EP0995881B1 - Joint d'étanchéité - Google Patents

Joint d'étanchéité Download PDF

Info

Publication number
EP0995881B1
EP0995881B1 EP99810907A EP99810907A EP0995881B1 EP 0995881 B1 EP0995881 B1 EP 0995881B1 EP 99810907 A EP99810907 A EP 99810907A EP 99810907 A EP99810907 A EP 99810907A EP 0995881 B1 EP0995881 B1 EP 0995881B1
Authority
EP
European Patent Office
Prior art keywords
sealing arrangement
guide
arrangement according
felt
sealing
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 - Lifetime
Application number
EP99810907A
Other languages
German (de)
English (en)
Other versions
EP0995881A3 (fr
EP0995881A2 (fr
Inventor
Alexander Dr. Beeck
Mohamed Dr. Nazmy
Bernhard Dr. Weigand
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.)
Alstom SA
Original Assignee
Alstom Schweiz 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 Alstom Schweiz AG filed Critical Alstom Schweiz AG
Publication of EP0995881A2 publication Critical patent/EP0995881A2/fr
Publication of EP0995881A3 publication Critical patent/EP0995881A3/fr
Application granted granted Critical
Publication of EP0995881B1 publication Critical patent/EP0995881B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D11/006—Sealing the gap between rotor blades or blades 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
    • F01D11/005—Sealing means between non relatively rotating elements

Definitions

  • the invention relates to a sealing arrangement for reducing leakage currents within a flow rotation machine according to the preamble of Claim 1.
  • Seals consist of a sealing surface with or without a spring element exist and in a correspondingly provided in the rotor or guide blade root Sealing groove contour.
  • the spring element generates one Contact pressure as well as the positioning of the sealing surface between those to be sealed Contours.
  • Such seals are used in static gas turbine components carrying hot gas, such as turbine guide vanes, heat accumulation segments or combustion chamber segments to reduce cooling air consumption, to prevent axial gap flows with hot gas and to shield against heat radiation.
  • the two sealing surfaces has, which each include an elastic corrugated surface.
  • the sealing arrangement to be designed in different surface shapes However, it requires flat, sealed contour surfaces on which they lie flat can. Is it the sealing of intermediate gaps, that of curved Surfaces are included, so the known sealing arrangement bumps to its limits.
  • GB 1 580 884 also describes a sealing arrangement with sealing elements made of metal, thermoplastic or ceramic.
  • the invention has for its object a sealing arrangement for reduction of leakage currents within a rotary flow machine, preferably an axial turbomachine, with rotor and guide vanes, each in at least a row of guide blades or guide vanes are arranged and have blade feet, via which the individual rotor blades and guide vanes are connected with fastening contours are to be designed such that the sealing arrangement between any shape Gaps between spaces is adjustable.
  • the sealing arrangement should consist of one Material that corresponds to the operating conditions prevailing in a gas turbine plant, with regard to the high temperatures and pressure conditions, without prejudice survives.
  • a sealing arrangement according to the preamble of the claim 1 designed such that in the space between two adjacent Blade feet within a guide or blade row or between Guide and / or blades and adjacent components of the turbomachine a sealing element comprising a felt-like material is provided.
  • Felt-like materials based on intermetallic fibers can be undamaged Temperatures of over 1000 ° C survive because of the intermetallic Fibers have a high heat resistance. They also have one high resistance to oxidation and advantageous thermal conductivity. These properties can also be specifically adjusted by the selected intermetallic fiber and be adapted to the respective conditions. Add to that that through appropriate Choice of the intermetallic used in the manufacture of the felt-like material Fibers a fine-grained structure with selectively adjustable porosity and thus associated elasticity is possible.
  • the intermetallic fibers preferably consist of an intermetallic Aluminum-iron or nickel-based phase or of an alloy of the above mentioned components.
  • the sealing elements according to the invention are designed like a strand and have, depending on the cross-sectional shape of the space to be sealed between two adjacent blade feet, over different strand cross-sections, for example rectangular, angled or cross-shaped cross sections.
  • the strand-like sealing element is preferably firmly attached to at least a blade root attached at a suitable location, for example by gluing, Soldering or welding.
  • a suitable location for example by gluing, Soldering or welding.
  • the felt-like material it is also possible to use the felt-like material to have a precise fit in the correspondingly provided grooves.
  • Figure 1 there are two blade feet 1, 2 in a highly schematic manner opposite, for example arranged in a guide or moving blade row are.
  • a sealing element 3 made of felt-like material.
  • the sealing element 3 is true to shape adapted the surface contours of both blade feet 1 and 2 so that the seal seals both blade feet 1 and 2 gas-tight against each other.
  • the sealing element 3 is fixed with a Blade foot connected. This is preferably done with the help of a soldering, adhesive or Welded joint.
  • the sealing element 3 is fixed with the blade root 1 along its contact contour 4.
  • FIG 2a two are arranged side by side in a perspective view Guide vanes 5 and 6 are shown, each having a headband 7, a guide blade blade 8 and have a guide blade root 9. Between the opposite Headbands 7 of the guide vanes 5 and 6 and the opposite guide vane feet 9 is in each case a sealing element suitably adapted to the intermediate space 3, consisting of felt-like material.
  • FIG. 2a shows two blades 10, 11 arranged side by side - the blade is only for reasons of a clearer presentation Blade 10 not shown - between those in the upper region of the blade feet likewise the sealing elements 3 according to the invention are provided.
  • FIGS. 3a to 3e A large number of differently shaped sealing elements are shown in FIGS. 3a to 3e.
  • the sealing element 3 in FIG. 3a protrudes into two opposite ones Grooves 12, 13 each of two adjacent blade feet.
  • this includes Sealing element 3 both a vertical contact surface of the blade root shown as well as part of the lower horizontal support surface.
  • Figure 3c shows one Sheet metal structure 14 for fastening purposes, on the vertical flank of which Felt-like material provided sealing element 3 is attached.
  • the sealing element 3 can also be made by means of soldered, adhesive and welded connections Detachable connections, such as screw connections, to corresponding Contact surfaces are attached.
  • a side view is shown by a guide vane in the area of the guide vane foot 9 has a sealing element 3, which is blunt on a plane Side surface is soldered.
  • the guide vane sits in the area of the headband 7 the felt-like sealing element 3 'in a corresponding groove-shaped recess within the headband.
  • Such grooves can also be in the form of a dovetail shape be carried out as shown in Figure 3e. Here it can Sealing element 3 inserted laterally into the dovetail-like recess or removed again.
  • sealing elements 3 are provided the entry of hot gases into the space between the housing 17 and the first Prevent vane 18.
  • a further sealing element 3 ' likewise seals the lateral space between the guide vane foot and housing 17 from gas-tight.
  • the sealing arrangement according to the invention consisting of felt-like material, which in Kind of an intermetallic felt is basically in there anywhere Spaces are inserted in which a gas flow is prevented should. Due to the high oxidation resistance and high resistance against mechanical deformations this is suitable on aluminides or Intermetallic felts based on nickel aluminides are particularly preferred for use in gas turbines, where hot temperature conditions and high pressure ratios are predominant.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (7)

  1. Agencement d'étanchéité pour réduire les courants de fuite à l'intérieur d'une turbomachine rotative, de préférence une turbomachine axiale, avec des aubes mobiles et directrices, qui sont à chaque fois disposées dans au moins une rangée d'aubes mobiles ou directrices et qui présentent des bases d'aubes (1, 2), par le biais desquelles les aubes mobiles et directrices individuelles sont raccordées à des contours de fixation, caractérisé en ce qu'entre deux bases d'aubes mobiles (1, 2) à l'intérieur d'une rangée d'aubes directrices ou d'aubes mobiles ou entre des aubes directrices et/ou mobiles et des composants adjacents de la turbomachine rotative, on prévoit un élément d'étanchéité (3) présentant un matériau de type feutre, le matériau de type feutre étant un feutre intermétallique constitué de fibres intermétalliques comprimées et frittées.
  2. Agencement d'étanchéité selon la revendication 1, caractérisé en ce que l'élément d'étanchéité (3) est adapté des deux côtés par engagement positif aux contours extérieurs des bases des aubes voisines (1, 2).
  3. Agencement d'étanchéité selon la revendication 1 ou 2, caractérisé en ce que l'élément d'étanchéité (3) est fixement raccordé à au moins une base d'aube (1).
  4. Agencement d'étanchéité selon la revendication 3, caractérisé en ce que la connexion est une connexion par brasage ou par collage.
  5. Agencement d'étanchéité selon l'une quelconque des revendications 1 à 4, caractérisé en ce que les fibres intermétalliques se composent d'une phase intermétallique à base d'aluminium, de fer ou de nickel, ou d'un alliage de ces constituants.
  6. Agencement d'étanchéité selon l'une quelconque des revendications 1 à 5, caractérisé en ce que le matériau de type feutre présente une porosité telle que le matériau puisse être traversé par de l'air de refroidissement.
  7. Agencement d'étanchéité selon l'une quelconque des revendications 1 à 6, caractérisé en ce que les composants adjacents de la turbomachine sont des pièces du carter ou la chambre de combustion.
EP99810907A 1998-10-19 1999-10-06 Joint d'étanchéité Expired - Lifetime EP0995881B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19848103 1998-10-19
DE19848103A DE19848103A1 (de) 1998-10-19 1998-10-19 Dichtungsanordnung

Publications (3)

Publication Number Publication Date
EP0995881A2 EP0995881A2 (fr) 2000-04-26
EP0995881A3 EP0995881A3 (fr) 2002-03-13
EP0995881B1 true EP0995881B1 (fr) 2004-01-07

Family

ID=7884914

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99810907A Expired - Lifetime EP0995881B1 (fr) 1998-10-19 1999-10-06 Joint d'étanchéité

Country Status (4)

Country Link
US (1) US6312218B1 (fr)
EP (1) EP0995881B1 (fr)
JP (1) JP4465067B2 (fr)
DE (2) DE19848103A1 (fr)

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19937577A1 (de) * 1999-08-09 2001-02-15 Abb Alstom Power Ch Ag Reibungsbehaftete Gasturbinenkomponente
DE10047307A1 (de) 2000-09-25 2002-08-01 Alstom Switzerland Ltd Dichtungsanordnung
JP2003035105A (ja) * 2001-07-19 2003-02-07 Mitsubishi Heavy Ind Ltd ガスタービン分割壁
DE50211431D1 (de) 2001-09-25 2008-02-07 Alstom Technology Ltd Dichtungsanordnung zur dichtspaltreduzierung innerhalb einer strömungsrotationsmaschine
US6854960B2 (en) * 2002-06-24 2005-02-15 Electric Boat Corporation Segmented composite impeller/propeller arrangement and manufacturing method
CN100430499C (zh) * 2002-08-16 2008-11-05 阿尔斯托姆科技有限公司 金属间材料及该材料的应用
US6883807B2 (en) 2002-09-13 2005-04-26 Seimens Westinghouse Power Corporation Multidirectional turbine shim seal
US6733234B2 (en) 2002-09-13 2004-05-11 Siemens Westinghouse Power Corporation Biased wear resistant turbine seal assembly
US6893217B2 (en) * 2002-12-20 2005-05-17 General Electric Company Methods and apparatus for assembling gas turbine nozzles
US20070048140A1 (en) * 2005-08-24 2007-03-01 General Electric Company Methods and apparatus for assembling gas turbine engines
EP1914389A1 (fr) * 2006-10-20 2008-04-23 Siemens Aktiengesellschaft Aube de turbine avec joint d'étanchéité séparé
US9133720B2 (en) * 2007-12-28 2015-09-15 United Technologies Corporation Integrally bladed rotor with slotted outer rim
US9273563B2 (en) 2007-12-28 2016-03-01 United Technologies Corporation Integrally bladed rotor with slotted outer rim
US8206087B2 (en) 2008-04-11 2012-06-26 Siemens Energy, Inc. Sealing arrangement for turbine engine having ceramic components
GB2462810B (en) * 2008-08-18 2010-07-21 Rolls Royce Plc Sealing means
US8322977B2 (en) * 2009-07-22 2012-12-04 Siemens Energy, Inc. Seal structure for preventing leakage of gases across a gap between two components in a turbine engine
FR2998610B1 (fr) * 2012-11-29 2019-04-05 Safran Aircraft Engines Roue de redresseurs a plateformes espacees
US9926790B2 (en) * 2014-07-21 2018-03-27 Rolls-Royce Corporation Composite turbine components adapted for use with strip seals
US10107127B2 (en) * 2014-07-31 2018-10-23 United Technologies Corporation Gas turbine engine with axial compressor having improved air sealing
US9759079B2 (en) 2015-05-28 2017-09-12 Rolls-Royce Corporation Split line flow path seals
US10890078B1 (en) * 2017-06-12 2021-01-12 Technetics Group Llc Flexible seal assembly
EP3438410B1 (fr) 2017-08-01 2021-09-29 General Electric Company Système d'étanchéité pour machine rotative
US10718226B2 (en) 2017-11-21 2020-07-21 Rolls-Royce Corporation Ceramic matrix composite component assembly and seal
FR3092867B1 (fr) * 2019-02-19 2021-08-13 Safran Aircraft Engines Partie de turbomachine pour aeronef a languettes d’etancheite
CN113252246B (zh) * 2021-06-18 2021-11-05 中国科学院武汉岩土力学研究所 一种可回收的地下连续墙接缝处渗漏检测装置

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US5149250A (en) 1991-02-28 1992-09-22 General Electric Company Gas turbine vane assembly seal and support system
FR2691749B1 (fr) * 1992-05-27 1994-07-22 Snecma Dispositif d'etancheite entre des etages d'aubes et un tambour tournant notamment pour eviter les fuites autour des etages d'aubes de redresseur .
DE4241420C1 (de) * 1992-12-09 1993-11-25 Mtu Muenchen Gmbh Verfahren zur Herstellung von Bauteilen oder Substraten mit Verbundbeschichtungen und dessen Anwendung
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JP2000193093A (ja) * 1998-12-25 2000-07-14 Nichias Corp 三部材接合部のシ―ル構造

Also Published As

Publication number Publication date
DE59908238D1 (de) 2004-02-12
JP2000120401A (ja) 2000-04-25
EP0995881A3 (fr) 2002-03-13
US6312218B1 (en) 2001-11-06
EP0995881A2 (fr) 2000-04-26
JP4465067B2 (ja) 2010-05-19
DE19848103A1 (de) 2000-04-20

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