EP2092164B1 - Strömungsmaschine, insbesondere gasturbine - Google Patents

Strömungsmaschine, insbesondere gasturbine Download PDF

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Publication number
EP2092164B1
EP2092164B1 EP07847789A EP07847789A EP2092164B1 EP 2092164 B1 EP2092164 B1 EP 2092164B1 EP 07847789 A EP07847789 A EP 07847789A EP 07847789 A EP07847789 A EP 07847789A EP 2092164 B1 EP2092164 B1 EP 2092164B1
Authority
EP
European Patent Office
Prior art keywords
rotor
blade
heat shield
stator
adjacent
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.)
Not-in-force
Application number
EP07847789A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2092164A1 (de
Inventor
Maxim Konter
Alexander Khanin
Alexander Burmistrov
Sergey Vorontsov
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.)
GE Vernova GmbH
Original Assignee
Alstom Technology 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 Technology AG filed Critical Alstom Technology AG
Publication of EP2092164A1 publication Critical patent/EP2092164A1/de
Application granted granted Critical
Publication of EP2092164B1 publication Critical patent/EP2092164B1/de
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades

Definitions

  • the present invention relates to a rotating turbomachine, in particular a gas turbine.
  • Rotary turbomachines usually have a rotor having at least two blade rows with multiple blades and at least one rotor heat shield with a plurality of shield elements, wherein the respective rotor heat shield is arranged axially between two adjacent blade rows. Furthermore, such a turbomachine usually comprises a stator which has at least one row of guide vanes arranged axially between two adjacent blade rows and having a plurality of guide vanes.
  • a rotating turbomachine with a rotor and a stator known.
  • a protective shield radial seal is formed in the circumferential direction between two adjacent shield elements, which separates the gas path from the rotor.
  • the shield elements and the blades are coordinated so that the protective shield radially passes without interruption in the blade radial seals of the two axially adjacent blades, in such a way that from one blade on the shield member to the other blade a continuous radial seal is formed.
  • the radial seals can be formed by means of blade grooves and protective shield grooves.
  • turbomachinery with radial seals are from the CH 525419 A , from the EP 1 371 814 A and from the US 3,551,068 A known.
  • the invention aims to remedy this situation.
  • the invention as characterized in the claims, deals with the problem, for a turbomachine of the type mentioned, to provide an improved embodiment, which is characterized in particular by an increased efficiency.
  • the invention is based on the general idea of combining an axial seal, which is formed by the interaction of a stator seal structure with a rotor-seal structure, with a radial seal passing through from one blade via the shield element to the other blade. In this way, leaks in the axial direction and in the radial direction can be reduced, which increases the efficiency of the turbomachine or its efficiency.
  • the combination of the axial seal in the region of the rotor heat shield with the continuous in the axial direction over the rotor heat shield, so uninterrupted or gapless radial seal plays together to increase efficiency.
  • the continuous radial seal is realized in the turbomachine according to the invention in that the shield elements and the blades are coordinated so that the trained in the shield elements Schutrschildradialichtung uninterrupted merges into the trained in the blades blade radial seals.
  • radial seals are realized by means of sealing elements, which are arranged in the shield shield elements in protective shield grooves and in the region of the blades in blade grooves.
  • an axial gap axially formed between the shield member and the respective blade can be effectively covered by the respective seal member in an area circumferentially between adjacent shield members and circumferentially between adjacent blades, respectively, which has the sealing effect the radial seal thus formed significantly improved.
  • adjacent sealing elements abut each other axially between the axial longitudinal ends of the blade grooves and / or between the axial longitudinal ends of the protective shield grooves.
  • the sealing effect of the radial seal can be increased, which improves the efficiency of the turbomachine.
  • the shield elements between their axial ends each have a radially inwardly recessed recess in which the rotor seal structure is arranged.
  • said recess is dimensioned so that the axial seal is formed within this recess and is arranged offset radially inwardly relative to the blade radial seals of the adjacent blades.
  • the single FIGURE shows a simplified longitudinal section through a portion of a turbomachine.
  • the turbomachine 1 which is preferably a gas turbine, which may, however, also be a compressor or a steam turbine, rotates the rotor 2 about a rotor axis 4, which simultaneously defines the axial direction of the turbomachine 1.
  • the rotor 2 has at least two blade rows 5, each having a plurality of circumferentially adjacent blades 6.
  • the rotor 2 has at least one rotor heat shield 7, which is arranged in each case axially between two adjacent rotor blade rows 5.
  • the stator 3 may have a plurality of stator blade rows 8, of which at least one is arranged axially between two adjacent blade rows 5.
  • Each vane row 8 has a plurality of circumferentially adjacent vanes 9.
  • the at least one vane row 8 arranged axially between two adjacent rows of rotor blades 5 is regularly meant.
  • the guide vanes 9 of at least one of these guide blade rows 8 have radially inward a stator seal structure 10, which can be designed to be closed in the circumferential direction.
  • a stator seal structure 10 which can be designed to be closed in the circumferential direction.
  • each vane 9 radially inwardly at its blade tip a flat, in the circumferential direction and axially extending platform 11, which may be configured in the manner of a shroud.
  • the stator seal structure 10 is disposed on these vane platforms 11.
  • the respective rotor heat shield 7 generally includes a plurality of circumferentially adjacent shield members 12 which form the respective rotor heat shield 7 in the manner of ring segments.
  • the individual shield elements 12 have radially outside a rotor seal structure 13 which extends closed in the circumferential direction.
  • the rotor-seal structure 13 and the stator-seal structure 10 are arranged radially adjacent thereto and cooperate to form an axial seal 14.
  • a blade radial seal 15 is formed on each side between two adjacent moving blades 6 of the same blade row 5, while on the other hand, a respective protective shield radial seal 16 is formed between two adjacent shielding elements 12.
  • Both the respective blade radial seal 15 and the respective protective shield radial seal 16 separate in the radial direction a gas path 17, the turbomachine 1 from the rotor 2 and from a cooling gas path 18 which is formed radially between the rotor 2 and the respective radial seal 15, 16.
  • the respective working gas such as a hot gas
  • a corresponding gas flow is symbolized by arrows 19.
  • the blades 6 and the vanes 9 each extend through the gas path 17.
  • a cooling gas flow which is indicated by arrows 20.
  • the shield elements 12 and the blades 6 of the rotor heat shield 7 adjacent blade rows 5 are so each other matched so that the shield radial seal 16 passes without interruption both in the upstream blade radial seal 15 and in the downstream blade radial seal 15.
  • This uninterrupted transition between the shield radial seal 16 and the two blade radial seals 15 is realized so that it can form a radial seal 21, which in the longitudinal direction of the one blade 6 via the respective shield member 12 to the other blade 6 quasi seamless or continuous is designed. It is noteworthy that both in an upstream transition 22 and at a downstream transition 23 between the shield element 12 and the respective blade 6, a continuous radial seal 21 can be realized.
  • the respective blade radial seal 15 comprises in the region of blade roots 24 of the circumferentially adjacent blades 6 each a circumferentially open blade groove 25.
  • the two blade grooves 25 of the respective blade radial seal 15 are aligned with their open sides facing each other, so that in these blade grooves 25 a plate-shaped or band-shaped sealing element 26 can be inserted.
  • the protective shield radial seal 16 is constructed in a corresponding manner and, in regions 27 adjoining the rotor-seal structure 13, has in each case one protective shield groove 28 which is open in the circumferential direction in the case of the protective shield elements 12 adjacent in the circumferential direction.
  • the protective shield grooves 28 of the two shielding elements 12 adjacent to one another in the circumferential direction are aligned with one another in the circumferential direction, so that a plate-shaped or band-shaped sealing element 26 can likewise be inserted into the protective shield grooves 28.
  • the shield grooves 28 and the blade grooves 25 are suitably matched to one another so that in the transition regions 22, 23 axial longitudinal ends 29 of the shield grooves 28 axially aligned axially adjacent axial longitudinal ends 30 of the blade grooves 25.
  • This makes it possible to arrange in the transition regions 22, 23 a common sealing element 26 or in each case a sealing element 26, specifically in such a way that it extends axially from the protective shield grooves 28 into the blade grooves 25 or that it extends from the blade grooves 25 Blades 6 of a blade row 5 extends axially into the shield grooves 28 inside.
  • sealing element 26 which extends in the respective grooves 25, 28 from one blade row 5 on the rotor heat shield 7 to the other blade row 5.
  • a plurality of sealing elements 26 may be provided, in particular adjacent sealing elements 26 axially abutting one another between the axial longitudinal ends 29 of the protective shield grooves 28 and / or between the axial longitudinal ends 30 of the respective blade grooves 25.
  • comparatively small sealing elements 26, which are arranged only in the respective transitional region 22 or 23 for bridging the annular axial gap there, extending on the one hand into the protective shield grooves 28 and on the other hand into the blade grooves 25.
  • the shield elements 12 may according to the embodiment shown here between their axial ends, ie between the transition regions 22, 23 have a radially inwardly recessed recess 31.
  • the rotor seal structure 13 is arranged.
  • the guide vanes 9 are here dimensioned so that the stator seal structure 10 is disposed within this recess 31.
  • the recess 31 may be dimensioned so that the formed by the interaction of the rotor seal structure 13 with the stator seal structure 10 axial seal 14 is formed within the recess 31.
  • the axial seal 14 is arranged offset radially inwardly relative to the blade radial seals 15 of the adjacent blades 6. As a result, the axial seal 14 is located radially outside the gas flow 19 in the gas path 17 and in particular in a dead water region of the gas flow 19.
  • the stator seal structure 10 may be configured so as to be grindable.
  • the stator-seal structure 10 may be designed as a honeycomb structure 33 with radially oriented honeycombs for this purpose.
  • the rotor seal structure 13 is designed einschleifend.
  • the rotor-seal structure 13 is formed by at least one blade-shaped annular web 32. In the example shown, two such annular webs 32 are provided, which are arranged spaced apart in the axial direction.
  • the rotor-seal structure 13 can be looped into the stator-seal structure 10, that is to say the respective annular rib 32 penetrates into the honeycomb structure 33.
  • stator seal structure 10 and the rotor seal structure 13 cooperate to form the axial seal 14 in the manner of a labyrinth seal.
  • stator seal structure 10 more, z. B. have two annular axial sections 34 which are offset from an adjacent thereto, here middle annular axial section 35 radially outward.
  • the rotor-seal structure 13 then has several, here two radially outwardly projecting annular webs 32, which are each arranged in the region of one of the radially outwardly offset radial sections 34.

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)
  • Low-Molecular Organic Synthesis Reactions Using Catalysts (AREA)
EP07847789A 2006-12-19 2007-12-04 Strömungsmaschine, insbesondere gasturbine Not-in-force EP2092164B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH20582006 2006-12-19
PCT/EP2007/063288 WO2008074633A1 (de) 2006-12-19 2007-12-04 Strömungsmaschine, insbesondere gasturbine

Publications (2)

Publication Number Publication Date
EP2092164A1 EP2092164A1 (de) 2009-08-26
EP2092164B1 true EP2092164B1 (de) 2010-10-06

Family

ID=37616891

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07847789A Not-in-force EP2092164B1 (de) 2006-12-19 2007-12-04 Strömungsmaschine, insbesondere gasturbine

Country Status (9)

Country Link
US (1) US8052382B2 (enrdf_load_stackoverflow)
EP (1) EP2092164B1 (enrdf_load_stackoverflow)
JP (1) JP5027245B2 (enrdf_load_stackoverflow)
KR (1) KR101426715B1 (enrdf_load_stackoverflow)
AT (1) ATE483891T1 (enrdf_load_stackoverflow)
CA (1) CA2673079C (enrdf_load_stackoverflow)
DE (1) DE502007005296D1 (enrdf_load_stackoverflow)
MX (1) MX2009006599A (enrdf_load_stackoverflow)
WO (1) WO2008074633A1 (enrdf_load_stackoverflow)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2673079C (en) 2006-12-19 2015-11-24 Alstom Technology Ltd. Turbomachine, especially gas turbine
RU2539404C2 (ru) * 2010-11-29 2015-01-20 Альстом Текнолоджи Лтд Осевая газовая турбина
US9341070B2 (en) 2012-05-30 2016-05-17 United Technologies Corporation Shield slot on side of load slot in gas turbine engine rotor
US9771818B2 (en) 2012-12-29 2017-09-26 United Technologies Corporation Seals for a circumferential stop ring in a turbine exhaust case
WO2014189564A2 (en) * 2013-03-06 2014-11-27 United Technologies Corporation Pretrenched rotor for gas turbine engine
US9441639B2 (en) 2013-05-13 2016-09-13 General Electric Company Compressor rotor heat shield
EP2832952A1 (en) 2013-07-31 2015-02-04 ALSTOM Technology Ltd Turbine blade and turbine with improved sealing
KR101584156B1 (ko) * 2014-12-22 2016-01-22 주식회사 포스코 가스 터빈용 씨일 및 이를 구비하는 씨일 조립체
CN115199343A (zh) * 2022-06-25 2022-10-18 中科航星科技有限公司 一种适用于转静子轴向封严的接触式封严组件

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3551068A (en) 1968-10-25 1970-12-29 Westinghouse Electric Corp Rotor structure for an axial flow machine
CH525419A (de) 1970-12-18 1972-07-15 Bbc Sulzer Turbomaschinen Dichtungsvorrichtung für Turbomaschinen
US5293717A (en) * 1992-07-28 1994-03-15 United Technologies Corporation Method for removal of abradable material from gas turbine engine airseals
GB2307279B (en) * 1995-11-14 1999-11-17 Rolls Royce Plc A gas turbine engine
DE19654471B4 (de) 1996-12-27 2006-05-24 Alstom Rotor einer Strömungsmaschine
DE19914227B4 (de) * 1999-03-29 2007-05-10 Alstom Wärmeschutzvorrichtung in Gasturbinen
JP3481596B2 (ja) * 2001-02-14 2003-12-22 株式会社日立製作所 ガスタービン
EP1371814A1 (en) 2002-06-11 2003-12-17 ALSTOM (Switzerland) Ltd Sealing arrangement for a rotor of a turbomachine
RU2297566C2 (ru) * 2002-07-03 2007-04-20 Альстом Текнолоджи Лтд Щелевое уплотнение для герметизации щели между двумя соседними конструкционными элементами
CA2673079C (en) 2006-12-19 2015-11-24 Alstom Technology Ltd. Turbomachine, especially gas turbine

Also Published As

Publication number Publication date
KR20090091190A (ko) 2009-08-26
JP2010513783A (ja) 2010-04-30
MX2009006599A (es) 2009-07-02
US20090274552A1 (en) 2009-11-05
WO2008074633A1 (de) 2008-06-26
EP2092164A1 (de) 2009-08-26
CA2673079A1 (en) 2008-06-26
JP5027245B2 (ja) 2012-09-19
CA2673079C (en) 2015-11-24
KR101426715B1 (ko) 2014-08-06
ATE483891T1 (de) 2010-10-15
US8052382B2 (en) 2011-11-08
DE502007005296D1 (de) 2010-11-18

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