EP2302174A2 - Turbine à gaz avec un joint à labyrinthe de la virole - Google Patents

Turbine à gaz avec un joint à labyrinthe de la virole Download PDF

Info

Publication number
EP2302174A2
EP2302174A2 EP10007636A EP10007636A EP2302174A2 EP 2302174 A2 EP2302174 A2 EP 2302174A2 EP 10007636 A EP10007636 A EP 10007636A EP 10007636 A EP10007636 A EP 10007636A EP 2302174 A2 EP2302174 A2 EP 2302174A2
Authority
EP
European Patent Office
Prior art keywords
gas turbine
housing
turbine according
shroud
sealing rib
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Withdrawn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
EP10007636A
Other languages
German (de)
English (en)
Other versions
EP2302174A3 (fr
Inventor
Zbigniew Schabowski
Robert Benton
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2302174A2 publication Critical patent/EP2302174A2/fr
Publication of EP2302174A3 publication Critical patent/EP2302174A3/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator

Definitions

  • the invention relates to a gas turbine with a shroud labyrinth seal according to the features of the preamble of claim 1.
  • the invention relates to an axial turbine of a gas turbine, in which at least one rotor provided with blades is provided, which has on its outer periphery, connecting the blade tips, a cover strip formed from segments.
  • housing is to be understood according to the invention as meaning a non-rotating component which may also be formed as a tubular component which does not form a housing in the strict sense.
  • the component designated according to the invention as a housing can consist of an arrangement of components, a ring or a part of the actual turbine housing.
  • the turbine In a turbine of a gas turbine, work is taken from the gas flow exiting the combustion chamber to thereby generate a torque for driving a compressor.
  • the turbine has a number of stationary blades and at least one rotor provided with a blade row. The number of these components may vary according to the invention.
  • the rotor moves relative to the housing, wherein between the rotor and the housing, a gap is provided, which is required for free mobility of the rotor.
  • a gap is provided, which is required for free mobility of the rotor.
  • the leakage flow reduces the gas mass which flows through the rotor, so that the work taken becomes smaller.
  • the flow caused by the gap results in an impairment of the actual flow through the turbine, as it has different angles and different local velocities. This results in a mixture of the two streams and in a reduction of the aerodynamic efficiency.
  • the Leakage flow also leads to a deterioration of the flow of a subsequent stator blade row.
  • FIG. 3 and 4 show a schematic representation of a blade root 7, which is part of a rotor 9. At the respective blade root 7, a blade 2 is arranged. The radially outer end regions of the blades 2 are connected by means of a shroud 3, which is formed substantially annular and is composed for example of individual segments.
  • the shroud 3 is provided with a plurality of sealing ribs 5 extending substantially in the radial direction.
  • the Fig. 3 and 4 each show three such sealing ribs. 5
  • Fig. 3 a stepped housing contour is provided with housing stages 8, while according to Fig. 4 a conically widening housing cross-sectional shape (in the axial cross-section) is shown.
  • the Fig. 3 and 4 thus show a meridional section of the turbine rotor and the housing.
  • the annular ribs 5 may be purely radially aligned, it is also possible to tilt them in the axial direction, as in the Fig. 3 and 4 is shown. Furthermore, it is known from the prior art to provide varying numbers of such annular ribs 5.
  • the invention has for its object to provide a gas turbine with shroud labyrinth seal, which avoids the disadvantages of the prior art with a simple design and simple, cost-effective manufacturability and ensures an optimized seal.
  • At least one, at least over a part of the circumference substantially radially to the shroud extending sealing rib is formed on the housing, which extends at least partially into a space between the annular ribs.
  • the sealing rib which according to the invention can be designed as a closed axial ring or segmented in the circumferential direction, thus constitutes a flow barrier, which additionally impedes the leakage flow. Thus, the flow mass of the leakage flow is reduced.
  • the sealing ribs according to the invention can have a constant cross section or a varying cross section in the circumferential direction.
  • the cross section may be rectangular with sharp edges, but it is also possible to provide a rounded cross section or to create a further leakage flow barrier by special cross sectional design.
  • the cross section of the sealing ribs can furthermore be designed so that the sealing ribs are arranged inclined in the axial direction. It is possible to angle one or both sides, with respect to the axial direction, angularly.
  • the radially arranged end face can also be chamfered or straight. It is also possible to provide a stepped cross section or a parallelogram-like cross section.
  • the sealing ribs can either be formed integrally with the housing, but it is also possible to form them as a separate component and to connect to the housing, for example by ring segments or the like.
  • the invention is applicable both in conically smooth, widening housing cross-sections, as well as in stepped housing cross-sections (each based on an axial section view).
  • the leakage flow through the annular gap between the surface of the shroud and the housing is significantly hindered.
  • the accelerated after the overflow of the annular ribs, jet-like flow is significantly hindered by the impact on the sealing ribs according to the invention and deflected with respect to the flow direction.
  • kinetic energy of the leakage flow is destroyed, resulting in a reduced mass of the leakage flow.
  • the leakage air flowing past the sealing ribs is hindered when hitting the next sealing rib of the housing or shroud in the axial direction, whereby flow energy is also dissipated in this case.
  • Fig. 1 and 2 show, analogous to Fig. 3 and 4 , a housing 1, which may be provided with housing steps 8 ( Fig. 1 ) or with a smooth, conically widening surface.
  • Fig. 1 and 2 show in dashed line the flow through the gap between the shroud 3 and the surface of the housing first
  • sealing grooves 6 are arranged in the spaces between axially spaced annular ribs, which extend substantially in the radial direction. It is thus provided in each space a sealing rib 6.
  • This is according to the embodiments of the Fig. 1 and 2 provided with a rectangular cross-section. However, it is also possible to vary the cross section, both in the circumferential direction and deviating from the rectangular cross section.
  • the sealing ribs 6 are formed so that they hinder the flow, without coming into contact with the shroud 3 and / or the annular ribs 5. It is therefore not sealing elements, which form part of a squeal seal, but a defined distance between the sealing ribs 6 and the shroud 3 and / or the annular ribs 5 is provided.

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)
EP10007636.3A 2009-09-24 2010-07-22 Turbine à gaz avec un joint à labyrinthe de la virole Withdrawn EP2302174A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102009042857A DE102009042857A1 (de) 2009-09-24 2009-09-24 Gasturbine mit Deckband-Labyrinthdichtung

Publications (2)

Publication Number Publication Date
EP2302174A2 true EP2302174A2 (fr) 2011-03-30
EP2302174A3 EP2302174A3 (fr) 2014-01-22

Family

ID=42537784

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10007636.3A Withdrawn EP2302174A3 (fr) 2009-09-24 2010-07-22 Turbine à gaz avec un joint à labyrinthe de la virole

Country Status (3)

Country Link
US (1) US20110070074A1 (fr)
EP (1) EP2302174A3 (fr)
DE (1) DE102009042857A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9416671B2 (en) 2012-10-04 2016-08-16 General Electric Company Bimetallic turbine shroud and method of fabricating
EP2650476B1 (fr) * 2012-04-13 2020-10-07 General Electric Company Virole d'extrémité de pales de turbomachine avec configuration de carter parallèle
EP3822461A1 (fr) * 2019-11-15 2021-05-19 MTU Aero Engines AG Système d'étanchéité de turbomachine axiale

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5484990B2 (ja) * 2010-03-30 2014-05-07 三菱重工業株式会社 タービン
US20120195742A1 (en) * 2011-01-28 2012-08-02 Jain Sanjeev Kumar Turbine bucket for use in gas turbine engines and methods for fabricating the same
US8807927B2 (en) 2011-09-29 2014-08-19 General Electric Company Clearance flow control assembly having rail member
US9109455B2 (en) 2012-01-20 2015-08-18 General Electric Company Turbomachine blade tip shroud
US8623708B1 (en) * 2012-07-05 2014-01-07 Stats Chippac Ltd. Integrated circuit packaging system with grid-array mechanism and method of manufacture thereof
EP3060763B1 (fr) * 2013-10-21 2020-04-15 United Technologies Corporation Découragement d'écoulement dans un écart d'aubes de turbine tolérant aux incidents
JP6510915B2 (ja) * 2015-07-03 2019-05-08 株式会社神戸製鋼所 ラビリンスシール
US10626739B2 (en) * 2015-10-27 2020-04-21 Mitsubishi Heavy Industries, Ltd. Rotary machine
FR3055353B1 (fr) * 2016-08-25 2018-09-21 Safran Aircraft Engines Ensemble formant joint d'etancheite a labyrinthe pour une turbomachine comportant un abradable et des lechettes inclines
JP6706585B2 (ja) * 2017-02-23 2020-06-10 三菱重工業株式会社 軸流回転機械
JP6917162B2 (ja) 2017-02-28 2021-08-11 三菱パワー株式会社 動翼、ロータユニット、及び、回転機械
FR3065483B1 (fr) * 2017-04-24 2020-08-07 Safran Aircraft Engines Dispositif d'etancheite entre rotor et stator de turbomachine
US11053807B2 (en) * 2017-06-12 2021-07-06 Mitsubishi Power, Ltd. Axial flow rotating machine
US20190072185A1 (en) 2017-09-07 2019-03-07 Kabushiki Kaisha Kobe Seiko Sho (Kobe Steel, Ltd.) Labyrinth seal and labyrinth seal structure
US10533610B1 (en) * 2018-05-01 2020-01-14 Florida Turbine Technologies, Inc. Gas turbine engine fan stage with bearing cooling
US11293295B2 (en) 2019-09-13 2022-04-05 Pratt & Whitney Canada Corp. Labyrinth seal with angled fins
CN113685234B (zh) * 2021-08-31 2022-08-09 北京航空航天大学 一种基于对冲原理的篦齿封严装置

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE533093A (fr) * 1953-11-12 1954-11-30
US4370094A (en) * 1974-03-21 1983-01-25 Maschinenfabrik Augsburg-Nurnberg Aktiengesellschaft Method of and device for avoiding rotor instability to enhance dynamic power limit of turbines and compressors
DE2413655C3 (de) * 1974-03-21 1978-05-03 Maschinenfabrik Augsburg-Nuernberg Ag, 8500 Nuernberg Einrichtung zum dynamischen Stabilisieren des Läufers einer Gas- oder Dampfturbine
CH666326A5 (en) * 1984-09-19 1988-07-15 Bbc Brown Boveri & Cie Turbine rotor blades with shroud plates at outer ends - have adjacent plates connected via damping circumferential wire through bores in plates
US5735667A (en) * 1996-05-06 1998-04-07 Innovative Technology, L.L.C. Method and apparatus for minimizing leakage in turbine seals
EP0903468B1 (fr) * 1997-09-19 2003-08-20 ALSTOM (Switzerland) Ltd Dispositif d'étanchéité pour un interstice
EP1515000B1 (fr) * 2003-09-09 2016-03-09 Alstom Technology Ltd Aubage d'une turbomachine avec un carenage contouré
US6926495B2 (en) * 2003-09-12 2005-08-09 Siemens Westinghouse Power Corporation Turbine blade tip clearance control device
US7255531B2 (en) * 2003-12-17 2007-08-14 Watson Cogeneration Company Gas turbine tip shroud rails
EP1557536A1 (fr) * 2004-01-22 2005-07-27 Siemens Aktiengesellschaft Turbine à gaz avec rotor axialement déplaçable
EP1905949A1 (fr) * 2006-09-20 2008-04-02 Siemens Aktiengesellschaft Refroidissement d'un élément d'une turbine à vapeur
US7686568B2 (en) * 2006-09-22 2010-03-30 General Electric Company Methods and apparatus for fabricating turbine engines
JP2008169705A (ja) * 2007-01-09 2008-07-24 Toshiba Corp 蒸気タービン
US8167547B2 (en) * 2007-03-05 2012-05-01 United Technologies Corporation Gas turbine engine with canted pocket and canted knife edge seal
JP4668976B2 (ja) * 2007-12-04 2011-04-13 株式会社日立製作所 蒸気タービンのシール構造

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2650476B1 (fr) * 2012-04-13 2020-10-07 General Electric Company Virole d'extrémité de pales de turbomachine avec configuration de carter parallèle
US9416671B2 (en) 2012-10-04 2016-08-16 General Electric Company Bimetallic turbine shroud and method of fabricating
EP3822461A1 (fr) * 2019-11-15 2021-05-19 MTU Aero Engines AG Système d'étanchéité de turbomachine axiale

Also Published As

Publication number Publication date
EP2302174A3 (fr) 2014-01-22
US20110070074A1 (en) 2011-03-24
DE102009042857A1 (de) 2011-03-31

Similar Documents

Publication Publication Date Title
EP2302174A2 (fr) Turbine à gaz avec un joint à labyrinthe de la virole
EP2123860B1 (fr) Redresseur de tourbillons combiné
EP3056813B1 (fr) Joint pour un interstice marginal entre les bardeaux d'effusion d'une chambre de combustion de turbines a gaz
EP0924386B1 (fr) Méthode et dispositif d'étanchéité pour isoler l'espace entre un rotor et un stator
DE69203705T2 (de) Stator zur Einführung von Luft in das Innere einer Turbomaschine und Verfahren zum Montieren einer Schaufel dieses Stators.
EP2250347B1 (fr) Compresseur axial avec un dispositif pour rediriger un courant de fuite
EP2647795B1 (fr) Système d'étanchéité pour turbomachine
EP2824282A1 (fr) Turbine à gaz avec système de refroidissement de turbine à haute pression
EP3051068A1 (fr) Bague d'aube directrice pour une turbomachine et procédé de fabrication additive
DE3148985C2 (de) Rotorbaugruppe
DE102015219556A1 (de) Diffusor für Radialverdichter, Radialverdichter und Turbomaschine mit Radialverdichter
EP2132414A1 (fr) Agencement en feuillure
EP3574188B1 (fr) Procédé permettant de fermer de manière étanche un interstice annulaire dans une turbine ainsi que turbine
DE102007054926A1 (de) Schutzvorrichtung für Turbinendichtungen
EP3336313A1 (fr) Ensemble d'aube mobile pour turbines d'une turbine turbine à gaz et procédé de fourniture d'air sceau dans un ensemble d'aube mobile pour turbines
EP2092164B1 (fr) Turbo machine, en particulier turbine à gaz
EP2647796A1 (fr) Système d'étanchéité pour turbomachine
EP3628030B1 (fr) Méthode de maintenance d'une turbomachine
DE102010031213A1 (de) Rotor einer Turbomaschine
EP3312388B1 (fr) Pièce de rotor, compresseur, turbine et procédé de fabrication associés
EP2725203B1 (fr) Conduite d'air froid dans une structure de boîtier d'une turbomachine
EP3194725B1 (fr) Rotor, compresseur axial, procédé de montage
EP1443182A2 (fr) Dispositif de refroidissement
DE102019211669A1 (de) Dichtungsvorrichtung und turbomaschine
EP2194233B1 (fr) Diviseur de flux pour un turboréacteur à double flux

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME RS

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME RS

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 11/08 20060101AFI20131216BHEP

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20140723