JP4671516B2 - タービン・シュラウド内の温度勾配を最小にする方法と装置 - Google Patents

タービン・シュラウド内の温度勾配を最小にする方法と装置 Download PDF

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Publication number
JP4671516B2
JP4671516B2 JP2001065848A JP2001065848A JP4671516B2 JP 4671516 B2 JP4671516 B2 JP 4671516B2 JP 2001065848 A JP2001065848 A JP 2001065848A JP 2001065848 A JP2001065848 A JP 2001065848A JP 4671516 B2 JP4671516 B2 JP 4671516B2
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JP
Japan
Prior art keywords
thickness
rear plate
shroud
abradable material
low pressure
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.)
Expired - Fee Related
Application number
JP2001065848A
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English (en)
Japanese (ja)
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JP2001271607A5 (enExample
JP2001271607A (ja
Inventor
フレデリック・ジョセフ・ゼガルスキー
ジョン・シェリル・カーペンター
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General Electric Co
Original Assignee
General Electric Co
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Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of JP2001271607A publication Critical patent/JP2001271607A/ja
Publication of JP2001271607A5 publication Critical patent/JP2001271607A5/ja
Application granted granted Critical
Publication of JP4671516B2 publication Critical patent/JP4671516B2/ja
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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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
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • 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
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
JP2001065848A 2000-03-10 2001-03-09 タービン・シュラウド内の温度勾配を最小にする方法と装置 Expired - Fee Related JP4671516B2 (ja)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US09/522564 2000-03-10
US09/522,564 US6341938B1 (en) 2000-03-10 2000-03-10 Methods and apparatus for minimizing thermal gradients within turbine shrouds

Publications (3)

Publication Number Publication Date
JP2001271607A JP2001271607A (ja) 2001-10-05
JP2001271607A5 JP2001271607A5 (enExample) 2008-04-24
JP4671516B2 true JP4671516B2 (ja) 2011-04-20

Family

ID=24081372

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2001065848A Expired - Fee Related JP4671516B2 (ja) 2000-03-10 2001-03-09 タービン・シュラウド内の温度勾配を最小にする方法と装置

Country Status (4)

Country Link
US (1) US6341938B1 (enExample)
EP (1) EP1132576B1 (enExample)
JP (1) JP4671516B2 (enExample)
DE (1) DE60118300T2 (enExample)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6467339B1 (en) * 2000-07-13 2002-10-22 United Technologies Corporation Method for deploying shroud segments in a turbine engine
FR2835563B1 (fr) * 2002-02-07 2004-04-02 Snecma Moteurs Agencement d'accrochage de secteurs en arc de cercle de distributeur porteur d'aubes
JP4269829B2 (ja) 2003-07-04 2009-05-27 株式会社Ｉｈｉ シュラウドセグメント
WO2005003518A1 (en) * 2003-07-04 2005-01-13 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbine shroud segment
WO2005003519A1 (en) * 2003-07-04 2005-01-13 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbine shroud segment
JP4285134B2 (ja) * 2003-07-04 2009-06-24 株式会社Ｉｈｉ シュラウドセグメント
US7255929B2 (en) * 2003-12-12 2007-08-14 General Electric Company Use of spray coatings to achieve non-uniform seal clearances in turbomachinery
US8074998B2 (en) * 2006-05-05 2011-12-13 The Texas A&M University System Annular seals for non-contact sealing of fluids in turbomachinery
US8608424B2 (en) * 2009-10-09 2013-12-17 General Electric Company Contoured honeycomb seal for a turbomachine
US9080459B2 (en) * 2012-01-03 2015-07-14 General Electric Company Forward step honeycomb seal for turbine shroud
US9097136B2 (en) * 2012-01-03 2015-08-04 General Electric Company Contoured honeycomb seal for turbine shroud
US9238977B2 (en) * 2012-11-21 2016-01-19 General Electric Company Turbine shroud mounting and sealing arrangement
US20140271142A1 (en) 2013-03-14 2014-09-18 General Electric Company Turbine Shroud with Spline Seal
FR3025124B1 (fr) * 2014-08-28 2016-09-30 Snecma Procede de fabrication de supports d'anneaux d'organe de turbomachine
EP3375980B1 (de) * 2017-03-13 2019-12-11 MTU Aero Engines GmbH Dichtungsträger für eine strömungsmaschine
JP6864510B2 (ja) * 2017-03-17 2021-04-28 三菱重工航空エンジン株式会社 シール支持リングおよびシール構造
US10774670B2 (en) * 2017-06-07 2020-09-15 General Electric Company Filled abradable seal component and associated methods thereof
US10753222B2 (en) 2017-09-11 2020-08-25 Raytheon Technologies Corporation Gas turbine engine blade outer air seal
FR3071273B1 (fr) * 2017-09-21 2019-08-30 Safran Aircraft Engines Ensemble d'etancheite de turbine pour turbomachine

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3907455A (en) * 1974-02-07 1975-09-23 United Technologies Corp Intermediate compressor case for gas turbine engines
GB1485032A (en) * 1974-08-23 1977-09-08 Rolls Royce Gas turbine engine casing
US4371311A (en) * 1980-04-28 1983-02-01 United Technologies Corporation Compression section for an axial flow rotary machine
JPS63154805A (ja) * 1986-12-17 1988-06-28 Mitsubishi Heavy Ind Ltd ガスタ−ビン翼先端すき間の自動最適化機構
US5314304A (en) * 1991-08-15 1994-05-24 The United States Of America As Represented By The Secretary Of The Air Force Abradeable labyrinth stator seal
US5188507A (en) * 1991-11-27 1993-02-23 General Electric Company Low-pressure turbine shroud
US5201846A (en) * 1991-11-29 1993-04-13 General Electric Company Low-pressure turbine heat shield
GB2310255B (en) * 1996-02-13 1999-06-16 Rolls Royce Plc A turbomachine
US5749701A (en) * 1996-10-28 1998-05-12 General Electric Company Interstage seal assembly for a turbine
US6120242A (en) * 1998-11-13 2000-09-19 General Electric Company Blade containing turbine shroud

Also Published As

Publication number Publication date
EP1132576B1 (en) 2006-03-29
EP1132576A2 (en) 2001-09-12
DE60118300T2 (de) 2006-11-30
JP2001271607A (ja) 2001-10-05
US6341938B1 (en) 2002-01-29
EP1132576A3 (en) 2003-09-17
DE60118300D1 (de) 2006-05-18

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