EP1076161A3 - Tip clearance control between rotor and stator of a turbomachine - Google Patents

Tip clearance control between rotor and stator of a turbomachine Download PDF

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Publication number
EP1076161A3
EP1076161A3 EP00810683A EP00810683A EP1076161A3 EP 1076161 A3 EP1076161 A3 EP 1076161A3 EP 00810683 A EP00810683 A EP 00810683A EP 00810683 A EP00810683 A EP 00810683A EP 1076161 A3 EP1076161 A3 EP 1076161A3
Authority
EP
European Patent Office
Prior art keywords
stator
rotor
turbomachine
carrier
axis
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Withdrawn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
EP00810683A
Other languages
German (de)
French (fr)
Other versions
EP1076161A2 (en
Inventor
Peter Marx
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 Schweiz 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 Schweiz AG filed Critical Alstom Schweiz AG
Publication of EP1076161A2 publication Critical patent/EP1076161A2/en
Publication of EP1076161A3 publication Critical patent/EP1076161A3/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Withdrawn legal-status Critical Current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
    • 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
    • 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
    • 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
    • F01D25/246—Fastening of diaphragms or stator-rings

Abstract

Beschrieben wird eine Vorrichtung sowie ein Verfahren zur gezielten Spalteinstellung zwischen Stator- und Rotoranordnung einer Strömungsmaschine, deren Statoranordnung einen Statorträger und wenigstens ein Statorsegment aufweist, das über wenigstens zwei Haltestege mit dem Statorträger verbindbar ist, und deren Rotoranordnung wenigstens eine, um eine Rotationsachse rotierbare Laufschaufelreihe mit einer Vielzahl einzelner Laufschaufeln vorsieht, deren Laufschaufelenden dem Statorsegment gegenüberstehen und mit diesem einen radialen Spalt einschließen.A device and a method for the targeted gap adjustment are described between the stator and rotor arrangement of a turbomachine, the stator arrangement has a stator carrier and at least one stator segment which over at least two retaining webs can be connected to the stator carrier, and their rotor arrangement at least one rotor blade row rotatable about an axis of rotation with a large number of individual blades, the blade ends of which Stand opposite stator segment and enclose a radial gap with this.

Die Erfindung zeichnet sich dadurch aus, daß die zwei Haltestege beabstandet voneinander auf dem Statorsegment angeordnet sind und wenigstens teilweise in Gegenkonturen innerhalb des Statorträgers eingreifen,
daß wenigstens ein Haltesteg einen, in die Gegenkontur des Statorträgers eingreifenden, geneigten Haltestegabschnitt aufweist, dessen Richtung seiner Längserstreckung mit einer, die Rotationsachse enthaltenen Ebene, die orthogonal zur radialen Längserstreckung derjenigen Laufschaufel orientiert ist, die mit dem Statorsegment den Spalt einschließt, einen Winkel a begrenzt, für den gilt: 0° < α < 90° oder 90° < α <180°.

Figure 00000001
The invention is characterized in that the two retaining webs are arranged at a distance from one another on the stator segment and at least partially engage in counter contours within the stator carrier.
that at least one retaining web has an inclined retaining web section which engages in the mating contour of the stator carrier, the direction of its longitudinal extension with an axis containing the axis of rotation which is oriented orthogonally to the radial longitudinal extension of the rotor blade which includes the gap with the stator segment, an angle a limited, for which the following applies: 0 ° <α <90 ° or 90 ° <α <180 °.
Figure 00000001
EP00810683A 1999-08-12 2000-07-31 Tip clearance control between rotor and stator of a turbomachine Withdrawn EP1076161A3 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19938274 1999-08-12
DE19938274A DE19938274A1 (en) 1999-08-12 1999-08-12 Device and method for drawing the gap between the stator and rotor arrangement of a turbomachine

Publications (2)

Publication Number Publication Date
EP1076161A2 EP1076161A2 (en) 2001-02-14
EP1076161A3 true EP1076161A3 (en) 2004-01-14

Family

ID=7918205

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00810683A Withdrawn EP1076161A3 (en) 1999-08-12 2000-07-31 Tip clearance control between rotor and stator of a turbomachine

Country Status (3)

Country Link
US (1) US6406256B1 (en)
EP (1) EP1076161A3 (en)
DE (1) DE19938274A1 (en)

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US6514041B1 (en) * 2001-09-12 2003-02-04 Alstom (Switzerland) Ltd Carrier for guide vane and heat shield segment
US6877952B2 (en) * 2002-09-09 2005-04-12 Florida Turbine Technologies, Inc Passive clearance control
US6883807B2 (en) 2002-09-13 2005-04-26 Seimens Westinghouse Power Corporation Multidirectional turbine shim seal
US6733234B2 (en) 2002-09-13 2004-05-11 Siemens Westinghouse Power Corporation Biased wear resistant turbine seal assembly
DE10247355A1 (en) * 2002-10-10 2004-04-22 Rolls-Royce Deutschland Ltd & Co Kg Turbine shroud segment attachment
DE10251752C1 (en) * 2002-11-05 2003-10-30 Klaus-Peter Priebe Self-regulating turbine set with turbine geometry matched to optimal operating efficiency for differing gas or steam quantities, temperatures and pressures
US6926495B2 (en) * 2003-09-12 2005-08-09 Siemens Westinghouse Power Corporation Turbine blade tip clearance control device
US6896484B2 (en) * 2003-09-12 2005-05-24 Siemens Westinghouse Power Corporation Turbine engine sealing device
US7128522B2 (en) * 2003-10-28 2006-10-31 Pratt & Whitney Canada Corp. Leakage control in a gas turbine engine
DE10356586A1 (en) * 2003-12-04 2005-07-07 Alstom Technology Ltd compressor rotor
GB2416194B (en) * 2004-07-15 2006-08-16 Rolls Royce Plc A spacer arrangement
US7195452B2 (en) * 2004-09-27 2007-03-27 Honeywell International, Inc. Compliant mounting system for turbine shrouds
DE102005013798A1 (en) * 2005-03-24 2006-09-28 Alstom Technology Ltd. Heat release segment for sealing a flow channel of a flow rotary machine
EP1717419B1 (en) 2005-04-28 2010-10-13 Siemens Aktiengesellschaft Method and device for adjustement of a radial clearance of a compressor of an axial turbomachine
US7686575B2 (en) * 2006-08-17 2010-03-30 Siemens Energy, Inc. Inner ring with independent thermal expansion for mounting gas turbine flow path components
US9039358B2 (en) * 2007-01-03 2015-05-26 United Technologies Corporation Replaceable blade outer air seal design
DE102007051027A1 (en) * 2007-10-25 2009-04-30 Mtu Aero Engines Gmbh Turbomachine, gap measuring system and method for determining a rotor gap
US8021103B2 (en) 2008-10-29 2011-09-20 General Electric Company Pressure activated flow path seal for a steam turbine
US8052380B2 (en) * 2008-10-29 2011-11-08 General Electric Company Thermally-activated clearance reduction for a steam turbine
US8128344B2 (en) * 2008-11-05 2012-03-06 General Electric Company Methods and apparatus involving shroud cooling
GB0910070D0 (en) * 2009-06-12 2009-07-22 Rolls Royce Plc System and method for adjusting rotor-stator clearance
US8337151B2 (en) * 2009-06-30 2012-12-25 General Electric Company System and method for aligning turbine components
US9062565B2 (en) * 2009-12-31 2015-06-23 Rolls-Royce Corporation Gas turbine engine containment device
EP2495399B1 (en) 2011-03-03 2016-11-23 Safran Aero Booster S.A. Segmented shroud assembly suitable for compensating a rotor misalignment relative to the stator
US9464536B2 (en) 2012-10-18 2016-10-11 General Electric Company Sealing arrangement for a turbine system and method of sealing between two turbine components
US9759082B2 (en) 2013-03-12 2017-09-12 Rolls-Royce Corporation Turbine blade track assembly
EP2971588A1 (en) 2013-03-13 2016-01-20 Rolls-Royce Corporation Dovetail retention system for blade tracks
US9506356B2 (en) * 2013-03-15 2016-11-29 Rolls-Royce North American Technologies, Inc. Composite retention feature
US20160123172A1 (en) 2013-06-11 2016-05-05 General Electric Company Passive control of gas turbine clearances using ceramic matrix composites inserts
EP3044425B1 (en) * 2013-09-11 2021-03-10 United Technologies Corporation Blade outer air seal having angled retention hook
US9488063B2 (en) * 2013-09-12 2016-11-08 General Electric Company Clearance control system for a rotary machine and method of controlling a clearance
FR3011034B1 (en) * 2013-09-25 2015-10-30 Snecma GAME LIMITING DEVICE FOR TURBOMACHINE
JP6804305B2 (en) 2014-06-12 2020-12-23 ゼネラル・エレクトリック・カンパニイ Shroud hanger assembly
FR3036436B1 (en) * 2015-05-22 2020-01-24 Safran Ceramics TURBINE RING ASSEMBLY WITH HOLDING BY FLANGES
US10563531B2 (en) * 2016-03-16 2020-02-18 United Technologies Corporation Seal assembly for gas turbine engine
US10138749B2 (en) 2016-03-16 2018-11-27 United Technologies Corporation Seal anti-rotation feature
US10107129B2 (en) * 2016-03-16 2018-10-23 United Technologies Corporation Blade outer air seal with spring centering
EP3228837B1 (en) * 2016-04-08 2019-08-28 Ansaldo Energia Switzerland AG Assembly of turboengine components
US10196918B2 (en) * 2016-06-07 2019-02-05 United Technologies Corporation Blade outer air seal made of ceramic matrix composite
EP3330498B1 (en) * 2016-11-30 2020-01-08 Rolls-Royce Corporation Turbine shroud with hanger attachment
US10655491B2 (en) 2017-02-22 2020-05-19 Rolls-Royce Corporation Turbine shroud ring for a gas turbine engine with radial retention features
US11761343B2 (en) * 2019-03-13 2023-09-19 Rtx Corporation BOAS carrier with dovetail attachments
US11248482B2 (en) 2019-07-19 2022-02-15 Raytheon Technologies Corporation CMC BOAS arrangement
US11073037B2 (en) 2019-07-19 2021-07-27 Raytheon Technologies Corporation CMC BOAS arrangement
US11073038B2 (en) 2019-07-19 2021-07-27 Raytheon Technologies Corporation CMC BOAS arrangement
US11105214B2 (en) * 2019-07-19 2021-08-31 Raytheon Technologies Corporation CMC BOAS arrangement

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US4728257A (en) * 1986-06-18 1988-03-01 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Thermal stress minimized, two component, turbine shroud seal
EP0381895A1 (en) * 1989-02-10 1990-08-16 ROLLS-ROYCE plc A blade tip clearance control arrangement for a gas turbine engine
EP0528520A1 (en) * 1991-06-24 1993-02-24 General Electric Company Compressor stator
US5616003A (en) * 1993-10-27 1997-04-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbine engine equipped with means for controlling the play between the rotor and stator
FR2761119A1 (en) * 1997-03-20 1998-09-25 Snecma Stator for axial=flow compressor, e.g. for aircraft

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US4642024A (en) * 1984-12-05 1987-02-10 United Technologies Corporation Coolable stator assembly for a rotary machine
FR2597921A1 (en) * 1986-04-24 1987-10-30 Snecma SECTORIZED TURBINE RING
US5228828A (en) * 1991-02-15 1993-07-20 General Electric Company Gas turbine engine clearance control apparatus
GB9103809D0 (en) * 1991-02-23 1991-04-10 Rolls Royce Plc Blade tip clearance control apparatus
US5333995A (en) * 1993-08-09 1994-08-02 General Electric Company Wear shim for a turbine engine
US5738490A (en) * 1996-05-20 1998-04-14 Pratt & Whitney Canada, Inc. Gas turbine engine shroud seals

Patent Citations (5)

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US4728257A (en) * 1986-06-18 1988-03-01 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Thermal stress minimized, two component, turbine shroud seal
EP0381895A1 (en) * 1989-02-10 1990-08-16 ROLLS-ROYCE plc A blade tip clearance control arrangement for a gas turbine engine
EP0528520A1 (en) * 1991-06-24 1993-02-24 General Electric Company Compressor stator
US5616003A (en) * 1993-10-27 1997-04-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbine engine equipped with means for controlling the play between the rotor and stator
FR2761119A1 (en) * 1997-03-20 1998-09-25 Snecma Stator for axial=flow compressor, e.g. for aircraft

Also Published As

Publication number Publication date
DE19938274A1 (en) 2001-02-15
EP1076161A2 (en) 2001-02-14
US6406256B1 (en) 2002-06-18

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