FR2840351B1 - Refroidissement du flasque amont d'une turbine a haute pression par un systeme a double injecteur fond de chambre - Google Patents

Refroidissement du flasque amont d'une turbine a haute pression par un systeme a double injecteur fond de chambre

Info

Publication number
FR2840351B1
FR2840351B1 FR0206600A FR0206600A FR2840351B1 FR 2840351 B1 FR2840351 B1 FR 2840351B1 FR 0206600 A FR0206600 A FR 0206600A FR 0206600 A FR0206600 A FR 0206600A FR 2840351 B1 FR2840351 B1 FR 2840351B1
Authority
FR
France
Prior art keywords
cooling
high pressure
pressure turbine
injector system
flask before
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
FR0206600A
Other languages
English (en)
Other versions
FR2840351A1 (fr
Inventor
Gerard Adam
Sylvie Coulon
Gerard Jacques Stangalini
Jean Claude Taillant
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 Moteurs SA
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 Moteurs SA filed Critical SNECMA Moteurs SA
Priority to FR0206600A priority Critical patent/FR2840351B1/fr
Priority to JP2003145777A priority patent/JP3940377B2/ja
Priority to DE60306990T priority patent/DE60306990T2/de
Priority to EP03291258A priority patent/EP1367221B1/fr
Priority to US10/445,354 priority patent/US6787947B2/en
Priority to CA2430143A priority patent/CA2430143C/fr
Priority to RU2003116095/06A priority patent/RU2318120C2/ru
Publication of FR2840351A1 publication Critical patent/FR2840351A1/fr
Application granted granted Critical
Publication of FR2840351B1 publication Critical patent/FR2840351B1/fr
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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
FR0206600A 2002-05-30 2002-05-30 Refroidissement du flasque amont d'une turbine a haute pression par un systeme a double injecteur fond de chambre Expired - Fee Related FR2840351B1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
FR0206600A FR2840351B1 (fr) 2002-05-30 2002-05-30 Refroidissement du flasque amont d'une turbine a haute pression par un systeme a double injecteur fond de chambre
JP2003145777A JP3940377B2 (ja) 2002-05-30 2003-05-23 燃焼室の端の二重インジェクタシステムによる高圧タービンの上流端プレートの冷却
EP03291258A EP1367221B1 (fr) 2002-05-30 2003-05-27 Système à double injecteurs fond de chambre pour le refroidissement du flasque amont d'une turbine à haute pression
US10/445,354 US6787947B2 (en) 2002-05-30 2003-05-27 Cooling the upstream end plate of a high pressure turbine by means of a system of dual injectors at the end of the combustion chamber
DE60306990T DE60306990T2 (de) 2002-05-30 2003-05-27 Doppeldüsenanordnung zur Kühlung der Seitenplatte einer Hochdruckturbine
CA2430143A CA2430143C (fr) 2002-05-30 2003-05-28 Refroidissement du flasque amont d'une turbine a haute pression par un systeme a double injecteurs fond de chambre
RU2003116095/06A RU2318120C2 (ru) 2002-05-30 2003-05-30 Устройство вентиляции ротора турбины высокого давления турбомашины

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0206600A FR2840351B1 (fr) 2002-05-30 2002-05-30 Refroidissement du flasque amont d'une turbine a haute pression par un systeme a double injecteur fond de chambre

Publications (2)

Publication Number Publication Date
FR2840351A1 FR2840351A1 (fr) 2003-12-05
FR2840351B1 true FR2840351B1 (fr) 2005-12-16

Family

ID=29415148

Family Applications (1)

Application Number Title Priority Date Filing Date
FR0206600A Expired - Fee Related FR2840351B1 (fr) 2002-05-30 2002-05-30 Refroidissement du flasque amont d'une turbine a haute pression par un systeme a double injecteur fond de chambre

Country Status (7)

Country Link
US (1) US6787947B2 (fr)
EP (1) EP1367221B1 (fr)
JP (1) JP3940377B2 (fr)
CA (1) CA2430143C (fr)
DE (1) DE60306990T2 (fr)
FR (1) FR2840351B1 (fr)
RU (1) RU2318120C2 (fr)

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FR2861129A1 (fr) * 2003-10-21 2005-04-22 Snecma Moteurs Dispositif de joint a labyrinthe pour moteur a turbine a gaz
GB0412476D0 (en) * 2004-06-04 2004-07-07 Rolls Royce Plc Seal system
GB2426289B (en) * 2005-04-01 2007-07-04 Rolls Royce Plc Cooling system for a gas turbine engine
DE102005025244A1 (de) * 2005-05-31 2006-12-07 Rolls-Royce Deutschland Ltd & Co Kg Luftführungssystem zwischen Verdichter und Turbine eines Gasturbinentriebwerks
GB0620430D0 (en) * 2006-10-14 2006-11-22 Rolls Royce Plc A flow cavity arrangement
FR2950656B1 (fr) * 2009-09-25 2011-09-23 Snecma Ventilation d'une roue de turbine dans une turbomachine
RU2443869C2 (ru) * 2010-02-19 2012-02-27 Вячеслав Евгеньевич Беляев Устройство для охлаждения ротора газовой турбины
US9091173B2 (en) 2012-05-31 2015-07-28 United Technologies Corporation Turbine coolant supply system
WO2014051690A1 (fr) * 2012-09-26 2014-04-03 United Technologies Corporation Jonction assemblée pour injecteur embarqué tangentiel (tobi)
US9388698B2 (en) * 2013-11-13 2016-07-12 General Electric Company Rotor cooling
EP3097292B1 (fr) 2014-01-20 2019-04-03 United Technologies Corporation Tuyau d'ajout conforme haute pression non arrondi, fixé sur cloison
EP2942483B2 (fr) * 2014-04-01 2022-09-28 Raytheon Technologies Corporation Injecteur de bord tangentiel ventilé pour un moteur à turbine à gaz
JP6174655B2 (ja) 2014-10-21 2017-08-02 ユナイテッド テクノロジーズ コーポレイションＵｎｉｔｅｄ Ｔｅｃｈｎｏｌｏｇｉｅｓ Ｃｏｒｐｏｒａｔｉｏｎ ガスタービンエンジン用のダクテッド熱交換器システム、およびガスタービンエンジン用の熱交換器の製造方法
US10450956B2 (en) 2014-10-21 2019-10-22 United Technologies Corporation Additive manufactured ducted heat exchanger system with additively manufactured fairing
JP6484430B2 (ja) * 2014-11-12 2019-03-13 三菱重工業株式会社 タービンの冷却構造及びガスタービン
EP3130750B1 (fr) * 2015-08-14 2018-03-28 Ansaldo Energia Switzerland AG Système de refroidissement de turbines à gaz
CN106523043B (zh) * 2016-12-21 2018-04-03 中国南方航空工业(集团)有限公司 燃气轮机用分气路装置及燃气轮机
US11021962B2 (en) * 2018-08-22 2021-06-01 Raytheon Technologies Corporation Turbulent air reducer for a gas turbine engine
CN111878178B (zh) * 2020-07-30 2022-10-25 中国航发湖南动力机械研究所 涡轮转盘及涡轮转子
CN112049688B (zh) * 2020-08-19 2021-08-10 西北工业大学 一种用于等半径预旋供气系统的过预旋叶型接受孔
CN112855283B (zh) * 2021-01-11 2022-05-20 中国科学院工程热物理研究所 一种可提高接收孔流量系数的发动机预旋系统
EP4450779A1 (fr) * 2023-04-18 2024-10-23 RTX Corporation Aube directrice de buse de chambre de combustion avec refroidissement intermédiaire et configuration d'air secondaire

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Publication number Priority date Publication date Assignee Title
US3575528A (en) * 1968-10-28 1971-04-20 Gen Motors Corp Turbine rotor cooling
US3832090A (en) * 1972-12-01 1974-08-27 Avco Corp Air cooling of turbine blades
SU556221A1 (ru) * 1975-11-20 1977-04-30 Уфимский авиационный институт им. Орджоникидзе Устройство дл охлаждени диска турбомашины
GB2108202B (en) * 1980-10-10 1984-05-10 Rolls Royce Air cooling systems for gas turbine engines
SU1132613A1 (ru) * 1982-10-29 1996-04-10 Производственное объединение "Турбомоторный завод" Охлаждаемый ротор турбомашины
US4526511A (en) * 1982-11-01 1985-07-02 United Technologies Corporation Attachment for TOBI
US4466239A (en) * 1983-02-22 1984-08-21 General Electric Company Gas turbine engine with improved air cooling circuit
US4807433A (en) * 1983-05-05 1989-02-28 General Electric Company Turbine cooling air modulation
US4822244A (en) * 1987-10-15 1989-04-18 United Technologies Corporation Tobi
US5143512A (en) * 1991-02-28 1992-09-01 General Electric Company Turbine rotor disk with integral blade cooling air slots and pumping vanes
US5310319A (en) * 1993-01-12 1994-05-10 United Technologies Corporation Free standing turbine disk sideplate assembly
FR2707698B1 (fr) * 1993-07-15 1995-08-25 Snecma Turbomachine munie d'un moyen de soufflage d'air sur un élément de rotor.
US5402636A (en) * 1993-12-06 1995-04-04 United Technologies Corporation Anti-contamination thrust balancing system for gas turbine engines
FR2744761B1 (fr) * 1996-02-08 1998-03-13 Snecma Disque labyrinthe avec raidisseur incorpore pour rotor de turbomachine
RU2200235C2 (ru) * 2001-02-05 2003-03-10 Открытое акционерное общество "Авиадвигатель" Ротор высокотемпературной газовой турбины

Also Published As

Publication number Publication date
RU2003116095A (ru) 2005-01-27
EP1367221A1 (fr) 2003-12-03
EP1367221B1 (fr) 2006-07-26
DE60306990T2 (de) 2007-03-08
FR2840351A1 (fr) 2003-12-05
RU2318120C2 (ru) 2008-02-27
JP3940377B2 (ja) 2007-07-04
CA2430143C (fr) 2010-10-05
CA2430143A1 (fr) 2003-11-30
US6787947B2 (en) 2004-09-07
JP2004132352A (ja) 2004-04-30
DE60306990D1 (de) 2006-09-07
US20030223893A1 (en) 2003-12-04

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Effective date: 20090119