EP1580404A3 - Arrangement for self adjusting the tip clearance in a two or multiple stage turbine - Google Patents

Arrangement for self adjusting the tip clearance in a two or multiple stage turbine Download PDF

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Publication number
EP1580404A3
EP1580404A3 EP05090065A EP05090065A EP1580404A3 EP 1580404 A3 EP1580404 A3 EP 1580404A3 EP 05090065 A EP05090065 A EP 05090065A EP 05090065 A EP05090065 A EP 05090065A EP 1580404 A3 EP1580404 A3 EP 1580404A3
Authority
EP
European Patent Office
Prior art keywords
guide vanes
stage turbine
arrangement
rotors
bridge
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
EP05090065A
Other languages
German (de)
French (fr)
Other versions
EP1580404B1 (en
EP1580404A2 (en
Inventor
Thomas Wunderlich
Peter Broadhead
Harald Schiebold
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 EP1580404A2 publication Critical patent/EP1580404A2/en
Publication of EP1580404A3 publication Critical patent/EP1580404A3/en
Application granted granted Critical
Publication of EP1580404B1 publication Critical patent/EP1580404B1/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • 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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments

Abstract

Bei einer zwei- oder mehrstufigen Turbine sind zur passiven kontinuierlichen Laufspalteinstellung in allen Stufen den Rotoren seitlich Dehnringe zugeordnet, deren thermisches Dehnungs- und Kontraktionsverhalten dem der Rotoren entspricht und die mit radial beweglichen vorgeschalteten und nachgeschalteten Leitschaufeln (5, 7) verbunden sind. Die nachgeschalteten Leitschaufeln sind an den vorgeschalteten Leitschaufeln über eine axial und in Umfangsrichtung fixierte sowie am Außengehäuse (10) der Turbine radial flexibel geführte Brücke (16; 17, 18) montiert. Die zwischen den Rotorscheiben angeordneten Leitschaufeln (6) sind integral mit der Brücke verbunden oder als separate Bauteile an dieser axial und in Umfangsrichtung zur Aufnahme von Roll- und Kippmomenten gehalten.

Figure imgaf001
In a two-stage or multi-stage turbine, laterally expansion rings are assigned to the rotors for passive continuous clearance adjustment in all stages, whose thermal expansion and contraction behavior corresponds to that of the rotors and which are connected to radially movable upstream and downstream guide vanes (5, 7). The downstream guide vanes are mounted on the upstream guide vanes via a bridge (16, 17, 18) which is fixed in an axially and circumferentially fixed manner and radially flexibly guided on the outer housing (10) of the turbine. The vanes (6) arranged between the rotor disks are integrally connected to the bridge or held as separate components at this axially and in the circumferential direction for receiving rolling and tilting moments.
Figure imgaf001
EP05090065A 2004-03-26 2005-03-16 Arrangement for self adjusting the tip clearance in a two or multiple stage turbine Expired - Fee Related EP1580404B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004016222 2004-03-26
DE102004016222A DE102004016222A1 (en) 2004-03-26 2004-03-26 Arrangement for automatic running gap adjustment in a two-stage or multi-stage turbine

Publications (3)

Publication Number Publication Date
EP1580404A2 EP1580404A2 (en) 2005-09-28
EP1580404A3 true EP1580404A3 (en) 2008-10-01
EP1580404B1 EP1580404B1 (en) 2011-10-05

Family

ID=34854112

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05090065A Expired - Fee Related EP1580404B1 (en) 2004-03-26 2005-03-16 Arrangement for self adjusting the tip clearance in a two or multiple stage turbine

Country Status (3)

Country Link
US (2) US7524164B2 (en)
EP (1) EP1580404B1 (en)
DE (1) DE102004016222A1 (en)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2887939B1 (en) 2005-06-29 2016-09-30 Soc Nat D'etude Et De Construction De Moteurs D'aviation Snecma TURBOMACHINE MULTI-STAGE COMPRESSOR
EP1890011A1 (en) * 2006-08-07 2008-02-20 ABB Turbo Systems AG Axial flow turbine with slotted shroud
DE102007031711A1 (en) 2007-07-06 2009-01-08 Rolls-Royce Deutschland Ltd & Co Kg Housing shroud segment suspension
EP2184445A1 (en) * 2008-11-05 2010-05-12 Siemens Aktiengesellschaft Axial segmented vane support for a gas turbine
DE102008060706A1 (en) * 2008-12-05 2010-06-10 Man Turbo Ag Nozzle segment for a steam turbine
US8876458B2 (en) * 2011-01-25 2014-11-04 United Technologies Corporation Blade outer air seal assembly and support
JP5665724B2 (en) * 2011-12-12 2015-02-04 株式会社東芝 Stator blade cascade, method of assembling stator blade cascade, and steam turbine
US9500095B2 (en) * 2013-03-13 2016-11-22 Pratt & Whitney Canada Corp. Turbine shroud segment sealing
EP2853685A1 (en) * 2013-09-25 2015-04-01 Siemens Aktiengesellschaft Insert element and gas turbine
US9266618B2 (en) 2013-11-18 2016-02-23 Honeywell International Inc. Gas turbine engine turbine blade tip active clearance control system and method
GB201507647D0 (en) * 2015-05-05 2015-06-17 Rolls Royce Plc Casing assembly
FR3045717B1 (en) * 2015-12-22 2020-07-03 Safran Aircraft Engines DEVICE FOR DRIVING A TURBINE ROTATING BLADE TOP
DE102016213810A1 (en) * 2016-07-27 2018-02-01 MTU Aero Engines AG Cladding element for a turbine intermediate housing
US10641129B2 (en) * 2017-11-08 2020-05-05 United Technologies Corporation Support rail truss for gas turbine engines
US11174742B2 (en) 2019-07-19 2021-11-16 Rolls-Royce Plc Turbine section of a gas turbine engine with ceramic matrix composite vanes

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB886626A (en) * 1958-09-04 1962-01-10 Bristol Siddeley Engines Ltd Improvements in or relating to axial flow turbines or compressors
US4242042A (en) * 1978-05-16 1980-12-30 United Technologies Corporation Temperature control of engine case for clearance control
GB2061396A (en) * 1979-10-24 1981-05-13 Rolls Royce Turbine blade tip clearance control
GB2226365A (en) * 1988-12-22 1990-06-27 Rolls Royce Plc Turbomachine clearance control
WO1995025879A1 (en) * 1994-03-21 1995-09-28 United Technologies Corporation Compressor stator vane assembly
US20030146578A1 (en) * 2002-02-07 2003-08-07 Snecma Moteurs Arrangement for the attachment of distributor sectors supporting vanes around an arc of a circle

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2634090A (en) * 1950-07-28 1953-04-07 Westinghouse Electric Corp Turbine apparatus
US2955800A (en) * 1957-05-28 1960-10-11 Gen Motors Corp Turbomachine stator assembly
US3446481A (en) * 1967-03-24 1969-05-27 Gen Electric Liquid cooled turbine rotor
BE786674A (en) * 1971-07-26 1973-01-25 Westinghouse Electric Corp MULTI-ENCLOSURE TURBINE
US4076451A (en) * 1976-03-05 1978-02-28 United Technologies Corporation Ceramic turbine stator
FR2548733B1 (en) * 1983-07-07 1987-07-10 Snecma DEVICE FOR SEALING MOBILE BLADES OF A TURBOMACHINE
US5181826A (en) * 1990-11-23 1993-01-26 General Electric Company Attenuating shroud support
US5228828A (en) * 1991-02-15 1993-07-20 General Electric Company Gas turbine engine clearance control apparatus
US5165850A (en) * 1991-07-15 1992-11-24 General Electric Company Compressor discharge flowpath
US5412939A (en) * 1993-12-20 1995-05-09 Alliedsignal Inc. Seal compression tool for gas turbine engine
DE19807247C2 (en) * 1998-02-20 2000-04-20 Mtu Muenchen Gmbh Turbomachine with rotor and stator
FR2794816B1 (en) * 1999-06-10 2001-07-06 Snecma HIGH PRESSURE COMPRESSOR STATOR
US6340285B1 (en) * 2000-06-08 2002-01-22 General Electric Company End rail cooling for combined high and low pressure turbine shroud
GB2388407B (en) * 2002-05-10 2005-10-26 Rolls Royce Plc Gas turbine blade tip clearance control structure
US20040219011A1 (en) * 2003-05-02 2004-11-04 General Electric Company High pressure turbine elastic clearance control system and method

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB886626A (en) * 1958-09-04 1962-01-10 Bristol Siddeley Engines Ltd Improvements in or relating to axial flow turbines or compressors
US4242042A (en) * 1978-05-16 1980-12-30 United Technologies Corporation Temperature control of engine case for clearance control
GB2061396A (en) * 1979-10-24 1981-05-13 Rolls Royce Turbine blade tip clearance control
GB2226365A (en) * 1988-12-22 1990-06-27 Rolls Royce Plc Turbomachine clearance control
WO1995025879A1 (en) * 1994-03-21 1995-09-28 United Technologies Corporation Compressor stator vane assembly
US20030146578A1 (en) * 2002-02-07 2003-08-07 Snecma Moteurs Arrangement for the attachment of distributor sectors supporting vanes around an arc of a circle

Also Published As

Publication number Publication date
US20050254939A1 (en) 2005-11-17
US20090269190A1 (en) 2009-10-29
EP1580404B1 (en) 2011-10-05
EP1580404A2 (en) 2005-09-28
US7524164B2 (en) 2009-04-28
DE102004016222A1 (en) 2005-10-06

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