EP1512842A3 - Gas turbine with tip clearance control for blades - Google Patents

Gas turbine with tip clearance control for blades Download PDF

Info

Publication number
EP1512842A3
EP1512842A3 EP04018924A EP04018924A EP1512842A3 EP 1512842 A3 EP1512842 A3 EP 1512842A3 EP 04018924 A EP04018924 A EP 04018924A EP 04018924 A EP04018924 A EP 04018924A EP 1512842 A3 EP1512842 A3 EP 1512842A3
Authority
EP
European Patent Office
Prior art keywords
blades
gas turbine
tip clearance
clearance control
segments
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
EP04018924A
Other languages
German (de)
French (fr)
Other versions
EP1512842A2 (en
EP1512842B1 (en
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/en
Publication of EP1512842A3 publication Critical patent/EP1512842A3/en
Application granted granted Critical
Publication of EP1512842B1 publication Critical patent/EP1512842B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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

Landscapes

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

Abstract

Die Erfindung bezieht sich auf eine Gasturbine mit mehreren Deckbandsegmenten 1, welche als Dichtung Laufschaufeln 3 eines Turbinenrades 5 umschließen, wobei zumindest eine vordere und eine hintere Befestigung der Deckbandsegmente 1 an dem radial äußeren Bereich von Leitschaufelsegmenten 7, 12 erfolgt, welche an ihrem radial inneren Bereich jeweils an einem Steuerring 9, 10 gelagert sind, dadurch gekennzeichnet, dass die Leitschaufelsegmente 7, 12 radial einstellbar an dem Steuerring 9, 10 gelagert sind.

Figure imgaf001
The invention relates to a gas turbine with a plurality of shroud segments 1, which enclose as blades 3 of a turbine wheel 5, wherein at least a front and a rear attachment of the shroud segments 1 takes place at the radially outer region of stator segments 7, 12, which at its radially inner Area are each mounted on a control ring 9, 10, characterized in that the guide blade segments 7, 12 are mounted radially adjustable on the control ring 9, 10.
Figure imgaf001
EP04018924A 2003-09-04 2004-08-10 Gas turbine with tip clearance control for blades Expired - Lifetime EP1512842B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10340825A DE10340825A1 (en) 2003-09-04 2003-09-04 Gas turbine with running gap control
DE10340825 2003-09-04

Publications (3)

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

Family

ID=34129646

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04018924A Expired - Lifetime EP1512842B1 (en) 2003-09-04 2004-08-10 Gas turbine with tip clearance control for blades

Country Status (3)

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

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
EP1712744B1 (en) * 2005-04-14 2009-01-07 Rolls-Royce Deutschland Ltd & Co KG Arrangement in a high pressure turbine for passive tip clearance control
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

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2061396A (en) * 1979-10-24 1981-05-13 Rolls Royce Turbine blade tip clearance control

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2061396A (en) * 1979-10-24 1981-05-13 Rolls Royce Turbine blade tip clearance control

Also Published As

Publication number Publication date
DE502004009777D1 (en) 2009-09-03
EP1512842A2 (en) 2005-03-09
DE10340825A1 (en) 2005-03-31
US7306428B2 (en) 2007-12-11
EP1512842B1 (en) 2009-07-22
US20050089400A1 (en) 2005-04-28

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