FR3085405B1 - PRESSURIZATION OF THE INTER-LECHETTES CAVITY BY DERIVATION OF THE BYPASS FLOW - Google Patents

PRESSURIZATION OF THE INTER-LECHETTES CAVITY BY DERIVATION OF THE BYPASS FLOW Download PDF

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Publication number
FR3085405B1
FR3085405B1 FR1857722A FR1857722A FR3085405B1 FR 3085405 B1 FR3085405 B1 FR 3085405B1 FR 1857722 A FR1857722 A FR 1857722A FR 1857722 A FR1857722 A FR 1857722A FR 3085405 B1 FR3085405 B1 FR 3085405B1
Authority
FR
France
Prior art keywords
lechettes
derivation
pressurization
inter
cavity
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
FR1857722A
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French (fr)
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FR3085405A1 (en
Inventor
Pierre Vincent
Simon Jose Pierre Amoedo
Olivier Arnaud Fabien Lambert
Josselin Luc Florent Sicard
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
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Safran Aircraft Engines SAS
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Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1857722A priority Critical patent/FR3085405B1/en
Publication of FR3085405A1 publication Critical patent/FR3085405A1/en
Application granted granted Critical
Publication of FR3085405B1 publication Critical patent/FR3085405B1/en
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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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • 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

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  • 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

L'invention concerne une structure d'étanchéité (20) d'un joint d'étanchéité (9) d'une turbomachine, la structure d'étanchéité (9) s'étendant circonférentiellement autour d'un axe (X) et étant configurée pour coopérer à frottement avec au moins une léchette (12) portée par un rotor de la turbomachine, la structure d'étanchéité comprenant un élément abradable (20) et présentant une face amont (25) destinée à être disposée en regard d'un flux traversant de l'amont vers l'aval la turbomachine et une face radialement interne (26) configurée pour s'étendre en regard de l'au moins une léchette (12), et au moins une canalisation (30), formée dans l'élément abradable (20), ladite au moins une canalisation (30) débouchant d'une part dans la face amont (25) et d'autre part dans la face radialement interne (26) avec une orientation circonférentielle par rapport à l'axe (X).The invention relates to a sealing structure (20) of a gasket (9) of a turbomachine, the sealing structure (9) extending circumferentially around an axis (X) and being configured to co-operate in friction with at least one wiper (12) carried by a rotor of the turbomachine, the sealing structure comprising an abradable element (20) and having an upstream face (25) intended to be placed facing a flow crossing from upstream to downstream the turbomachine and a radially internal face (26) configured to extend facing the at least one wiper (12), and at least one pipe (30), formed in the abradable element (20), said at least one pipe (30) opening out on the one hand into the upstream face (25) and on the other hand into the radially internal face (26) with a circumferential orientation with respect to the axis ( X).

FR1857722A 2018-08-28 2018-08-28 PRESSURIZATION OF THE INTER-LECHETTES CAVITY BY DERIVATION OF THE BYPASS FLOW Active FR3085405B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1857722A FR3085405B1 (en) 2018-08-28 2018-08-28 PRESSURIZATION OF THE INTER-LECHETTES CAVITY BY DERIVATION OF THE BYPASS FLOW

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1857722A FR3085405B1 (en) 2018-08-28 2018-08-28 PRESSURIZATION OF THE INTER-LECHETTES CAVITY BY DERIVATION OF THE BYPASS FLOW

Publications (2)

Publication Number Publication Date
FR3085405A1 FR3085405A1 (en) 2020-03-06
FR3085405B1 true FR3085405B1 (en) 2020-12-04

Family

ID=63638113

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1857722A Active FR3085405B1 (en) 2018-08-28 2018-08-28 PRESSURIZATION OF THE INTER-LECHETTES CAVITY BY DERIVATION OF THE BYPASS FLOW

Country Status (1)

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FR (1) FR3085405B1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5281090A (en) * 1990-04-03 1994-01-25 General Electric Co. Thermally-tuned rotary labyrinth seal with active seal clearance control
US5984630A (en) * 1997-12-24 1999-11-16 General Electric Company Reduced windage high pressure turbine forward outer seal
FR2999249B1 (en) * 2012-12-07 2015-01-09 Snecma COMPRESSOR FOR TURBOMACHINE WITH COOLING MEANS FOR A ROTATING SEAL ENSURING SEALING BETWEEN A RECTIFIER AND A ROTOR
EP2837856B1 (en) * 2013-08-14 2016-10-26 General Electric Technology GmbH Fluid seal arrangement and method for constricting a leakage flow through a leakage gap

Also Published As

Publication number Publication date
FR3085405A1 (en) 2020-03-06

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