EP1900907A3 - Turbine blade tip gap reduction system for a turbine engine - Google Patents

Turbine blade tip gap reduction system for a turbine engine Download PDF

Info

Publication number
EP1900907A3
EP1900907A3 EP07113096A EP07113096A EP1900907A3 EP 1900907 A3 EP1900907 A3 EP 1900907A3 EP 07113096 A EP07113096 A EP 07113096A EP 07113096 A EP07113096 A EP 07113096A EP 1900907 A3 EP1900907 A3 EP 1900907A3
Authority
EP
European Patent Office
Prior art keywords
turbine
turbine blade
turbine blades
ring segments
blade assembly
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.)
Withdrawn
Application number
EP07113096A
Other languages
German (de)
French (fr)
Other versions
EP1900907A2 (en
Inventor
Gennadiy Afanasiev
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.)
Siemens Energy Inc
Original Assignee
Siemens Energy Inc
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 Siemens Energy Inc filed Critical Siemens Energy Inc
Publication of EP1900907A2 publication Critical patent/EP1900907A2/en
Publication of EP1900907A3 publication Critical patent/EP1900907A3/en
Withdrawn legal-status Critical Current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
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2250/40—Movement of components

Abstract

A turbine blade gap control system (10) configured to move a vane carrier (22) and attached ring segments (16) of a turbine engine (18) axially relative to a turbine blade assembly (28) to reduce the gaps (12) between the tips (20) of the turbine blades (14) and the ring segments (16) to increase the efficiency of the turbine engine (18) once operating in a steady state condition. The turbine blade assembly (28) may be formed from a plurality rows (30) of turbine blades (14) extending radially from a rotor (32), wherein each row (30) may be formed from a plurality of turbine blades (14) and wherein the turbine blades (14) may have tips (20) positioned at an acute angle (24) relative to a rotational axis (26) of the turbine blade assembly (28). A vane carrier (22) may be positioned concentric with the rotor (32) and positioned radially outward from the turbine blades (14), and a plurality of ring segments (16) may be attached to the vane carrier (22).
EP07113096A 2006-09-08 2007-07-25 Turbine blade tip gap reduction system for a turbine engine Withdrawn EP1900907A3 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/518,018 US20080063513A1 (en) 2006-09-08 2006-09-08 Turbine blade tip gap reduction system for a turbine engine

Publications (2)

Publication Number Publication Date
EP1900907A2 EP1900907A2 (en) 2008-03-19
EP1900907A3 true EP1900907A3 (en) 2009-12-16

Family

ID=38776301

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07113096A Withdrawn EP1900907A3 (en) 2006-09-08 2007-07-25 Turbine blade tip gap reduction system for a turbine engine

Country Status (3)

Country Link
US (1) US20080063513A1 (en)
EP (1) EP1900907A3 (en)
CA (1) CA2600788A1 (en)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2233701A1 (en) * 2009-03-26 2010-09-29 Siemens Aktiengesellschaft Axial turbomachine with axially displaceable vane carrier
US8186945B2 (en) 2009-05-26 2012-05-29 General Electric Company System and method for clearance control
DE102009023062A1 (en) * 2009-05-28 2010-12-02 Mtu Aero Engines Gmbh Gap control system, turbomachine and method for adjusting a running gap between a rotor and a casing of a turbomachine
US8939715B2 (en) * 2010-03-22 2015-01-27 General Electric Company Active tip clearance control for shrouded gas turbine blades and related method
US8550785B2 (en) 2010-06-11 2013-10-08 Siemens Energy, Inc. Wire seal for metering of turbine blade cooling fluids
US9488062B2 (en) * 2012-05-10 2016-11-08 General Electric Company Inner turbine shell axial movement
US20130315716A1 (en) * 2012-05-22 2013-11-28 General Electric Company Turbomachine having clearance control capability and system therefor
US9435218B2 (en) * 2013-07-31 2016-09-06 General Electric Company Systems relating to axial positioning turbine casings and blade tip clearance in gas turbine engines
US9441499B2 (en) * 2013-07-31 2016-09-13 General Electric Company System and method relating to axial positioning turbine casings and blade tip clearance in gas turbine engines
US9683453B2 (en) * 2013-09-11 2017-06-20 General Electric Company Turbine casing clearance management system
US9593589B2 (en) 2014-02-28 2017-03-14 General Electric Company System and method for thrust bearing actuation to actively control clearance in a turbo machine
US10323536B2 (en) * 2015-04-09 2019-06-18 United Technologies Corporation Active clearance control for axial rotor systems
WO2017074352A1 (en) * 2015-10-28 2017-05-04 Halliburton Energy Services, Inc. Downhole turbine with an adjustable shroud
CN109751131A (en) * 2019-03-29 2019-05-14 国电环境保护研究院有限公司 A kind of method of adjustment promoting gas turbine proficiency and power
CN110725722B (en) * 2019-08-27 2022-04-19 中国科学院工程热物理研究所 Dynamic and continuous adjustable structure for movable blade top clearance suitable for impeller machinery

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1249577A1 (en) * 2001-04-12 2002-10-16 Siemens Aktiengesellschaft Gas turbine with axially movable shroud elements
EP1676978A2 (en) * 2004-12-29 2006-07-05 United Technologies Corporation Gas turbine engine blade tip clearance apparatus and method

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3520635A (en) * 1968-11-04 1970-07-14 Avco Corp Turbomachine shroud assembly
US5203673A (en) * 1992-01-21 1993-04-20 Westinghouse Electric Corp. Tip clearance control apparatus for a turbo-machine blade
DE10060740A1 (en) * 2000-12-07 2002-06-13 Alstom Switzerland Ltd Device for setting gap dimensions for a turbomachine
GB2374123B (en) * 2001-04-05 2004-09-08 Rolls Royce Plc Gas turbine engine system
US7407369B2 (en) * 2004-12-29 2008-08-05 United Technologies Corporation Gas turbine engine blade tip clearance apparatus and method

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1249577A1 (en) * 2001-04-12 2002-10-16 Siemens Aktiengesellschaft Gas turbine with axially movable shroud elements
EP1676978A2 (en) * 2004-12-29 2006-07-05 United Technologies Corporation Gas turbine engine blade tip clearance apparatus and method

Also Published As

Publication number Publication date
EP1900907A2 (en) 2008-03-19
US20080063513A1 (en) 2008-03-13
CA2600788A1 (en) 2008-03-08

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