DE602006004235D1 - Einrichtung zur Veränderung des Durchtrittsquerschnitts bei einem Turbinenleitapparat - Google Patents

Einrichtung zur Veränderung des Durchtrittsquerschnitts bei einem Turbinenleitapparat

Info

Publication number
DE602006004235D1
DE602006004235D1 DE602006004235T DE602006004235T DE602006004235D1 DE 602006004235 D1 DE602006004235 D1 DE 602006004235D1 DE 602006004235 T DE602006004235 T DE 602006004235T DE 602006004235 T DE602006004235 T DE 602006004235T DE 602006004235 D1 DE602006004235 D1 DE 602006004235D1
Authority
DE
Germany
Prior art keywords
changing
section
passage cross
turbine nozzle
turbine
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.)
Active
Application number
DE602006004235T
Other languages
English (en)
Inventor
Gilles Charier
Claude Nottin
Stephane Rousselin
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of DE602006004235D1 publication Critical patent/DE602006004235D1/de
Active 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • F05D2300/5021—Expansivity
    • F05D2300/50212—Expansivity dissimilar

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
DE602006004235T 2005-02-22 2006-02-21 Einrichtung zur Veränderung des Durchtrittsquerschnitts bei einem Turbinenleitapparat Active DE602006004235D1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0501768A FR2882394B1 (fr) 2005-02-22 2005-02-22 Dispositif de variation de la section de col d'un distributeur de turbine

Publications (1)

Publication Number Publication Date
DE602006004235D1 true DE602006004235D1 (de) 2009-01-29

Family

ID=34954654

Family Applications (1)

Application Number Title Priority Date Filing Date
DE602006004235T Active DE602006004235D1 (de) 2005-02-22 2006-02-21 Einrichtung zur Veränderung des Durchtrittsquerschnitts bei einem Turbinenleitapparat

Country Status (6)

Country Link
US (1) US7553126B2 (de)
EP (1) EP1703084B1 (de)
JP (1) JP4637764B2 (de)
DE (1) DE602006004235D1 (de)
FR (1) FR2882394B1 (de)
RU (1) RU2396437C2 (de)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2889863B1 (fr) * 2005-08-22 2007-11-02 Snecma Compresseur comportant une pluralite de caissons reconstituant un volume annulaire de separation de flux dans une turbomachine.
AT503840B1 (de) * 2006-06-30 2010-09-15 Facc Ag Leitschaufelanordnung für ein triebwerk
DE102006050907A1 (de) * 2006-10-28 2008-05-15 Man Turbo Ag Leitvorrichtung einer Strömungsmaschine sowie Leitschaufel für eine derartige Leitvorrichtung
EP2474709A1 (de) * 2011-01-05 2012-07-11 Siemens Aktiengesellschaft Leitschaufelkranz für eine Dampfturbine mit einer Feinjustage der Schluckfähigkeit und zugehöriges Verfahren
DE102011082131A1 (de) * 2011-09-05 2013-03-07 Siemens Aktiengesellschaft Leitvorrichtung für eine Turbine
US9045984B2 (en) 2012-05-31 2015-06-02 United Technologies Corporation Stator vane mistake proofing
US9500122B2 (en) 2013-06-28 2016-11-22 General Electric Company Variable geometry nozzle and associated method of operation
US10662792B2 (en) * 2014-02-03 2020-05-26 Raytheon Technologies Corporation Gas turbine engine cooling fluid composite tube
JP6302368B2 (ja) * 2014-06-27 2018-03-28 三菱日立パワーシステムズ株式会社 静翼及び静翼ユニット、蒸気タービン
EP2998517B1 (de) * 2014-09-16 2019-03-27 Ansaldo Energia Switzerland AG Dichtungsanordnung an der Schnittstelle zwischen einer Brennkammer und einer Turbine einer Gasturbine sowie Gasturbine mit solch einer Dichtungsanordnung
US10655482B2 (en) * 2015-02-05 2020-05-19 Rolls-Royce Corporation Vane assemblies for gas turbine engines
JP6546481B2 (ja) * 2015-08-31 2019-07-17 川崎重工業株式会社 排気ディフューザ
DE102016217320A1 (de) * 2016-09-12 2018-03-15 Siemens Aktiengesellschaft Gasturbine mit getrennter Kühlung für Turbine und Abgasgehäuse
FR3074840B1 (fr) * 2017-12-11 2021-01-08 Safran Aircraft Engines Distributeur de turbomachine a etancheite amelioree
US10934883B2 (en) * 2018-09-12 2021-03-02 Raytheon Technologies Cover for airfoil assembly for a gas turbine engine

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2914300A (en) * 1955-12-22 1959-11-24 Gen Electric Nozzle vane support for turbines
GB1242534A (en) * 1967-08-15 1971-08-11 Rolls Royce Bladed fluid flow machine
US3966353A (en) * 1975-02-21 1976-06-29 Westinghouse Electric Corporation Ceramic-to-metal (or ceramic) cushion/seal for use with three piece ceramic stationary vane assembly
FR2576974B1 (fr) * 1985-02-06 1989-02-03 Snecma Dispositif de variation de section du col d'un distributeur de turbine
JPS61250303A (ja) * 1985-04-26 1986-11-07 Toshiba Corp 軸流タ−ボ機械の可変ノズル装置
US4768924A (en) * 1986-07-22 1988-09-06 Pratt & Whitney Canada Inc. Ceramic stator vane assembly
US5301500A (en) * 1990-07-09 1994-04-12 General Electric Company Gas turbine engine for controlling stall margin
FR2708311B1 (fr) * 1993-07-28 1995-09-01 Snecma Stator de turbomachine à aubes pivotantes et anneau de commande.
US5931636A (en) * 1997-08-28 1999-08-03 General Electric Company Variable area turbine nozzle
JP4275081B2 (ja) * 2005-02-10 2009-06-10 三菱重工業株式会社 可変容量型排気ターボ過給機のスクロール構造及びその製造方法

Also Published As

Publication number Publication date
EP1703084B1 (de) 2008-12-17
FR2882394A1 (fr) 2006-08-25
FR2882394B1 (fr) 2007-05-18
US20060188369A1 (en) 2006-08-24
RU2006105523A (ru) 2007-12-27
JP4637764B2 (ja) 2011-02-23
EP1703084A1 (de) 2006-09-20
JP2006233967A (ja) 2006-09-07
RU2396437C2 (ru) 2010-08-10
US7553126B2 (en) 2009-06-30

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Legal Events

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8364 No opposition during term of opposition