FR3081911B1 - Dispositif de refroidissement d'un carter de turbine pour turbomachine - Google Patents

Dispositif de refroidissement d'un carter de turbine pour turbomachine Download PDF

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Publication number
FR3081911B1
FR3081911B1 FR1854818A FR1854818A FR3081911B1 FR 3081911 B1 FR3081911 B1 FR 3081911B1 FR 1854818 A FR1854818 A FR 1854818A FR 1854818 A FR1854818 A FR 1854818A FR 3081911 B1 FR3081911 B1 FR 3081911B1
Authority
FR
France
Prior art keywords
tube
cooling device
distal end
turbomachine
cooling
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
FR1854818A
Other languages
English (en)
Other versions
FR3081911A1 (fr
Inventor
Josselin Luc Florent Sicard
Simon Jose Pierre Amoedo
Olivier Arnaud Fabien Lambert
Cyrille Telman
Pierre Vincent
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
Safran Aircraft Engines 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 Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1854818A priority Critical patent/FR3081911B1/fr
Publication of FR3081911A1 publication Critical patent/FR3081911A1/fr
Application granted granted Critical
Publication of FR3081911B1 publication Critical patent/FR3081911B1/fr
Active legal-status Critical Current
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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20Actively adjusting tip-clearance
    • F01D11/24Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08Cooling; Heating; Heat-insulation
    • F01D25/14Casings modified therefor
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00Geometry
    • F05D2250/10Two-dimensional
    • F05D2250/14Two-dimensional elliptical
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00Geometry
    • F05D2250/10Two-dimensional
    • F05D2250/14Two-dimensional elliptical
    • F05D2250/141Two-dimensional elliptical circular
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00Function
    • F05D2260/20Heat transfer, e.g. cooling
    • F05D2260/201Heat transfer, e.g. cooling by impingement of a fluid
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/60Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un dispositif de refroidissement (100) s'étendant autour d'un axe (X) et destiné à refroidir un carter (7) coaxial de turbine (1) pour une turbomachine, le dispositif de refroidissement (100) comportant des moyens de prélèvement et d'amenée d'air (110) reliés à un boitier (119) de répartition, et au moins un tube (120) de refroidissement s'étendant circonférentiellement autour de l'axe (X) à partir du boitier (119), ledit au moins un tube (120) comportant une pluralité d'orifices primaires (123), répartis le long du tube (120) et qui sont destinés à refroidir le carter (7) à partir de l'air provenant du boitier (119) entre une extrémité proximale (121) du tube (120) située au niveau du boitier (119) et une extrémité distale (122) du tube (120), le dispositif de refroidissement (100) étant caractérisé en ce que le tube (120) comporte à son extrémité distale (122) un orifice secondaire (124) pour créer une circulation d'air au niveau de l'extrémité distale (122) du tube (120), l'orifice secondaire (124) délimitant une ouverture ayant une section supérieure à la section de l'ouverture de chaque orifice primaire (123).
FR1854818A 2018-06-04 2018-06-04 Dispositif de refroidissement d'un carter de turbine pour turbomachine Active FR3081911B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1854818A FR3081911B1 (fr) 2018-06-04 2018-06-04 Dispositif de refroidissement d'un carter de turbine pour turbomachine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1854818A FR3081911B1 (fr) 2018-06-04 2018-06-04 Dispositif de refroidissement d'un carter de turbine pour turbomachine
FR1854818 2018-06-04

Publications (2)

Publication Number Publication Date
FR3081911A1 FR3081911A1 (fr) 2019-12-06
FR3081911B1 true FR3081911B1 (fr) 2021-05-28

Family

ID=62952141

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1854818A Active FR3081911B1 (fr) 2018-06-04 2018-06-04 Dispositif de refroidissement d'un carter de turbine pour turbomachine

Country Status (1)

Country Link
FR (1) FR3081911B1 (fr)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5100291A (en) * 1990-03-28 1992-03-31 General Electric Company Impingement manifold
FR2867806B1 (fr) * 2004-03-18 2006-06-02 Snecma Moteurs Dispositif de pilotage de jeu de turbine a gaz a equilibrage des debits d'air
US20130028705A1 (en) * 2011-07-26 2013-01-31 Ken Lagueux Gas turbine engine active clearance control
FR3050228B1 (fr) * 2016-04-18 2019-03-29 Safran Aircraft Engines Dispositif de refroidissement par jets d'air d'un carter de turbine
FR3054000B1 (fr) * 2016-07-15 2020-02-14 Safran Aircraft Engines Dispositif de refroidissement d'un carter de turbine pour une turbomachine

Also Published As

Publication number Publication date
FR3081911A1 (fr) 2019-12-06

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