FR3064668B1 - Dispositif d'etancheite d'une partie de rotor ou stator de turbomachine - Google Patents

Dispositif d'etancheite d'une partie de rotor ou stator de turbomachine Download PDF

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Publication number
FR3064668B1
FR3064668B1 FR1752802A FR1752802A FR3064668B1 FR 3064668 B1 FR3064668 B1 FR 3064668B1 FR 1752802 A FR1752802 A FR 1752802A FR 1752802 A FR1752802 A FR 1752802A FR 3064668 B1 FR3064668 B1 FR 3064668B1
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FR
France
Prior art keywords
sealing device
stator
axis
turbomachine rotor
coating
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
FR1752802A
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English (en)
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FR3064668A1 (fr
Inventor
Etienne Leon Francois
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.)
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Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1752802A priority Critical patent/FR3064668B1/fr
Publication of FR3064668A1 publication Critical patent/FR3064668A1/fr
Application granted granted Critical
Publication of FR3064668B1 publication Critical patent/FR3064668B1/fr
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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)

Abstract

Est concerné un dispositif d'étanchéité d'une turbomachine présentant comprenant un carter externe auquel sont fixés des blocs de matière abradable définissant un revêtement (46) interne adapté à coopérer avec des léchettes d'aubes d'un rotor tournant autour d'un axe (X). Le revêtement (46) comprenant des alvéoles (52) polygonales, liées deux à deux par des scellements (54), axialement (axe X), à l'endroit de côtés respectifs (54,56) circonférentiels du polygone, adjacents et s'étendant le long l'un de l'autre. Un dit scellement (54) s'étend circonférentiellement, sur une longueur (L1) déterminée commune desdits côtés circonférentiels respectifs où il est situé, et, circonférentiellement, une dite alvéole présente une longueur (L2) supérieure à au moins 2 fois celle (L1) d'un dit scellement.
FR1752802A 2017-03-31 2017-03-31 Dispositif d'etancheite d'une partie de rotor ou stator de turbomachine Active FR3064668B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1752802A FR3064668B1 (fr) 2017-03-31 2017-03-31 Dispositif d'etancheite d'une partie de rotor ou stator de turbomachine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1752802A FR3064668B1 (fr) 2017-03-31 2017-03-31 Dispositif d'etancheite d'une partie de rotor ou stator de turbomachine
FR1752802 2017-03-31

Publications (2)

Publication Number Publication Date
FR3064668A1 FR3064668A1 (fr) 2018-10-05
FR3064668B1 true FR3064668B1 (fr) 2020-10-09

Family

ID=59070844

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1752802A Active FR3064668B1 (fr) 2017-03-31 2017-03-31 Dispositif d'etancheite d'une partie de rotor ou stator de turbomachine

Country Status (1)

Country Link
FR (1) FR3064668B1 (fr)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3616141A (en) * 1969-12-15 1971-10-26 Hexcel Corp Formable honeycomb core and method of making the same
US4618152A (en) * 1983-01-13 1986-10-21 Thomas P. Mahoney Honeycomb seal structure
US20090072488A1 (en) * 2007-09-18 2009-03-19 Honeywell International, Inc. Labyrinth seals and methods of manufacture
GB2502309A (en) * 2012-05-23 2013-11-27 Rolls Royce Plc A honeycomb seal a method of manufacturing a honeycomb seal

Also Published As

Publication number Publication date
FR3064668A1 (fr) 2018-10-05

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