11-26 Rolls-Royce Plc Gas turbine engine

Also Published As

Publication number Publication date
JP2007298033A (ja) 2007-11-15
RU2007116056A (ru) 2008-11-10
CA2585497A1 (fr) 2007-11-01
US20070253809A1 (en) 2007-11-01
CN101074610A (zh) 2007-11-21

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