EP1898054A1 - Turbine à gaz - Google Patents

Turbine à gaz Download PDF

Info

Publication number: EP1898054A1
Authority: EP; European Patent Office
Prior art keywords: sealing; stator; rotor; fin; fins
Prior art date: 2006-08-25
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.): Granted

Application number

EP07114082A

Other languages

German (de)

English (en)

Other versions

EP1898054B1 (fr

Inventor

Ulrich Steiger

Sven Olmes

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.)

Ansaldo Energia IP UK Ltd

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.)

2006-08-25

Filing date

2007-08-09

Publication date

2008-03-12

2007-08-09 Application filed by Alstom Technology AG filed Critical Alstom Technology AG

2008-03-12 Publication of EP1898054A1 publication Critical patent/EP1898054A1/fr

2018-05-30 Application granted granted Critical

2018-05-30 Publication of EP1898054B1 publication Critical patent/EP1898054B1/fr

Status Active legal-status Critical Current

2027-08-09 Anticipated expiration legal-status Critical

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
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
- 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
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/18—Two-dimensional patterned
- F05D2250/182—Two-dimensional patterned crenellated, notched
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/28—Three-dimensional patterned
- F05D2250/283—Three-dimensional patterned honeycomb
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/30—Arrangement of components
- F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
- F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other

Definitions

the invention relates to a turbomachine, in particular a gas turbine, having a rotor and a stator and an axial sealing device arranged between the rotor and the stator, according to the preamble of claim 1.
turbomachines In order to be able to produce the highest possible efficiency in modern turbomachines, in particular in gas turbines or compressors, it is desirable to effectively seal the turbomachine and thereby avoid a loss of the turbomachine driving hot gases as well as a collapse of cooling gases, the temperature within the Reduce flow machine and thereby adversely affect the efficiency.
a particular problem with the sealing of such turbomachines occurs in particular when the sealing device is arranged between relatively moving component components. This is for example the case with a sealing device which is arranged between a rotating rotor and a stator fixed relative thereto. Additional relative movements of the opposing sealing device components occur at the transition from the thermally cold resting state to the warm operating state due to the thermal expansion and the mechanical load at different material properties of the supporting parts.
a stator-side radially stepped sealing contour is provided in the case of such sealing devices, which has regions that project back and forth in the direction of the rotor.
a plurality of sealing fins projecting in the direction of the stator are arranged, which respectively engage in adjacent, recessed regions of the stator-side sealing contour.
a poor sealing property of the sealing device also results in a hot gas breakdown in the sealing region, which accelerates an oxidation process and thus also corrosion.
the invention deals with the problem of providing an improved or at least another embodiment for a turbomachine of the generic type, which is characterized in particular by an improved sealing effect of an associated sealing device.
the invention is based on the general idea, in a turbomachine with at least one arranged between a rotor and a stator axial sealing device in addition to the already commonly existing sealing fins so-called. Additional fins provide, which increase a labyrinth effect of the sealing device and thereby improve the sealing effect of the sealing device.
the sealing device on the stator side has a radially stepped sealing contour with regions projecting back and forth in the direction of the rotor. In each adjacent, recessed areas of the stator-side sealing contour engage sealing fins arranged on the rotor side and projecting in the direction of the stator, whereby a certain labyrinth seal is already provided in conventional sealing devices.
At least one additional fin projecting in the direction of the stator is now provided on the rotor side, which lies opposite a projecting region of the stator-side sealing contour and is positioned between two adjacent fins arranged on the rotor side.
the additional fins can in the same way as the sealing fins be formed and, for example, consist of erosive material, while the opposite sealing contour consists oftechnologytragendem material, so that optionally the additional fins may possibly dig into a surface of the sealing contour.
both the additional fins and the sealing fins abut against the opposite regions of the sealing contour.
Both the additional fins and the sealing fins are formed as continuous contours in the circumferential direction of the rotor, whereby they receive the shape of a projecting collar of the rotor.
the stator-side sealing contour is also constructed substantially uniformly in the circumferential direction, so that the regions of the sealing contour projecting radially back and forth in the axial longitudinal section are annular.
the arrangement of at least one additional fin substantially improves the labyrinth effect and thus the sealing effect of the sealing device.
At least one additional fin and / or one sealing fin are arranged radially and axially inclined on the rotor or on a rotor-side heat shield.
An inclination in the direction opposite to the main flow direction of the sealing fin or the additional fin amplifies a flow upstream and downstream of the respective fin located Stauströmung, or a so-called. Totwasser Scheme, which counteracts the flow and thereby improves the sealing effect of the sealing device.
the inclined fins deform radially outward due to the centrifugal forces and thereby create the opposite sealing contour.
a burying of the fins can take place in the honeycomb-shaped sealing structure, wherein a removal of material should take place exclusively in the region of the sealing contour.
the sealing fins and / or the additional fin in the circumferential direction each one wedge-shaped cross-sectional profile.
a wedge-shaped cross-sectional profile provides a wide connection base to the rotor and thereby a reliable connection of the fin with the rotor and at the same time a weight-optimized fin, as it tapers radially outward.
This is particularly favorable for attacking centrifugal forces, since a cross-sectionally uniform fin would produce significantly greater centrifugal forces at its free end, which causes a significantly greater load on the connection region of the fin to the rotor or on a heat shield of the rotor.
a turbomachine in particular a gas turbine or a compressor, has a stator 2 and a rotor 3.
the stator 2 may be formed, for example, as a guide blade 4.
a blade 5 can be arranged in the usual manner.
at least one sealing device 6 is arranged between the stator 2 and the rotor 3. The sealing device 6 extends in the axial direction of the turbomachine 1.
the sealing device 6 On the stator side, the sealing device 6 has a honeycomb-like and radially stepped sealing contour 8 with regions 9 and 10 projecting in the direction of the rotor 3 (see also FIG.).
a plurality of sealing fins 11 projecting in the direction of the stator 2 are arranged, which respectively engage in adjacent, recessed regions 10 of the stator-side sealing contour 8.
at least one additional fin 12 projecting in the direction of the stator 2 is additionally provided on the rotor side, which is positioned between two adjacent sealing fins 11 arranged on the rotor side and faces a projecting region 9 of the stator-side sealing contour 8.
so-called additional fins 12 are additionally arranged which abut against the projecting regions 9 of the sealing contour 8 or even dig into them.
Both the sealing fins 11 and the additional fins 12 are made of a wear-resistant compared to the sealing contour 8 material, so at a Contact between the fins 11, 12 and the sealing contour 8, a removal of the sealing contour 8 takes place and the fins 11, 12 dig into the sealing contour 8, whereby the sealing effect of the sealing device 6 is additionally improved.
At least one additional fin 12 and / or one sealing fin 11 are arranged radially and axially inclined on the rotor 3 or on a heat shield 13 of the rotor 3.
a degree of inclination of the at least one additional fin 12 or the at least one sealing fin 11 is approximately 25 ° -35 ° with respect to a radial perpendicular to the axis of the turbomachine 1.
the inclination of the sealing fins 11 and the additional fins 12 takes place in opposite to the main flow 7a Direction, whereby upstream and / or downstream of the respective fin 11, 12 can form a so-called.
Stauströmung which is also referred to as dead water area, and which additionally improves the sealing effect of the sealing device 6.
the reference character 7b designates the leakage flow between the stator 2 and the rotor 3.
FIGS. 2a to e Different embodiments of the sealing device 6 are shown in FIGS. 2a to e, the sealing devices 6 according to FIGS. 2a to d having a constant radial height over their entire axial extent, while a radial height of the sealing device 6 according to FIG. 2e changed in the axial direction of the turbomachine 1.
sealing devices 6 are particularly suitable for cases in which the axial relative movement is greater than the radial. For this reason, all the sealing devices 6 according to FIGS. 1 and 2 have in common that the recessed areas 10 of the sealing contour 8 have a greater axial longitudinal extent than the projecting portions 9 of the sealing contour 8. In addition, an axial distance between two forward or recessed stator-side areas 9 or 10 about twice as large as a radial height of the sealing fin 11th
sealing devices 6 according to FIGS. 1 and 2 have in common that at least the sealing fins 11 each have a wedge-shaped cross-sectional profile in the circumferential direction and thereby taper starting from their rotor-side connection as far as a free end.
This offers the advantage that a connection area on the rotor side is stronger and therefore more load-bearing, while the free end of the sealing fin 11 is significantly lighter and thus causes lower centrifugal forces or centrifugal forces.
the stator-side, recessed portion 10 preferably has an axial longitudinal extent of about two to three times the height h of the sealing fin 11 shown in longitudinal section, while a stator Weger, projecting portion 9 an axial longitudinal extent of about 1 to 2.5 times the Height h, that is, has a width b shown in longitudinal section of 1 to 2.5 times h.
a radial height of the sealing fin 11 is approximately 2 to 4 times greater than a radial height of the auxiliary fin 12.
a last projecting region 9 ' is significantly narrower, ie formed with a significantly smaller axial longitudinal extent, while it is completely missing according to FIG. 2b.
all the sealing contours according to FIGS. 1 and 2 have in common that the protruding or recessed regions 9 and 10 have a rectangular, stepped cross-sectional shape, wherein it is also intended that differently stepped or corrugated cross-sectional shapes should be enclosed by the invention.
combinations of sealing fins 11 and additional fins 12 optimized with respect to the sealing effect can be used, wherein the sealing fins 1 and / or the additional fins can preferably be inclined opposite to the main flow direction 7a.

Landscapes

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

EP07114082.6A 2006-08-25 2007-08-09 Turbine a gaz Active EP1898054B1 (fr)

Applications Claiming Priority (1)

Application Number	Priority Date	Filing Date	Title
CH13592006		2006-08-25

Publications (2)

Publication Number	Publication Date
EP1898054A1 true EP1898054A1 (fr)	2008-03-12
EP1898054B1 EP1898054B1 (fr)	2018-05-30

Family

ID=37441281

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
EP07114082.6A Active EP1898054B1 (fr)	2006-08-25	2007-08-09	Turbine a gaz

Country Status (2)

Country	Link
US (1)	US8182211B2 (fr)
EP (1)	EP1898054B1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP3318724A1 (fr) *	2016-11-04	2018-05-09	Siemens Aktiengesellschaft	Segment d'étanchéité d'un rotor et rotor

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
US8376697B2 (en) *	2008-09-25	2013-02-19	Siemens Energy, Inc.	Gas turbine sealing apparatus
US8221062B2 (en) *	2009-01-14	2012-07-17	General Electric Company	Device and system for reducing secondary air flow in a gas turbine
US8561997B2 (en) *	2010-01-05	2013-10-22	General Electric Company	Adverse pressure gradient seal mechanism
US8845284B2 (en)	2010-07-02	2014-09-30	General Electric Company	Apparatus and system for sealing a turbine rotor
US8434766B2 (en) *	2010-08-18	2013-05-07	General Electric Company	Turbine engine seals
GB2492546A (en)	2011-07-04	2013-01-09	Alstom Technology Ltd	A labyrinth seal for an axial fluid flow turbomachine
US20130186103A1 (en) *	2012-01-20	2013-07-25	General Electric Company	Near flow path seal for a turbomachine
US8864453B2 (en)	2012-01-20	2014-10-21	General Electric Company	Near flow path seal for a turbomachine
US9080456B2 (en)	2012-01-20	2015-07-14	General Electric Company	Near flow path seal with axially flexible arms
JP2014020509A (ja) *	2012-07-20	2014-02-03	Toshiba Corp	シール装置、軸流タービン、および発電プラント
US10036278B2 (en) *	2014-04-11	2018-07-31	United Technologies Corporation	High pressure compressor thermal shield apparatus and system
JP6601677B2 (ja) *	2016-02-16	2019-11-06	三菱日立パワーシステムズ株式会社	シール装置及び回転機械
CN112671124B (zh) *	2020-12-26	2023-01-13	山东双华易驱智能制造研究院有限公司	一种电机内定子和电机

Citations (5)

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DE668667C (de) *		1938-12-08	Oerlikon Maschf	Vorrichtung zur Verminderung der Dampfverluste bei Labyrinthdichtungen fuer umlaufende Wellen
DE3940607A1 (de) *	1988-12-14	1990-06-21	Gen Electric	Labyrinth-dichtungssystem
EP0799973A1 (fr) *	1996-04-01	1997-10-08	Asea Brown Boveri Ag	Contour de paroi pour une turbomachine axiale
EP1079070A2 (fr) *	1999-08-26	2001-02-28	Asea Brown Boveri Ag	Bouclier thermique pour un rotor de turbine
DE102004026503A1 (de) *	2003-05-29	2004-12-16	General Electric Co.	Düsenzwischenstufendichtung für Dampfturbinen

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US1708044A (en) *	1923-09-12	1929-04-09	Westinghouse Electric & Mfg Co	Labyrinth-gland packing
US3251601A (en) *	1963-03-20	1966-05-17	Gen Motors Corp	Labyrinth seal
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US5961279A (en) *	1996-05-31	1999-10-05	Atlantic Richfield Company	Turbine power plant having minimal-contact brush seal augmented labyrinth seal
JP3477347B2 (ja) *	1997-07-30	2003-12-10	三菱重工業株式会社	ガスタービン段間部シール装置

2007
- 2007-08-09 EP EP07114082.6A patent/EP1898054B1/fr active Active
- 2007-08-20 US US11/841,333 patent/US8182211B2/en not_active Expired - Fee Related

Patent Citations (5)

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Publication number	Priority date	Publication date	Assignee	Title
DE668667C (de) *		1938-12-08	Oerlikon Maschf	Vorrichtung zur Verminderung der Dampfverluste bei Labyrinthdichtungen fuer umlaufende Wellen
DE3940607A1 (de) *	1988-12-14	1990-06-21	Gen Electric	Labyrinth-dichtungssystem
EP0799973A1 (fr) *	1996-04-01	1997-10-08	Asea Brown Boveri Ag	Contour de paroi pour une turbomachine axiale
EP1079070A2 (fr) *	1999-08-26	2001-02-28	Asea Brown Boveri Ag	Bouclier thermique pour un rotor de turbine
DE102004026503A1 (de) *	2003-05-29	2004-12-16	General Electric Co.	Düsenzwischenstufendichtung für Dampfturbinen

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP3318724A1 (fr) *	2016-11-04	2018-05-09	Siemens Aktiengesellschaft	Segment d'étanchéité d'un rotor et rotor
WO2018082907A1 (fr) *	2016-11-04	2018-05-11	Siemens Aktiengesellschaft	Segment étanche d'un rotor et rotor

Also Published As

Publication number	Publication date
US8182211B2 (en)	2012-05-22
US20080050233A1 (en)	2008-02-28
EP1898054B1 (fr)	2018-05-30

Publication	Publication Date	Title
EP1898054B1 (fr)	2018-05-30	Turbine a gaz
EP1320662B1 (fr)	2005-11-30	Systeme de garniture d'etancheite
DE102011055150B4 (de)	2024-07-18	Turbinenschaufelanordnung
DE10210866C5 (de)	2008-04-10	Leitschaufelbefestigung in einem Strömungskanal einer Fluggasturbine
DE69105837T2 (de)	1995-04-27	Gekühlte Turbinenschaufel.
EP2320030B1 (fr)	2012-12-19	Rotor et aube de rotor pour une turbomachine axiale
DE112016003244T5 (de)	2018-04-12	Abdeckung für Axialgebläseanordnung
EP1293644A1 (fr)	2003-03-19	Support pour aubes statoriques et segment d'accumulation de chaleur
EP2478186B1 (fr)	2015-07-29	Rotor de turbomachine
EP3051068A1 (fr)	2016-08-03	Bague d'aube directrice pour une turbomachine et procédé de fabrication additive
DE102014119693B4 (de)	2024-03-07	Turbinenschaufel mit hohlem schaufelblatt mit inneren rippen und kühlkanälen
CH707459A2 (de)	2014-07-15	Innenkühlungsaufbau einer Turbinenlaufschaufel.
CH697747A2 (de)	2009-02-13	Schema zum Halten der äusseren Seitenwand für eine Singlet-Düse der ersten Stufe.
DE112020004602B4 (de)	2024-08-29	Turbinenflügel
CH709048A2 (de)	2015-06-30	Laufschaufel mit einer Dämpferanordnung für eine Turbine.
EP3324002A1 (fr)	2018-05-23	Système d'étanchéité pour une turbomachine axiale et turbomachine axiale
DE102007050916A1 (de)	2008-04-30	Verfahren und Vorrichtung zum Zusammenbau von Gasturbinen-Triebwerken
EP3412875A2 (fr)	2018-12-12	Structure de rodage pour une turbomachine et procédé de fabrication d'une structure de rodage
EP3379037B1 (fr)	2021-06-02	Étanchéité sur une bague intérieure d'une couronne d'aubes directrices
DE4100554A1 (de)	1991-08-14	Vorrichtung zur spaltabdichtung zwischen benachbarten segmenten von turbinenleitschaufelkraenzen und mantelringen
EP3287611A1 (fr)	2018-02-28	Turbine à gaz et procédé de suspension d'un segment d'aube de guidage d'une turbine à gaz
DE602004006035T2 (de)	2008-01-03	Kühleinrichtung für Turbinenscheiben
DE2532554C2 (de)	1985-05-23	Verdichterstator
EP3263838A1 (fr)	2018-01-03	Pale de turbine avec canal de refroidissement interne
DE102016215807A1 (de)	2018-03-01	Innenring für einen Leitschaufelkranz einer Strömungsmaschine

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