CA2061939A1 - Cooled shroud support - Google Patents

Cooled shroud support

Info

Publication number
CA2061939A1
CA2061939A1 CA002061939A CA2061939A CA2061939A1 CA 2061939 A1 CA2061939 A1 CA 2061939A1 CA 002061939 A CA002061939 A CA 002061939A CA 2061939 A CA2061939 A CA 2061939A CA 2061939 A1 CA2061939 A1 CA 2061939A1
Authority
CA
Canada
Prior art keywords
hanger
shroud
circumferentially
flow duct
shroud support
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
CA002061939A
Other languages
French (fr)
Other versions
CA2061939C (en
Inventor
Peter Joseph Rock
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 Co
Original Assignee
Peter Joseph Rock
General Electric Company
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 Peter Joseph Rock, General Electric Company filed Critical Peter Joseph Rock
Publication of CA2061939A1 publication Critical patent/CA2061939A1/en
Application granted granted Critical
Publication of CA2061939C publication Critical patent/CA2061939C/en
Anticipated expiration legal-status Critical
Expired - Fee Related 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

Abstract

A shroud support includes an annular casing and an annular hanger spaced radially inwardly therefrom. The hanger includes a circumferentially extending flow duct therein and a base for radially supporting a shroud positionable radially over a plurality of circumferentially spaced turbine blades. The hanger is cooled by channeling a cooling fluid circumferentially inside the hanger flow duct for providing more uniform circumferential blade tip clearance and for better matching the thermal movement between the shroud and blade tips.
CA002061939A 1991-03-11 1992-02-27 Cooled shroud support Expired - Fee Related CA2061939C (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US07/666,959 US5167487A (en) 1991-03-11 1991-03-11 Cooled shroud support
US666,959 1991-03-11

Publications (2)

Publication Number Publication Date
CA2061939A1 true CA2061939A1 (en) 1992-09-12
CA2061939C CA2061939C (en) 2002-05-28

Family

ID=24676243

Family Applications (1)

Application Number Title Priority Date Filing Date
CA002061939A Expired - Fee Related CA2061939C (en) 1991-03-11 1992-02-27 Cooled shroud support

Country Status (6)

Country Link
US (1) US5167487A (en)
EP (1) EP0503752B1 (en)
JP (1) JPH0751888B2 (en)
CA (1) CA2061939C (en)
DE (1) DE69210077T2 (en)
IL (1) IL100515A0 (en)

Families Citing this family (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5927942A (en) * 1993-10-27 1999-07-27 United Technologies Corporation Mounting and sealing arrangement for a turbine shroud segment
US5380150A (en) * 1993-11-08 1995-01-10 United Technologies Corporation Turbine shroud segment
US5540547A (en) * 1994-06-23 1996-07-30 General Electric Company Method and apparatus for damping vibrations of external tubing of a gas turbine engine
US5639210A (en) * 1995-10-23 1997-06-17 United Technologies Corporation Rotor blade outer tip seal apparatus
US5813830A (en) * 1996-02-09 1998-09-29 Allison Engine Company, Inc. Carbon seal contaminant barrier system
DE29714742U1 (en) * 1997-08-18 1998-12-17 Siemens Ag Heat shield component with cooling fluid return and heat shield arrangement for a hot gas-carrying component
US6139257A (en) * 1998-03-23 2000-10-31 General Electric Company Shroud cooling assembly for gas turbine engine
US6626635B1 (en) * 1998-09-30 2003-09-30 General Electric Company System for controlling clearance between blade tips and a surrounding casing in rotating machinery
US6902371B2 (en) * 2002-07-26 2005-06-07 General Electric Company Internal low pressure turbine case cooling
DE10352089A1 (en) * 2003-11-07 2005-06-09 Alstom Technology Ltd Method for operating a turbomachine, and turbomachinery
US7147432B2 (en) * 2003-11-24 2006-12-12 General Electric Company Turbine shroud asymmetrical cooling elements
US6997673B2 (en) * 2003-12-11 2006-02-14 Honeywell International, Inc. Gas turbine high temperature turbine blade outer air seal assembly
US7588412B2 (en) * 2005-07-28 2009-09-15 General Electric Company Cooled shroud assembly and method of cooling a shroud
US7771160B2 (en) * 2006-08-10 2010-08-10 United Technologies Corporation Ceramic shroud assembly
US7665960B2 (en) 2006-08-10 2010-02-23 United Technologies Corporation Turbine shroud thermal distortion control
US7918642B2 (en) * 2007-01-10 2011-04-05 United Technologies Corporation Instrument port seal for RF measurement
EP2674579B1 (en) 2008-10-08 2018-01-17 MITSUBISHI HEAVY INDUSTRIES, Ltd. Gas turbine and operating method thereof
US8172521B2 (en) * 2009-01-15 2012-05-08 General Electric Company Compressor clearance control system using turbine exhaust
US8206085B2 (en) * 2009-03-12 2012-06-26 General Electric Company Turbine engine shroud ring
US8167546B2 (en) * 2009-09-01 2012-05-01 United Technologies Corporation Ceramic turbine shroud support
US8915701B2 (en) * 2011-09-08 2014-12-23 General Electric Company Piping assembly and method for connecting inner and outer shell in turbine system
CN102606312B (en) * 2012-04-10 2014-07-09 北京航空航天大学 Cooling method used for segmented geometric adjustment of guide vanes of gas turbine
US9568009B2 (en) 2013-03-11 2017-02-14 Rolls-Royce Corporation Gas turbine engine flow path geometry
US9279339B2 (en) * 2013-03-13 2016-03-08 Siemens Aktiengesellschaft Turbine engine temperature control system with heating element for a gas turbine engine
WO2014143311A1 (en) * 2013-03-14 2014-09-18 Uskert Richard C Turbine shrouds
CA2951425C (en) * 2014-06-12 2019-12-24 General Electric Company Shroud hanger assembly
CN106089324B (en) * 2016-06-07 2018-05-01 中国南方航空工业(集团)有限公司 stator casing sealing structure
US10753232B2 (en) 2017-06-16 2020-08-25 General Electric Company Assemblies and methods for cooling flowpath support structure and flowpath components
US11111809B2 (en) * 2018-05-14 2021-09-07 Raytheon Technologies Corporation Electric heating for turbomachinery clearance control
US10760444B2 (en) 2018-05-14 2020-09-01 Raytheon Technologies Corporation Electric heating for turbomachinery clearance control powered by hybrid energy storage system
US10907501B2 (en) * 2018-08-21 2021-02-02 General Electric Company Shroud hanger assembly cooling

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH299035A (en) * 1942-08-12 1954-05-31 Vorkauf Heinrich Cooled gas turbine rotor.
US2402841A (en) * 1944-06-26 1946-06-25 Allis Chalmers Mfg Co Elastic fluid turbine apparatus
US2940660A (en) * 1956-04-11 1960-06-14 Alfred M Caddell Compressor with air cooler between stages
BE756582A (en) * 1969-10-02 1971-03-01 Gen Electric CIRCULAR SCREEN AND SCREEN HOLDER WITH TEMPERATURE ADJUSTMENT FOR TURBOMACHINE
US3807891A (en) * 1972-09-15 1974-04-30 United Aircraft Corp Thermal response turbine shroud
US4127357A (en) * 1977-06-24 1978-11-28 General Electric Company Variable shroud for a turbomachine
US4303371A (en) * 1978-06-05 1981-12-01 General Electric Company Shroud support with impingement baffle
GB2047354B (en) * 1979-04-26 1983-03-30 Rolls Royce Gas turbine engines
DE2917137A1 (en) * 1979-04-27 1980-11-06 Luk Lamellen & Kupplungsbau DEVICE FOR SELECTIVELY DISCONNECTING AND CONNECTING A ROTATING SHAFT
US4573865A (en) * 1981-08-31 1986-03-04 General Electric Company Multiple-impingement cooled structure
GB2117451B (en) * 1982-03-05 1985-11-06 Rolls Royce Gas turbine shroud
GB2125111B (en) * 1982-03-23 1985-06-05 Rolls Royce Shroud assembly for a gas turbine engine
US4573866A (en) * 1983-05-02 1986-03-04 United Technologies Corporation Sealed shroud for rotating body
US4553901A (en) * 1983-12-21 1985-11-19 United Technologies Corporation Stator structure for a gas turbine engine
FR2576637B1 (en) * 1985-01-30 1988-11-18 Snecma GAS TURBINE RING.
FR2597921A1 (en) * 1986-04-24 1987-10-30 Snecma SECTORIZED TURBINE RING
GB2206651B (en) * 1987-07-01 1991-05-08 Rolls Royce Plc Turbine blade shroud structure

Also Published As

Publication number Publication date
JPH0751888B2 (en) 1995-06-05
IL100515A0 (en) 1992-09-06
DE69210077D1 (en) 1996-05-30
JPH04303104A (en) 1992-10-27
CA2061939C (en) 2002-05-28
EP0503752A1 (en) 1992-09-16
DE69210077T2 (en) 1996-12-19
US5167487A (en) 1992-12-01
EP0503752B1 (en) 1996-04-24

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Legal Events

Date Code Title Description
EEER Examination request
MKLA Lapsed