FR3128501B1 - Lamella sealing device, turbomachine provided with it and corresponding aircraft - Google Patents

Lamella sealing device, turbomachine provided with it and corresponding aircraft Download PDF

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Publication number
FR3128501B1
FR3128501B1 FR2111292A FR2111292A FR3128501B1 FR 3128501 B1 FR3128501 B1 FR 3128501B1 FR 2111292 A FR2111292 A FR 2111292A FR 2111292 A FR2111292 A FR 2111292A FR 3128501 B1 FR3128501 B1 FR 3128501B1
Authority
FR
France
Prior art keywords
wings
sealing device
lamella
structural element
slat
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
FR2111292A
Other languages
French (fr)
Other versions
FR3128501A1 (en
Inventor
Paul Jean-Jacques Michel Reverseau
Sabrina Benkaci
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 FR2111292A priority Critical patent/FR3128501B1/en
Publication of FR3128501A1 publication Critical patent/FR3128501A1/en
Application granted granted Critical
Publication of FR3128501B1 publication Critical patent/FR3128501B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/02—Sealings between relatively-stationary surfaces
    • F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
    • F16J15/08—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with exclusively metal packing
    • F16J15/0887—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with exclusively metal packing the sealing effect being obtained by elastic deformation of the packing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped

Abstract

La présente invention se rapporte notamment à un dispositif d'étanchéité à lamelle pour assurer une étanchéité aux fluides entre un premier élément de structure et un deuxième élément de structure, qui comporte : - au moins une lamelle d'étanchéité disposée en position d'étanchéité dans un espace séparant le premier et le deuxième éléments de structure et comportant une première et une deuxième génératrices de contact appuyées respectivement sur lesdits premier et deuxième éléments de structure ; - au moins un crochet (3) qui comporte une première partie (30) de fixation, en forme d'épingle en "U" à ailes parallèles (300, 301) qui est engagée à cheval sur une cloison dudit deuxième élément de structure, ainsi qu'une deuxième partie intermédiaire (31) d'appui qui se situe dans la continuité de l'une desdites ailes (301) mais en direction opposée, cette partie intermédiaire (31) venant en appui contre ladite lamelle, caractérisé par le fait que ladite partie intermédiaire (31) comporte un prolongement (32) qui constitue une butée d'arrêt pour ladite lamelle et qui s'oppose à l'échappement de celle-ci dans une direction généralement parallèle auxdites ailes (300, 301). Figure pour l’abrégé : Figure 4The present invention relates in particular to a lamella sealing device for ensuring fluid tightness between a first structural element and a second structural element, which comprises: - at least one sealing lamella arranged in the sealing position in a space separating the first and second structural elements and comprising a first and a second contact generator supported respectively on said first and second structural elements; - at least one hook (3) which comprises a first fixing part (30), in the shape of a "U" pin with parallel wings (300, 301) which is engaged astride a partition of said second structural element, as well as a second intermediate support part (31) which is located in the continuity of one of said wings (301) but in the opposite direction, this intermediate part (31) coming to bear against said slat, characterized by the fact that said intermediate part (31) comprises an extension (32) which constitutes a stop for said slat and which opposes the escape thereof in a direction generally parallel to said wings (300, 301). Figure for abstract: Figure 4

FR2111292A 2021-10-25 2021-10-25 Lamella sealing device, turbomachine provided with it and corresponding aircraft Active FR3128501B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2111292A FR3128501B1 (en) 2021-10-25 2021-10-25 Lamella sealing device, turbomachine provided with it and corresponding aircraft

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2111292A FR3128501B1 (en) 2021-10-25 2021-10-25 Lamella sealing device, turbomachine provided with it and corresponding aircraft
FR2111292 2021-10-25

Publications (2)

Publication Number Publication Date
FR3128501A1 FR3128501A1 (en) 2023-04-28
FR3128501B1 true FR3128501B1 (en) 2023-11-10

Family

ID=80448539

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2111292A Active FR3128501B1 (en) 2021-10-25 2021-10-25 Lamella sealing device, turbomachine provided with it and corresponding aircraft

Country Status (1)

Country Link
FR (1) FR3128501B1 (en)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090169369A1 (en) * 2007-12-29 2009-07-02 General Electric Company Turbine nozzle segment and assembly
US8142142B2 (en) * 2008-09-05 2012-03-27 Siemens Energy, Inc. Turbine transition duct apparatus
ES2760550T3 (en) * 2017-04-07 2020-05-14 MTU Aero Engines AG Gasket arrangement for a gas turbine
FR3095830B1 (en) * 2019-05-10 2021-05-07 Safran Aircraft Engines TURBOMACHINE MODULE EQUIPPED WITH A SEALING FLAP HOLDING DEVICE
FR3096401B1 (en) * 2019-05-21 2021-06-04 Safran Aircraft Engines SECTOR OF A DISTRIBUTOR AND DISTRIBUTOR OF A TURBINE OF AN AIRCRAFT TURBOMACHINE

Also Published As

Publication number Publication date
FR3128501A1 (en) 2023-04-28

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