EP1995413A1 - Outil de nettoyage d'au moins un partie d'un toit - Google Patents

Outil de nettoyage d'au moins un partie d'un toit Download PDF

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Publication number
EP1995413A1
EP1995413A1 EP08153316A EP08153316A EP1995413A1 EP 1995413 A1 EP1995413 A1 EP 1995413A1 EP 08153316 A EP08153316 A EP 08153316A EP 08153316 A EP08153316 A EP 08153316A EP 1995413 A1 EP1995413 A1 EP 1995413A1
Authority
EP
European Patent Office
Prior art keywords
blade
gap
projection
blades
circumferential direction
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.)
Granted
Application number
EP08153316A
Other languages
German (de)
English (en)
Other versions
EP1995413B1 (fr
Inventor
Thomas Heinz-Schwarzmaier
Sven Olmes
Ronald Wifling
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 Technology 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 EP1995413A1 publication Critical patent/EP1995413A1/fr
Application granted granted Critical
Publication of EP1995413B1 publication Critical patent/EP1995413B1/fr
Active 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms

Definitions

  • the present invention relates to a gap seal for radially sealing a gap extending axially and radially between two circumferentially adjacent blades of a turbomachine.
  • Blades are circumferentially adjacent to each other.
  • rotor blades in the region of the blade roots form gaps that extend in each case axially and radially between the blade roots of adjacent blades.
  • two axially adjacent blades in the circumferential direction at their respective blade root to provide extending, open towards the gap longitudinal groove.
  • a band-shaped or strip-shaped sealing element can be inserted, such that it engages with its longitudinal sides in the two longitudinal grooves and thus bridges the gap.
  • a residual gap may still be present at the front end of the sealing element. This can be attributed to manufacturing tolerances. Furthermore, this residual gap may form or increase during operation of the turbomachine due to thermal expansion effects.
  • the invention deals with the problem of providing a gap seal of the type mentioned an improved embodiment, which is characterized in particular by an increased sealing effect.
  • the invention is based on the general idea to allow the sealing element to engage in its end face in a corresponding groove, so that no residual gap is left.
  • a projection is formed on one of the two blades, between the feet of which there is a gap, which protrudes in the circumferential direction from the blade root of a blade and thereby at least in the region of the longitudinal groove of this blade in the circumferential direction and extends in the radial direction.
  • the projection may overlap the gap in the circumferential direction.
  • a transverse groove can be incorporated, in which the end face of the sealing element can be inserted.
  • the gap can now also be sealed in the area of the end face of the sealing element. The effectiveness of the gap seal thus formed is thus improved.
  • the projection may be dimensioned such that it overlaps on the one hand the axially open longitudinal groove of the other blade and that on the other hand it is large enough to design the transverse groove incorporated therein at its front ends closed.
  • the projection and the recess may optionally be coordinated with each other so that the projection in the recess abuts axially on the blade root of the other blade.
  • the transverse groove in the projection of one blade passes virtually seamlessly into the longitudinal groove of the other blade. As a result, the sealing effect of the gap seal can be improved.
  • Fig. 1 are two blades, namely a first blade 1 and a second blade 2 partially shown, each forming a part of a turbomachine, otherwise not shown.
  • This turbomachine is for example a turbine or a compressor.
  • the turbomachine has a stator and a rotor which is rotatably arranged in the stator about an axis of rotation.
  • the directions given above and below, such as axial direction, radial direction and circumferential direction relate in each case to the axis of rotation which defines the axial direction.
  • the directions related to the axis of rotation of the rotor are indicated by double arrows. With 3, the circumferential direction is denoted by 4 denotes the axial direction and 5 denotes the radial direction.
  • the blades 1, 2 may be stator vanes. Preferably, however, the blades 1, 2 are blades of the rotor.
  • the two blades 1, 2 shown here are arranged adjacent to one another in the circumferential direction 3.
  • Each blade 1, 2 has a blade root 6 and 7, respectively.
  • the blade root 6 of the first blade 1 is referred to below as the first blade root 6.
  • the blade root 7 of the second blade 2 is referred to below as the second blade root 7.
  • a gap 8 which extends in the axial direction 4 and in the radial direction 5, is formed in the circumferential direction 3 between adjacent blades 1, 2 in the area of the blade roots 6, 7.
  • a gap seal 9 is formed in the region of the gap 8, which will be explained in more detail below.
  • the gap seal 9 is in the one blade 1, so e.g. in the first blade 1, at its blade root 6, a longitudinal groove 10 incorporated, which is referred to below as the first longitudinal groove 10.
  • the first longitudinal groove 10 extends axially and is open to the gap 8.
  • a longitudinal groove 11 is incorporated, which is referred to below as the second longitudinal groove 11.
  • the second longitudinal groove 11 is also open to the gap 8 and extends axially.
  • the two longitudinal grooves 10, 11 are arranged on the respective blade root 6, 7 so that they face each other in the gap 8 and aligned with each other.
  • the gap seal 9 comprises a band-shaped or strip-shaped sealing element 12, which may be formed for example by a flat metal component.
  • the term "flat” here defines that the sealing element 12 in his axial longitudinal direction and in its direction parallel to the circumferential direction 3 transverse direction greater dimensions than in its radial thickness direction.
  • the sealing element 12 is dimensioned such that it engages with its longitudinal sides 13, 14 in the two longitudinal grooves 10, 11 in the circumferential direction 3. As a result, the sealing element 12 bridges the gap 8 in the region of an axial longitudinal end.
  • the one or first blade 1 has at its blade root 6 on a projection 15 which projects in the circumferential direction 3 from the first blade root 6.
  • This projection 15 extends at least in the region of the associated longitudinal groove 10 in the circumferential direction 3 and radially.
  • the projection 15 extends over the entire radial height of the first blade root 6.
  • the other or second blade 2 at its blade root 7 a stepped recess 16, in which the projection 15 engages in the illustrated assembled state. In this case, the projection 16 projects into the recess 16 in the circumferential direction 3.
  • the gap seal 9 now also comprises a transverse groove 17, which is incorporated in the projection 15, in such a way that it extends in the circumferential direction 3 and the gap 8 is open.
  • the transverse groove 17 is positioned at the height of the longitudinal grooves 10, 11. Accordingly, the sealing element 12 can engage axially with a projection 15 facing end face 18 in the transverse groove 17.
  • the thus formed gap seal 9 is characterized by an increased sealing effect.
  • the transverse groove 17 is expediently designed such that it merges directly into the first longitudinal groove 10.
  • the second longitudinal groove 11 is in the region of the recess 16 frontally open, so axially open.
  • the projection 15 is expedient in the circumferential direction 3 dimensioned so that it is the frontally open end of the second longitudinal groove 11 overlaps in the recess 16.
  • the dimensioning of the projection 15 is matched to the second longitudinal groove 11, that the projection 15, the recess 16 overlaps so far that the transverse groove 17 may be configured to be closed at both front ends.
  • the projection 15 in one of the second blade 2 facing end-side end portion of the transverse groove 17 forms a closure of this end face of the transverse groove 17.
  • the embodiment shown here in which the recess 16 and the projection 15 are coordinated so that the projection 15 axially abuts in the mounted state shown within the recess 16 on the second blade root 7.
  • leaks can be reduced by a flow around the projection 15 within the recess 16.
  • the transverse groove 17 can thus also merge seamlessly into the second longitudinal groove 11.
  • transverse groove 17 with respect to their groove depth and the sealing element 12 are matched with respect to its axial extent to one another so that the sealing element 12 can still engage with its end face 18 sufficiently deep into the transverse groove 17 to a desired sealing effect to be able to guarantee if the usual manufacturing tolerances to be expected in the production and the usual thermal expansion processes to be expected during operation of the turbomachine have extreme values and unfavorably add up.
  • the proposed gap seal 9 can thus cause a sufficient sealing of the gap 9 for usual manufacturing tolerances and thermal expansion processes in the region of the end face 18.
  • the two blades 1, 2 can be basically identical, so that the second blade 2 on its side facing away from the first blade 1 side also has such a projection 15, which in turn engages in a recess 16, the in the circumferential direction 3 on the second blade 2 subsequent further blade is formed.
  • the first blade 1 has on its blade root 6 on its side remote from the second blade 2 side such a recess 6, in which a projection 15 engages, which is formed on an adjacent in this direction to the first blade 1 further blade.

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)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
EP08153316A 2007-04-05 2008-03-26 Joint d'étanchéité pour le jeu d'aubes d'une turbomachine Active EP1995413B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH5732007 2007-04-05

Publications (2)

Publication Number Publication Date
EP1995413A1 true EP1995413A1 (fr) 2008-11-26
EP1995413B1 EP1995413B1 (fr) 2010-04-28

Family

ID=38457915

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08153316A Active EP1995413B1 (fr) 2007-04-05 2008-03-26 Joint d'étanchéité pour le jeu d'aubes d'une turbomachine

Country Status (6)

Country Link
US (1) US8043050B2 (fr)
EP (1) EP1995413B1 (fr)
JP (1) JP5094510B2 (fr)
AT (1) ATE466169T1 (fr)
DE (1) DE502008000588D1 (fr)
ES (1) ES2345303T3 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ATE537333T1 (de) * 2009-01-28 2011-12-15 Alstom Technology Ltd Streifendichtung und verfahren zum entwurf einer streifendichtung
US20120045337A1 (en) * 2010-08-20 2012-02-23 Michael James Fedor Turbine bucket assembly and methods for assembling same
US8905716B2 (en) 2012-05-31 2014-12-09 United Technologies Corporation Ladder seal system for gas turbine engines
BE1022361B1 (fr) * 2014-11-06 2016-03-17 Techspace Aero Sa Stator mixte de compresseur de turbomachine axiale.
EP3498980B1 (fr) * 2017-12-15 2021-02-17 Ansaldo Energia Switzerland AG Agencement de joint à feuillure

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000057031A1 (fr) * 1999-03-19 2000-09-28 Siemens Aktiengesellschaft Rotor de turbine a gaz dote d'une aube a refroidissement interne
EP1221539A2 (fr) * 2001-01-09 2002-07-10 Mitsubishi Heavy Industries, Ltd. Dispositif d'étanchéité d'une virole de turbine
EP1408199A1 (fr) * 2002-10-08 2004-04-14 United Technologies Corporation Configuration des fentes dans un segment d'un anneau de guidage
US20050135925A1 (en) 2001-07-11 2005-06-23 Mitsubishi Heavy Industries Ltd Gas turbine stationary blade
US20050186074A1 (en) * 2004-02-23 2005-08-25 Mitsubishi Heavy Industries, Ltd. Moving blade and gas turbine using the same

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3981609A (en) * 1975-06-02 1976-09-21 United Technologies Corporation Coolable blade tip shroud
US3995971A (en) * 1975-06-02 1976-12-07 United Technologies Corporation Rotatable vane seal
US3970318A (en) * 1975-09-26 1976-07-20 General Electric Company Sealing means for a segmented ring
EP0103260A3 (fr) * 1982-09-06 1984-09-26 Hitachi, Ltd. Régulation du jeu des extrémités des aubes de turbine
FR2552159B1 (fr) * 1983-09-21 1987-07-10 Snecma Dispositif de liaison et d'etancheite de secteurs d'aubes de stator de turbine
JPS60133103U (ja) * 1984-02-17 1985-09-05 株式会社日立製作所 シ−ル構造
EP0536575B1 (fr) * 1991-10-08 1995-04-05 Asea Brown Boveri Ag Bande de recouvrement pour roue de turbine axiale
DE59710924D1 (de) * 1997-09-15 2003-12-04 Alstom Switzerland Ltd Kühlvorrichtung für Gasturbinenkomponenten
JP3999395B2 (ja) * 1999-03-03 2007-10-31 三菱重工業株式会社 ガスタービン分割環

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000057031A1 (fr) * 1999-03-19 2000-09-28 Siemens Aktiengesellschaft Rotor de turbine a gaz dote d'une aube a refroidissement interne
EP1221539A2 (fr) * 2001-01-09 2002-07-10 Mitsubishi Heavy Industries, Ltd. Dispositif d'étanchéité d'une virole de turbine
US20050135925A1 (en) 2001-07-11 2005-06-23 Mitsubishi Heavy Industries Ltd Gas turbine stationary blade
EP1408199A1 (fr) * 2002-10-08 2004-04-14 United Technologies Corporation Configuration des fentes dans un segment d'un anneau de guidage
US20050186074A1 (en) * 2004-02-23 2005-08-25 Mitsubishi Heavy Industries, Ltd. Moving blade and gas turbine using the same

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same

Also Published As

Publication number Publication date
US8043050B2 (en) 2011-10-25
JP2008255989A (ja) 2008-10-23
EP1995413B1 (fr) 2010-04-28
ATE466169T1 (de) 2010-05-15
JP5094510B2 (ja) 2012-12-12
US20080247867A1 (en) 2008-10-09
ES2345303T3 (es) 2010-09-20
DE502008000588D1 (de) 2010-06-10

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