FR3066228B1 - Limitation du deplacement d'un tube de liaison par engagement d'une portion incurvee de paroi d'enceinte pour turbomachine - Google Patents

Limitation du deplacement d'un tube de liaison par engagement d'une portion incurvee de paroi d'enceinte pour turbomachine Download PDF

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Publication number
FR3066228B1
FR3066228B1 FR1754218A FR1754218A FR3066228B1 FR 3066228 B1 FR3066228 B1 FR 3066228B1 FR 1754218 A FR1754218 A FR 1754218A FR 1754218 A FR1754218 A FR 1754218A FR 3066228 B1 FR3066228 B1 FR 3066228B1
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FR
France
Prior art keywords
connecting tube
movement
engaging
limitation
curved portion
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
FR1754218A
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English (en)
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FR3066228A1 (fr
Inventor
Nicolas Daniel Delaporte
Anthony Pierre Beguin
Didier Noel Durand
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 FR1754218A priority Critical patent/FR3066228B1/fr
Publication of FR3066228A1 publication Critical patent/FR3066228A1/fr
Application granted granted Critical
Publication of FR3066228B1 publication Critical patent/FR3066228B1/fr
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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
    • F01D9/00Stators
    • F01D9/06Fluid supply conduits to nozzles or the like
    • F01D9/065Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F01D11/005Sealing means between non relatively rotating elements
    • 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
    • F01D5/00Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12Blades
    • F01D5/14Form or construction
    • F01D5/18Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187Convection cooling
    • 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
    • F05D2260/30Retaining components in desired mutual position
    • 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)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un ensemble de raccordement d'un distributeur pour turbomachine à une enceinte (6) de circulation de fluide de refroidissement. L'ensemble comprend un tube de liaison (8) et une paroi interne (17). Le tube de liaison (8) est configuré pour raccorder une première paroi (13) de l'enceinte et à une paroi (40) du distributeur, de manière mobile au moins le long de l'axe longitudinal (X-X) du tube de liaison. La paroi interne (17) comprend un élément de paroi incurvé (20) qui est destiné à entourer au moins partiellement le tube de liaison (8), pour limiter le déplacement du tube de liaison (8) le long de son axe longitudinal (X-X) par contact du tube de liaison (8) avec l'élément de paroi incurvé (20).
FR1754218A 2017-05-12 2017-05-12 Limitation du deplacement d'un tube de liaison par engagement d'une portion incurvee de paroi d'enceinte pour turbomachine Active FR3066228B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1754218A FR3066228B1 (fr) 2017-05-12 2017-05-12 Limitation du deplacement d'un tube de liaison par engagement d'une portion incurvee de paroi d'enceinte pour turbomachine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1754218 2017-05-12
FR1754218A FR3066228B1 (fr) 2017-05-12 2017-05-12 Limitation du deplacement d'un tube de liaison par engagement d'une portion incurvee de paroi d'enceinte pour turbomachine

Publications (2)

Publication Number Publication Date
FR3066228A1 FR3066228A1 (fr) 2018-11-16
FR3066228B1 true FR3066228B1 (fr) 2021-06-11

Family

ID=59811438

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1754218A Active FR3066228B1 (fr) 2017-05-12 2017-05-12 Limitation du deplacement d'un tube de liaison par engagement d'une portion incurvee de paroi d'enceinte pour turbomachine

Country Status (1)

Country Link
FR (1) FR3066228B1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3095232B1 (fr) * 2019-04-16 2022-06-03 Safran Aircraft Engines Ensemble pour une turbine de turbomachine

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH10238301A (ja) * 1997-02-21 1998-09-08 Mitsubishi Heavy Ind Ltd ガスタービン翼の冷却通路
ITMI991208A1 (it) * 1999-05-31 2000-12-01 Nuovo Pignone Spa Dispositivo per il posizionamento di ugelli di uno stadio statorico eper il raffreddamento di dischi rotorici in turbine a gas
US6884023B2 (en) * 2002-09-27 2005-04-26 United Technologies Corporation Integral swirl knife edge injection assembly
FR2862338B1 (fr) * 2003-11-17 2007-07-20 Snecma Moteurs Dispositif de liaison entre un distributeur et une enceinte d'alimentation pour injecteurs de fluide de refroidissement dans une turbomachine
FR3000522B1 (fr) * 2012-12-27 2018-11-02 Safran Aircraft Engines Dispositif de liaison a double tube

Also Published As

Publication number Publication date
FR3066228A1 (fr) 2018-11-16

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