EP1512842B1 - Turbine à gaz avec réglage du jeu des aubes - Google Patents

Turbine à gaz avec réglage du jeu des aubes Download PDF

Info

Publication number
EP1512842B1
EP1512842B1 EP04018924A EP04018924A EP1512842B1 EP 1512842 B1 EP1512842 B1 EP 1512842B1 EP 04018924 A EP04018924 A EP 04018924A EP 04018924 A EP04018924 A EP 04018924A EP 1512842 B1 EP1512842 B1 EP 1512842B1
Authority
EP
European Patent Office
Prior art keywords
control ring
gas turbine
segments
stator vane
accordance
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
EP04018924A
Other languages
German (de)
English (en)
Other versions
EP1512842A3 (fr
EP1512842A2 (fr
Inventor
Harald Schiebold
Olaf Mistareck
Thomas Wunderlich
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 EP1512842A2 publication Critical patent/EP1512842A2/fr
Publication of EP1512842A3 publication Critical patent/EP1512842A3/fr
Application granted granted Critical
Publication of EP1512842B1 publication Critical patent/EP1512842B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion

Definitions

  • the invention relates to a gas turbine with a plurality of shroud segments, which surround as blades rotor blades of a turbine wheel, wherein at least one front or a rear attachment of the shroud segments takes place at the radially outer region of Leitschaufelsegmenten, which are each mounted on a control ring at its inner region.
  • control ring The purpose of using a control ring is to utilize the thermal expansion of the control ring to adjust the vane segments according to the thermal conditions in their outer circumference. This results in a reduction or enlargement of the overall diameter of the ring formed by the shroud segments. This results in an adjustment of the gap between the tips of the blades and the interior of the shroud segments. Otherwise, thermal contraction or expansion of the blades would result in enlargement of the gap or contact with the shroud segments.
  • the prior art is therefore based on the basic idea to achieve an optimal passive running gap control. This is achieved, as described, by the fact that the fastening means of the shroud segments have a thermal operating behavior which is synchronized with the radial movement of the blade tips of the rotor blades. Instationary operating conditions can ideally not adversely affect the running gap in stationary operation.
  • the invention has for its object to provide a gas turbine with an optimized passive clearance control, which has an optimized performance with a simple design and cost-effective production and assembly.
  • the guide blade segments are mounted radially adjustable on the control ring.
  • the construction according to the invention has a number of significant advantages.
  • annular gap seal (running gap) can be optimized in terms of dimensions compared to the basic design, since an exact adaptation to the thermal performance is possible.
  • axisymmetric and eccentric position deviations can be compensated without component change.
  • the guide blade segments are also mounted adjustably in the circumferential direction on the control ring.
  • the guide blade segments are also mounted adjustably in the circumferential direction on the control ring.
  • adjustable storage By inventively provided adjustable storage, the possibility is created during the installation to make an exact adjustment and to optimize the assignment of the components accordingly.
  • the guide blade segments are fixed by means of a screw under frictional engagement on the control ring.
  • a screw under frictional engagement on the control ring For example, it is possible to provide a sleeve with a setting clearance or a segment with a setting clearance.
  • the setting can also be done by an Excentervorraum, such as a fitting sleeve with eccentric.
  • At least one secondary air seal is formed on the control ring and the control ring is configured such that its thermal operating behavior controls the width of the annular gap of the secondary air seal.
  • the arranged within the vane annulus control ring is thereby designed so that its thermal performance in addition to the control of the nip also for controlling at least one annular gap seal of the rotor cooling air system (secondary air system) is used.
  • at least one secondary air seal connected to the control ring can be designed as a brush seal or multi-stage labyrinth.
  • the annular gap of this Seal optimized by the thermal performance accordingly.
  • the elements relevant for the thermal expansion of the control ring arrangement are selected with regard to their material selection such that their thermal expansion coefficient is at least 15% smaller than the thermal expansion coefficient of the respectively adjacent rotor disk.
  • the Fig. 3 shows the shroud segment 1 which is associated with the vane segment of the HDT 7 and the vane segment of the NDT 12.
  • the design of the housing and the cooling air ducts located therein are dispensed with at this point.
  • the guide blade segments 7 and 12 are mounted.
  • the fastening of the guide blade segments takes place in each case on a control ring, namely a front control ring 9 and a rear control ring 10.
  • the reference numeral 11 relates to a secondary air seal, which may be in the form of a brush seal.
  • Reference numeral 15 represents a housing of the HDT.
  • Fig. 3 The general structure of in Fig. 3 shown arrangement broadly corresponds to the prior art, the variants of the invention show in particular the enlarged Fig. 1 and 2 ,
  • the control ring 9 is provided with an insulation 16 which approximates its thermal behavior to the thermal behavior of the disk 5.
  • the attachment is effected by means of a sleeve 17 and a screw 18, wherein additionally a load compensation element 19 is provided.
  • the sleeve has a setting game, the fixation via the screw by means of the screw 18 with frictional engagement.
  • the vane segment 7 it is possible to adjust the vane segment 7 to some extent in both the radial and circumferential directions.
  • the pressure on the control ring can be adjusted.
  • the load compensation element 19 the inner blade suspension 14 is relieved and can thereby be made smaller. This has a favorable effect on the weight and costs of the entire body.
  • Each blade is thus screwed by means of a screw 18 to the control ring 9.
  • the sleeve 17 is located in the lower Bar of the vane (vane segment 7).
  • the sleeve can, viewed from the center of the sleeve, forces transmitted only in the radial direction of the vane.
  • the guide blade can thus, as described, tilt in the axial direction and the circumference over the sleeve center.
  • the bore diameter of the sleeve has a play to the screw diameter, which then allows the adjustability of the vanes to the control ring.
  • At least one brush seal is formed as an integral part of the control ring.
  • the selection of the respective materials (alloys) is made such that an adaptation to the thermal behavior and the joining technical concerns of the control ring takes place and the connection of the brush seal to the control ring without detachable connection elements is possible.
  • control ring and its positive axial connection to the stator segments are inventively designed so that an outer seal is formed on the control ring.
  • an outer seal is formed on the control ring.
  • it is ensured that a pressure gradient across the control ring results in load compensation at the location of the inner blade suspension.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (10)

  1. Turbine à gaz avec plusieurs segments de virole (1) qui entourent en tant que joints d'étanchéité les aubes mobiles (3) d'une roue de turbine (5), sachant qu'au moins une fixation avant et une fixation arrière des segments de virole (1) sont effectuées dans la zone radialement extérieure de segments d'aubes fixes (7, 12), lesquels sont respectivement logés dans leur zone radialement intérieure sur un anneau de commande (9, 10), caractérisée en ce que les segments d'aubes fixes (7, 12) sont logés sur l'anneau de commande (9, 10) de manière réglable dans le sens radial.
  2. Turbine à gaz selon la revendication n° 1, caractérisée en ce que les segments d'aubes fixes (7, 12) sont logés sur l'anneau de commande de manière réglable dans le sens circonférentiel.
  3. Turbine à gaz selon la revendication n° 1 ou n° 2, caractérisée en ce que les segments d'aubes fixes (7, 12) sont fixés à force sur l'anneau de commande (9, 10) par un boulonnage.
  4. Turbine à gaz selon une des revendications n° 1 à n° 3, caractérisée en ce que les segments d'aubes fixes (7, 12) sont ajustables par rapport à l'anneau de commande (9, 10) au moyen d'un jeu de réglage.
  5. Turbine à gaz selon une des revendications n° 1 à n° 3, caractérisée en ce que les segments d'aubes fixes (7, 12) sont ajustables par rapport à l'anneau de commande (9, 10) au moyen d'un dispositif excentrique.
  6. Turbine à gaz selon une des revendications n° 1 à n° 3, caractérisée en ce que les segments d'aubes fixes (7, 12) sont ajustables par rapport à l'anneau de commande (9, 10) au moyen de segments réglables.
  7. Turbine à gaz selon une des revendications n° 1 à n° 6, caractérisée en ce qu'au moins un joint d'air secondaire (11) est formé sur l'anneau de commande (9, 10), et que l'anneau de commande (9, 10) est conçu de manière à ce que son comportement thermique en fonctionnement règle la largeur de l'interstice annulaire du joint d'air secondaire (11).
  8. Turbine à gaz selon une des revendications n° 1 à n° 7, caractérisée en ce que les matériaux des éléments d'au moins un anneau de commande sont sélectionnés de manière telle que leur coefficient de dilatation thermique est inférieur d'au moins 15 % à celui du disque de rotor voisin (5).
  9. Turbine à gaz selon une des revendications n° 1 à n° 8, caractérisée en ce qu'un dispositif de compensation de charge se trouve sur les segments d'aubes fixes (7).
  10. Turbine à gaz selon une des revendications n° 1 à n° 9, caractérisée en ce qu'il s'agit d'une turbine polyétagée, sachant que la partie avant des premiers segments de virole est logée dans les segments d'aubes fixes situés en amont de la première roue de turbine, et que la partie arrière des derniers segments de virole est logée dans les segments d'aubes fixes situés en aval de la dernière roue de turbine.
EP04018924A 2003-09-04 2004-08-10 Turbine à gaz avec réglage du jeu des aubes Expired - Lifetime EP1512842B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10340825A DE10340825A1 (de) 2003-09-04 2003-09-04 Gasturbine mit Laufspaltkontrolle
DE10340825 2003-09-04

Publications (3)

Publication Number Publication Date
EP1512842A2 EP1512842A2 (fr) 2005-03-09
EP1512842A3 EP1512842A3 (fr) 2006-04-05
EP1512842B1 true EP1512842B1 (fr) 2009-07-22

Family

ID=34129646

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04018924A Expired - Lifetime EP1512842B1 (fr) 2003-09-04 2004-08-10 Turbine à gaz avec réglage du jeu des aubes

Country Status (3)

Country Link
US (1) US7306428B2 (fr)
EP (1) EP1512842B1 (fr)
DE (2) DE10340825A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7160078B2 (en) * 2004-09-23 2007-01-09 General Electric Company Mechanical solution for rail retention of turbine nozzles
DE502005006421D1 (de) * 2005-04-14 2009-02-26 Rolls Royce Deutschland Anordnung zur inneren passiven Laufspalteinstellung bei einer Hochdruckturbine
US9200530B2 (en) 2012-07-20 2015-12-01 United Technologies Corporation Radial position control of case supported structure
US9500095B2 (en) 2013-03-13 2016-11-22 Pratt & Whitney Canada Corp. Turbine shroud segment sealing
US9394801B2 (en) 2013-10-07 2016-07-19 General Electric Company Adjustable turbine seal and method of assembling same
US9206700B2 (en) * 2013-10-25 2015-12-08 Siemens Aktiengesellschaft Outer vane support ring including a strong back plate in a compressor section of a gas turbine engine

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2061396B (en) * 1979-10-24 1983-05-18 Rolls Royce Turbine blade tip clearance control
US4688378A (en) * 1983-12-12 1987-08-25 United Technologies Corporation One piece band seal
US5141394A (en) * 1990-10-10 1992-08-25 Westinghouse Electric Corp. Apparatus and method for supporting a vane segment in a gas turbine
US5149250A (en) * 1991-02-28 1992-09-22 General Electric Company Gas turbine vane assembly seal and support system
US5224822A (en) * 1991-05-13 1993-07-06 General Electric Company Integral turbine nozzle support and discourager seal
US5372476A (en) * 1993-06-18 1994-12-13 General Electric Company Turbine nozzle support assembly
US5921749A (en) * 1996-10-22 1999-07-13 Siemens Westinghouse Power Corporation Vane segment support and alignment device
US6095750A (en) * 1998-12-21 2000-08-01 General Electric Company Turbine nozzle assembly

Also Published As

Publication number Publication date
EP1512842A3 (fr) 2006-04-05
DE10340825A1 (de) 2005-03-31
EP1512842A2 (fr) 2005-03-09
US20050089400A1 (en) 2005-04-28
US7306428B2 (en) 2007-12-11
DE502004009777D1 (de) 2009-09-03

Similar Documents

Publication Publication Date Title
DE69812052T2 (de) Turbinenmantelring
DE69509884T2 (de) Leitschaufelanordnung für einen axialkompressor
EP2960438B1 (fr) Système d'aubes de guidage variables pour une turbine à gaz et turbine à gaz dotée d'un tel système
EP1428983B1 (fr) Carter de turbine à gas d'échappement
DE3305170C2 (de) Turbomaschinengehäuse
EP2918913B1 (fr) Chambre de combustion d'une turbine à gaz
EP0485556B1 (fr) Couronne directrice d'une turbine d'un groupe propulseur a turbine a gas
DE1033965B (de) Lader fuer Brennkraftmaschinen od. dgl.
DE3446389A1 (de) Statoraufbau fuer ein gasturbinen-triebwerk
DE1218800B (de) Gasturbine, insbesondere Kleingasturbine
EP2503246A2 (fr) Tête de chambre de combustion segmentée
EP3000984A1 (fr) Dispositif de reglage d'aube directrice d'une turbine a gaz
EP1389265A1 (fr) Anneau d'enveloppe
EP2574731A2 (fr) Composant segmenté
EP3152407A2 (fr) Couronne d'aubes fixes, bague intérieure et turbomachine
EP2342425A1 (fr) Turbine à gaz avec plaque de fixation entre la base d'aube et le disque
EP3091188A1 (fr) Turbomachine dotée d'un dispositif d'étanchéité
EP2955336B1 (fr) Boîtier intermédiaire pour une turbine à gaz et turbine à gaz dotée d'un tel boîtier intermédiaire
EP3159505B1 (fr) Carter intermédiaire pour une turbine a gaz
EP1512842A2 (fr) Turbine à gaz avec réglage du jeu des aubes
DE1476742A1 (de) Ringduese fuer den Einlauf von Gasturbinen
EP2526263B1 (fr) Système de boîtier pour une turbomachine axiale
DE102010036071A1 (de) Gehäuseseitige Struktur einer Turbomaschine
EP2271876B1 (fr) Dispositif de brûleur pour combustibles fluides et procédé de fabrication du dispositif de brûleur
EP3921577B1 (fr) Système de chambre de combustion à tubes et installation de turbine à gaz pourvue d'un tel système de chambre de combustion à tubes

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): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL HR LT LV MK

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL HR LT LV MK

17P Request for examination filed

Effective date: 20060518

AKX Designation fees paid

Designated state(s): DE FR GB

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RIN1 Information on inventor provided before grant (corrected)

Inventor name: MISTARECK, OLAF

Inventor name: WUNDERLICH, THOMAS

Inventor name: SCHIEBOLD, HARALD

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 502004009777

Country of ref document: DE

Date of ref document: 20090903

Kind code of ref document: P

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20100423

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 502004009777

Country of ref document: DE

Representative=s name: HOEFER & PARTNER, DE

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 502004009777

Country of ref document: DE

Representative=s name: HOEFER & PARTNER, DE

Effective date: 20130402

Ref country code: DE

Ref legal event code: R081

Ref document number: 502004009777

Country of ref document: DE

Owner name: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG, DE

Free format text: FORMER OWNER: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG, 15827 BLANKENFELDE, DE

Effective date: 20130402

Ref country code: DE

Ref legal event code: R082

Ref document number: 502004009777

Country of ref document: DE

Representative=s name: HOEFER & PARTNER PATENTANWAELTE MBB, DE

Effective date: 20130402

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 12

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20150827

Year of fee payment: 12

Ref country code: GB

Payment date: 20150827

Year of fee payment: 12

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20150817

Year of fee payment: 12

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502004009777

Country of ref document: DE

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20160810

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20170428

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170301

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160831

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160810