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EP1291493A2 - Garniture latérale d'étanchéité pour une pièce de transition et ensemble de turbine comportant une telle garniture d'étanchéité - Google Patents

Garniture latérale d'étanchéité pour une pièce de transition et ensemble de turbine comportant une telle garniture d'étanchéité Download PDF

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Publication number
EP1291493A2
EP1291493A2 EP02255697A EP02255697A EP1291493A2 EP 1291493 A2 EP1291493 A2 EP 1291493A2 EP 02255697 A EP02255697 A EP 02255697A EP 02255697 A EP02255697 A EP 02255697A EP 1291493 A2 EP1291493 A2 EP 1291493A2
Authority
EP
European Patent Office
Prior art keywords
turbine
seal
edge regions
raised edge
thickness
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Withdrawn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
EP02255697A
Other languages
German (de)
English (en)
Other versions
EP1291493A3 (fr
Inventor
Robert Harold Cromer
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 EP1291493A2 publication Critical patent/EP1291493A2/fr
Publication of EP1291493A3 publication Critical patent/EP1291493A3/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Withdrawn legal-status Critical Current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
    • F01D11/005—Sealing means between non relatively rotating elements

Definitions

  • the present invention relates generally to seals, and more particularly to a spline seal for a turbine.
  • Turbines include gas and steam turbines.
  • Gas turbines include, but are not limited to, gas turbine power generation equipment and gas turbine aircraft engines.
  • a gas turbine has a gas path which typically includes, in serial-flow relationship, an air intake (or inlet), a compressor, a combustor, a turbine, and a gas outlet (or exhaust nozzle).
  • Gas-path leakage occurs through gaps between gas turbine subassemblies such as through gaps between the combustor and the turbine, and gas-path leakage occurs through gaps between the components that make up a gas turbine subassembly, such as through gaps between combustor casing segments.
  • Such components and subassemblies have surfaces of different shapes, suffer from assembly misalignment, and undergo vibration. Hot-section components thermally experience hot gas flow and typically undergo different thermal growths.
  • Gas leakage either out of the gas path or into the gas path, from an area of higher pressure to an area of lower pressure, is generally undesirable.
  • gas-path leakage in the turbine or compressor area of a gas turbine between the rotor of the turbine or compressor and the circumferentially surrounding turbine or compressor casing, will lower the efficiency of the gas turbine leading to increased fuel costs.
  • gas-path leakage in the combustor area of a gas turbine will require an increase in burn temperature to maintain power level, such increased burn temperature leading to increased pollution, such as increased NOx and CO production.
  • Steam turbines (which can be considered a special type of gas turbine) include, but are not limited to, steam turbine power generation equipment.
  • a steam turbine includes a steam inlet, a turbine, and a steam outlet, wherein steam is the gas which turns the turbine rotor.
  • the turbine of a steam turbine is similar to the turbine of a gas turbine and suffers from steam-path leakage the way the turbine of a gas turbine suffers from gas-path leakage.
  • a known fluid-path leakage seal is a cloth seal having a generally impervious and uniformly-thick shim assemblage and a cloth assemblage generally surrounding the shim assemblage.
  • Cloth seals may be used in many applications including, but not limited to, seal assemblies for steam turbines and gas turbines used for power generation and seal assemblies for gas turbines used for aircraft and marine propulsion.
  • Another fluid-path leakage seal for sealing the gap between two circumferentially-adjacent (and non-rotating) transition pieces of a power-system gas turbine is disclosed in commonly owned U.S. Patent Number 6,162,014.
  • This seal is a manually-flexible metal seal that has a uniform thickness in the general shape of an elongated rectangular metal sheet, and has a fiber-fabric cloth layer wrapped around the metal sheet.
  • One elongated edge of the metal bar is engaged in a surface groove of one transition piece.
  • the other elongated edge of the metal bar is engaged in a matching and aligned surface groove of the other transition piece.
  • One end of the metal bar serves as a mounting bracket, having a right-angle bend, which is used to secure the seal to a (non-rotating) first-stage nozzle.
  • the grooves of transition pieces are not perfectly machined, and the grooves of transition pieces installed in power-system gas turbines are not perfectly aligned. As a result, in spite of the flexibility of the metal seal an effective seal may not be achieved between the transition pieces.
  • the metal sheet component design limits functional, manufacturing and assembly options.
  • the gas-path leakage seal is for generally sealing a gas-path leakage-gap between spaced-apart first and second members of a turbine.
  • the turbine seal of the present invention includes an elongated seal member having a length and having opposing first and second ends bounding said length, an elongated, imperforate, and flexible first portion, and a rigid second portion lengthwise adjoining said first portion, wherein said first portion is lengthwise disposed between said first end and said second portion, wherein said second portion is lengthwise disposed between said first portion and said second end, wherein said flexible first portion includes a shim-layer assemblage having opposing first and second surfaces and having two longitudinally extending raised edge regions, wherein each of said raised edge regions extends a generally identical distance above said first surface and each of said raised edge regions extends generally said identical distance below said second surface; and wherein said flexible first portion further includes a cloth layer assemblage having a thickness generally equal to or slightly greater than said identical distance and superimposed on said second surface between said raised edge regions, and wherein said second portion defines a mounting bracket.
  • the cloth layer assemblage and the shim-layer assemblage are attached together by spot welds, and the raised edges have curved portions.
  • a turbine assembly in another aspect of the invention, includes a) a first turbine member having a first surface groove; b) a second turbine member proximate and spaced apart from said first turbine member so as to define a fluid-path leakage gap therebetween, said second turbine member having a second surface groove facing and generally aligned with said first surface groove; and c) a turbine seal including an elongated turbine seal member having a length and having opposing first and second ends bounding said length, an elongated, imperforate, and flexible first portion, and a rigid second portion lengthwise adjoining said first portion, wherein said first portion is lengthwise disposed between said first end and said second portion, wherein said second portion is lengthwise disposed between said first portion and said second end, wherein said flexible first portion includes a shim-layer assemblage having opposing first and second surfaces and having two longitudinally extending raised edge regions, wherein each of said raised edge regions extends a generally identical distance above said first surface and each of said raised edge regions extends generally said identical
  • the turbine seal is vibrationally excited within a range of vibrational frequencies by motion of generally only the first and second turbine members during operation of the turbine, and the turbine seal is devoid of any resonant frequency within the range of vibrational frequencies.
  • the turbine assembly is a power-system gas turbine assembly
  • the first and second turbine members are circumferentially-adjacent transition pieces
  • the mounting bracket is secured to a third turbine member comprising a first stage nozzle.
  • the manually-flexible main body of the turbine seal member allows all transition-piece turbine spline seals in a standard power-system gas turbine to be replaced in generally half a day instead of the several days required for prior-art seals.
  • manually flexible main body which may be a metal sheet, provides good sealing of gas flow as the raised edges are pushed against the first and second turbine members by gas from the higher-pressure side of the seal.
  • the first cloth layer provides some sealing and good wear resistance.
  • the flexible metal sheet and the inherent flexibility of the cloth layer provides good seal flexibility which means the seal is very compliant and can accommodate surfaces of different shapes, assembly misalignment, vibration, and differential thermal growth. The spot welds make it easier to assemble the seal, and the curved portions make it easier to install the seal.
  • FIGURE 1 shows a first embodiment of the turbine seal of the present invention.
  • the turbine seal is defined by an elongated turbine seal member 10 that has having a length and first and second ends 12 and 14.
  • the turbine seal member includes an elongated, imperforate first portion 16 and also includes a second portion 18 lengthwise adjoining the first portion.
  • the first portion 16 defines the main body of the seal member and is manually-flexible.
  • the second portion 18 defines a mounting bracket of the seal member and is manually-rigid.
  • manufactured it is meant that the first portion 16 can be flexed by hand by an adult person of average strength.
  • manufactured it is meant that the second portion 18 cannot be flexed by hand by an adult person of average strength.
  • the first portion is lengthwise disposed between the first end and the second portion, the second portion is lengthwise disposed between the first portion and the second end.
  • the first portion 16 is comprised of an imperforate shim-layer assemblage 20 that has a first thickness and the second portion 18 is defined from a bent strip or plate 22 that has a second thickness.
  • the second thickness is on the order of at least about five times greater than the first thickness.
  • the shim-layer assemblage comprises at least one shim layer or plate of uniform thickness, and may comprise at least two superimposed, generally identical shim layers or plates.
  • the assemblage has no more than four layers.
  • Each shim layer is impervious to gas and comprises a metal, ceramic, and/or polymer sheet.
  • the choice of materials for the shim and the choice of the thickness for a shim layer are made by the artisan to meet the sealing, flexibility, and resilience requirements of a particular seal application.
  • the shim-layer has a thickness of generally between about five and twenty thousandths of an inch, for example, about ten thousandths of an inch where two shim layers are provided.
  • each shim layer comprises a high-temperature, cobalt-based super-alloy, such as HS-188. It is noted that the shim layers can comprise different materials and/or have different thicknesses depending on the particular seal application.
  • the first portion of the seal member is comprised of two superimposed and identical shim layers 24, 124, formed from metal.
  • the first end 12 of the seal member is edge-welded. Further, to facilitate placement of the seal member, the first end 12 is chamfered as shown at 26.
  • a flexible and generally imperforate shim-layer assemblage 20 having opposing first and second surfaces, defined in the illustrated embodiment by the top surface 28 of shim plate 24 and the bottom surface 30 of shim plate 124, respectively.
  • the shim-layer assemblage further includes to raised edges 32, 132.
  • one raised edge 32 is formed entirely from one of the edges of one metal shim sheet 24, and the other raised edge 132 is formed entirely from one of the edges of another metal shim sheet 124.
  • Each of the raised edges extends a generally identical distance above the first surface 28, and each of the raised edges extends generally that same identical distance below the second surface 30.
  • the directions “above” and “below” are relative directions applying to the seal as viewed in FIGURES 1 and 3.
  • the raised edges 32, 132 are generally mirror images of each other.
  • the shim-layer assemblage is an elongated metal strip assemblage having a centerline running midway between the raised edges and having a cross section (shown in FIGURE 3) generally perpendicular to the centerline.
  • each of the raised edges has a first portion 34, 134 disposed at the previously-defined generally identical distance above the first surface 28 of the metal sheet assemblage
  • each of the raised edges has a second portion 36, 136 disposed at the previously-defined generally identical distance below the second surface 30.
  • the first portion has a curved shape.
  • the raised edges each terminate proximate the second portion 36, 136.
  • each of the raised edges has a connecting portion 38, 138 joining together the first and second portions.
  • the connecting portions 38, 138 have a curved shape, more specifically a generally bowed shape, pointing away from each other as illustrated in FIGURE 3. Such curved bowed shape facilitates seal installation in many seal applications, as described in greater detail below.
  • each sheet metal member is stamped or rolled to form the curved raised edges. It is noted that seal can be made by pressing seal between two pressing plates (not shown).
  • the seal member further includes a cloth layer assemblage 40.
  • the cloth layer assemblage 40 has a thickness generally the same as or slightly greater than (e.g. by the thickness of one of the metal sheets or shims comprising the shim-layer assemblage) the previously defined identical distance (i.e., the identical distance the first and second raised edges extend above the first surface).
  • the cloth layer assemblage 40 is superimposed on the second surface between the raised edges.
  • the cloth layer assemblage comprises at least one cloth layer, only one of which is shown in FIGURE 3.
  • Each cloth layer comprises metal, ceramic, and/or polymer fibers that have been woven, knitted, or pressed into a layer of fabric.
  • each cloth layer is a woven cloth layer comprising L605 or Haynes-25.
  • An exemplary cloth layer is a twilled metal cloth layer.
  • twilled is meant a cloth having a twill weave (such as a twill weave which floats weft threads over two warp threads and which staggers these floats regularly).
  • the cloth layer has 30 warp wires per inch and 250 weft wires per inch with each warp and weft wire having a thickness of 7-10 mils and with the cloth layer having an overall thickness of about 0.052 inch.
  • An exemplary cloth-layer assemblage is a Dutch Twill weave cloth assemblage comprising a high-temperature, cobalt-based super-alloy, such as L-605. It is noted that a Dutch Twill weave will allow a small controlled leakage which provides cooling, as can be appreciated by the artisan.
  • the cloth layer assemblage 40 is superimposed on generally the entire second surface 30.
  • the cloth layer assemblage 40 and the metal shim-layer assemblage 20 are attached together by a plurality of spot welds 42 (as shown in FIGURE 4).
  • spot welds 42 as shown in FIGURE 4
  • seam welds are used in place of spot welds.
  • the first portion 16 of the turbine seal member is defined by its corresponding sections of the shim-layer and cloth-layer assemblages.
  • the second portion 18 of the turbine seal member 10 includes a base portion 44 lengthwise overlapping the corresponding section of the cloth-layer assemblage 40 of the first portion and attached (such as by spot welding 46) to the corresponding sections of the cloth-layer and shim-layer assemblages.
  • the second portion 18 of the turbine seal member 10 which may be made of stainless steel, includes a generally right-angle bend 48 to define mounting bracket 22 having a support portion 50 adjoining the base portion 44.
  • FIGURES 7 and 8 schematically show a first embodiment of the gas-path leakage seal of the present invention.
  • the gas-path leakage seal is for generally sealing a gas-path leakage-gap between spaced-apart first and second members of a gas turbine (only a small portion of which is shown in FIGURE 7).
  • the turbine assembly includes a first turbine member 52, a second turbine member 54 which is proximate and circumferentially spaced apart from the first turbine member so as to define a fluid-path leakage gap 56 therebetween, and a turbine seal 10 embodying the invention.
  • the first turbine member 52 has a first surface groove or slot 58
  • the second turbine member has a second surface groove or slot 60 facing and generally aligned with the first surface groove 58.
  • a fluid-path leakage gap as used herein includes, without limitation, a steam-path leakage gap of a turbine of a steam turbine, a compressed-air leakage gap of a compressor of a gas turbine, and a combustion-gas leakage gap in or downstream of a combustor of a gas turbine.
  • downstream of the combustor includes the transition pieces, first-stage nozzle and turbine sections.
  • the turbine seal 10 is identical to the previously-described turbine seal shown in FIGURES 1-6.
  • the gas-path leakage seal member is disposed in the gap to extend partially in the first groove and partially in the second groove with one of the raised edges disposed entirely within the first groove and the other of the raised edges disposed entirely within the second groove.
  • the gas-path leakage-gap has a higher-pressure end and a lower-pressure end. This pressure differential seats the seal such that the raised edges can resiliently and unattachedly contact the first and second members respectively along the lower pressure side of the respective first and second slots and such that the second cloth layer assemblage can also unattachedly contact the first and second members and along the lower pressure side of the first and second slots.
  • the resilient contact of the metal sheet assemblage maintains sealing in the "plane" of the seal while allowing for different surface shapes, assembly misalignment, vibration, and/or thermally-induced relative movement between the first and second members.
  • the way in which the seal assembly is inserted with respect to the turbine members is controlled so that the cloth layer 40 may only be provided on one side of the seal strip, as illustrated. Specifically, the cloth is provided on the downstream, pressure side of the junction.
  • the cloth layer assemblage is pushed by the differential pressure into contact with the first and second members (as shown in FIGURE 8).
  • the cloth layer assemblage protects the metal sheet assemblage 20 against wear.
  • the installed seal is not welded or otherwise attached to the first and/or second members allowing for ease of installation.
  • the turbine spline seal is vibrationally excited within a range of vibrational frequencies by motion of generally only the first and second turbine members 52, 54.
  • the turbine spline seal is devoid of any resonant frequency within the range of vibrational frequencies, as is within the skill of the artisan to design by choosing, for example, an appropriate thickness and length of the mounting bracket 22.
  • the turbine assembly also includes a third turbine member 62, and the mounting bracket 22 is secured to the third turbine member 62.
  • the turbine assembly is a power-system gas turbine assembly
  • the first and second turbine members 52, 54 are circumferentially-adjacent transition pieces of the gas turbine assembly
  • the third turbine member 62 is a first stage nozzle of the gas turbine assembly.
  • the installed turbine seal member 10 is radially aligned, with the mounting bracket 22 located at its radially-outer end, and a mounting block 64 is used to secure the mounting bracket 35 to the third turbine member 62.
  • the mounting block has a bolt hole 66 and the third turbine member has a threaded bolt hole (not shown).
  • a bolt 68 passes through the bolt hole in the mounting block and threadably-engages the threaded bolt hole of the third turbine member.
  • Mounting block 64 also has a first slot 70 and a second slot 72.
  • the right-angle bend 48 of the second portion 18 engages the lower of the two slots.
  • the first slot 70 is the lower slot in FIGURE 7.
  • the mounting block 64 may be rotated one half turn about bolt 66. As rotated, the second slot 72 will become the lower slot for engagement with the right-angle bend 48 of the second portion 18 of the turbine seal member 10.
  • the manually-flexible first portion 16 of the turbine seal member 10 allows all transition-piece turbine spline seals in a standard power-system gas turbine to be replaced in generally half a day instead of the several days required for prior-art seals. It has been found that some prior-art seals had a dominant resonant frequency which was excited by the vibration (including twisting) motion of the transition pieces leading to early seal failure.
  • the manually-rigid second portion 18 of the turbine seal member of the turbine seal 10 has its length and thickness chosen, as can be appreciated by those skilled in the art, to avoid the installed turbine seal from having any resonant frequencies which can be excited by the vibrational motion (typically between 80 and 200 Hertz) of the transition pieces during operation of the turbine.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)
EP02255697A 2001-08-21 2002-08-13 Garniture latérale d'étanchéité pour une pièce de transition et ensemble de turbine comportant une telle garniture d'étanchéité Withdrawn EP1291493A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US682335 2001-08-21
US09/682,335 US20030039542A1 (en) 2001-08-21 2001-08-21 Transition piece side sealing element and turbine assembly containing such seal

Publications (2)

Publication Number Publication Date
EP1291493A2 true EP1291493A2 (fr) 2003-03-12
EP1291493A3 EP1291493A3 (fr) 2009-06-10

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EP02255697A Withdrawn EP1291493A3 (fr) 2001-08-21 2002-08-13 Garniture latérale d'étanchéité pour une pièce de transition et ensemble de turbine comportant une telle garniture d'étanchéité

Country Status (3)

Country Link
US (1) US20030039542A1 (fr)
EP (1) EP1291493A3 (fr)
JP (1) JP2003097220A (fr)

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EP1785592A2 (fr) * 2005-11-10 2007-05-16 General Electric Company Système de joint d'étanchéité pour turbine à gaz
WO2011153393A3 (fr) * 2010-06-04 2012-04-26 Siemens Energy, Inc. Structure d'étanchéité de turbine à gaz
CN102536338A (zh) * 2010-11-29 2012-07-04 通用电气公司 用于涡轮机的织物密封件
FR2970503A1 (fr) * 2011-01-14 2012-07-20 Gen Electric Ensemble et procede pour empecher le passage d'un fluide
CN103375589A (zh) * 2012-04-30 2013-10-30 通用电气公司 用于涡轮系统中的过渡管道的柔性密封件
WO2014025733A1 (fr) * 2012-08-06 2014-02-13 General Electric Company Joint d'étanchéité contre les fuites de trajet de gaz pour une turbine
FR3065986A1 (fr) * 2017-05-02 2018-11-09 Safran Aircraft Engines Ensemble pour turbine a gaz, turbine a gaz associee
US10196913B1 (en) 2014-12-17 2019-02-05 United Technologies Corporation Featherseal having tapered radial portion
EP3789638A1 (fr) * 2019-09-05 2021-03-10 Siemens Aktiengesellschaft Joint pour appareil de combustion

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US10436445B2 (en) 2013-03-18 2019-10-08 General Electric Company Assembly for controlling clearance between a liner and stationary nozzle within a gas turbine
US9416675B2 (en) * 2014-01-27 2016-08-16 General Electric Company Sealing device for providing a seal in a turbomachine
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US9970308B2 (en) * 2015-01-26 2018-05-15 United Technologies Corporation Feather seal
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US10927691B2 (en) 2019-03-21 2021-02-23 Solar Turbines Incorporated Nozzle segment air seal
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Cited By (16)

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Publication number Priority date Publication date Assignee Title
EP1785592A3 (fr) * 2005-11-10 2012-08-01 General Electric Company Système de joint d'étanchéité pour turbine à gaz
EP1785592A2 (fr) * 2005-11-10 2007-05-16 General Electric Company Système de joint d'étanchéité pour turbine à gaz
US8821114B2 (en) 2010-06-04 2014-09-02 Siemens Energy, Inc. Gas turbine engine sealing structure
WO2011153393A3 (fr) * 2010-06-04 2012-04-26 Siemens Energy, Inc. Structure d'étanchéité de turbine à gaz
CN102536338A (zh) * 2010-11-29 2012-07-04 通用电气公司 用于涡轮机的织物密封件
CN102536338B (zh) * 2010-11-29 2015-12-16 通用电气公司 用于涡轮机的织物密封件
FR2970503A1 (fr) * 2011-01-14 2012-07-20 Gen Electric Ensemble et procede pour empecher le passage d'un fluide
EP2660428A1 (fr) * 2012-04-30 2013-11-06 General Electric Company Système de turbine comprenant un conduit de transition avec un joint d'étanchéité souple
CN103375589A (zh) * 2012-04-30 2013-10-30 通用电气公司 用于涡轮系统中的过渡管道的柔性密封件
WO2014025733A1 (fr) * 2012-08-06 2014-02-13 General Electric Company Joint d'étanchéité contre les fuites de trajet de gaz pour une turbine
US10196913B1 (en) 2014-12-17 2019-02-05 United Technologies Corporation Featherseal having tapered radial portion
FR3065986A1 (fr) * 2017-05-02 2018-11-09 Safran Aircraft Engines Ensemble pour turbine a gaz, turbine a gaz associee
US10760440B2 (en) 2017-05-02 2020-09-01 Safran Aircraft Engines Assembly for gas turbine, associated gas turbine
EP3789638A1 (fr) * 2019-09-05 2021-03-10 Siemens Aktiengesellschaft Joint pour appareil de combustion
WO2021043527A1 (fr) * 2019-09-05 2021-03-11 Siemens Energy Global GmbH & Co. KG Joint pour appareil de combustion
US11746667B2 (en) 2019-09-05 2023-09-05 Siemens Energy Global GmbH & Co. KG Seal for combustion apparatus

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US20030039542A1 (en) 2003-02-27
EP1291493A3 (fr) 2009-06-10
JP2003097220A (ja) 2003-04-03

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