FR3081512B1 - LARGE DISPLACEMENT SEALING DEVICE FOR AN AIRCRAFT ENGINE - Google Patents

LARGE DISPLACEMENT SEALING DEVICE FOR AN AIRCRAFT ENGINE Download PDF

Info

Publication number
FR3081512B1
FR3081512B1 FR1854512A FR1854512A FR3081512B1 FR 3081512 B1 FR3081512 B1 FR 3081512B1 FR 1854512 A FR1854512 A FR 1854512A FR 1854512 A FR1854512 A FR 1854512A FR 3081512 B1 FR3081512 B1 FR 3081512B1
Authority
FR
France
Prior art keywords
annular
wall
aircraft engine
sealing device
sealing
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
FR1854512A
Other languages
French (fr)
Other versions
FR3081512A1 (en
Inventor
Eddy Keomorakott Souryavongsa
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 FR1854512A priority Critical patent/FR3081512B1/en
Publication of FR3081512A1 publication Critical patent/FR3081512A1/en
Application granted granted Critical
Publication of FR3081512B1 publication Critical patent/FR3081512B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/28—Arrangement of seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/072—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with counter-rotating, e.g. fan rotors
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F05D2240/58—Piston ring seals
    • F05D2240/581—Double or plural piston ring arrangements, i.e. two or more piston rings

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Sealing Devices (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)

Abstract

L'invention concerne un dispositif d'étanchéité entre deux parois sensiblement cylindriques d'un moteur d'aéronef, les deux parois, respectivement radialement interne et externe, étant engagées coaxialement l'une dans l'autre, caractérisé en ce que : - la paroi externe (10) comprend des premiers (20) et des deuxièmes (24) moyens annulaires de support qui sont formés en saillie radialement vers l'intérieur et définissent entre eux un espace annulaire s'étendant autour de la paroi interne, - la paroi interne (9) comprend des troisièmes moyens annulaires (12-13) d'appui axial qui sont formés en saillie radialement vers l'extérieur et sont situés au moins en partie dans ledit espace annulaire, - une première bague annulaire (19) d'étanchéité en appui axial sur un côté (15) desdits troisièmes moyens (12-13) est sollicitée axialement contre ces derniers par des premiers moyens élastiques (22) portés par lesdits premiers moyens (20), et - une seconde bague annulaire (23) d'étanchéité en appui axial sur un côté opposé (16) desdits troisièmes moyens (12-13) est sollicitée axialement contre ces derniers par des seconds moyens élastiques (26) portés par lesdits seconds moyens (24).The invention relates to a sealing device between two substantially cylindrical walls of an aircraft engine, the two walls, respectively radially internal and external, being engaged coaxially with one another, characterized in that: - the outer wall (10) comprises first (20) and second (24) annular support means which are formed projecting radially inwards and define between them an annular space extending around the inner wall, - the wall internal (9) comprises third annular axial support means (12-13) which are formed to project radially outwards and are located at least partly in said annular space, - a first annular ring (19) of sealing in axial bearing on one side (15) of said third means (12-13) is biased axially against the latter by first elastic means (22) carried by said first means (20), and - a second annular ring (23) sealing support axial on an opposite side (16) of said third means (12-13) is biased axially against the latter by second elastic means (26) carried by said second means (24).

FR1854512A 2018-05-28 2018-05-28 LARGE DISPLACEMENT SEALING DEVICE FOR AN AIRCRAFT ENGINE Active FR3081512B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1854512A FR3081512B1 (en) 2018-05-28 2018-05-28 LARGE DISPLACEMENT SEALING DEVICE FOR AN AIRCRAFT ENGINE

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1854512A FR3081512B1 (en) 2018-05-28 2018-05-28 LARGE DISPLACEMENT SEALING DEVICE FOR AN AIRCRAFT ENGINE
FR1854512 2018-05-28

Publications (2)

Publication Number Publication Date
FR3081512A1 FR3081512A1 (en) 2019-11-29
FR3081512B1 true FR3081512B1 (en) 2021-06-04

Family

ID=62875012

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1854512A Active FR3081512B1 (en) 2018-05-28 2018-05-28 LARGE DISPLACEMENT SEALING DEVICE FOR AN AIRCRAFT ENGINE

Country Status (1)

Country Link
FR (1) FR3081512B1 (en)

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4916892A (en) * 1988-05-06 1990-04-17 General Electric Company High pressure seal
US10233762B2 (en) * 2013-02-27 2019-03-19 United Technologies Corporation Cooled seal assembly for arranging between a stator and a rotor
WO2016207761A1 (en) * 2015-06-23 2016-12-29 Turboden S.R.L. Seal arrangement in a turbine and method for confining the operating fluid

Also Published As

Publication number Publication date
FR3081512A1 (en) 2019-11-29

Similar Documents

Publication Publication Date Title
FR3071296B1 (en) SEALING DEVICE FOR MAN-MACHINE DIALOGUE MEMBER
CA2494943A1 (en) Diffuser for jet turbine engine
US10138973B2 (en) Fluid damper device and apparatus with damper
CA2504177A1 (en) Cooling device for the fixed ring of a gas turbine
ES2344136T3 (en) UNION DEVICE FOR CONNECTING A PRESSURE CONTAINER WITH A LIQUID GAS FILLING MOUTH.
FR2514095A1 (en) FLUID PRESSURE ACTUATOR FOR VALVE
FR3081211B1 (en) TURBOMACHINE COMBUSTION CHAMBER SET
FR3081512B1 (en) LARGE DISPLACEMENT SEALING DEVICE FOR AN AIRCRAFT ENGINE
FR3051527B1 (en) ASSEMBLY FORMING A SEAL WITH SOLIDITY BODY RETAINING CAVITIES
FR3064980A1 (en) AIRCRAFT PROPULSION SYSTEM HAVING A NACELLE WITH AN IMPROVED OPENING SYSTEM
FR2909746A1 (en) JOINT FLEXIBLE WITH BELLOW.
FR3079590B1 (en) CONNECTION DEVICE FOR AN AIR CIRCUIT OF AN AIRCRAFT ENGINE
FR3088671B1 (en) TIGHTNESS BETWEEN A MOBILE WHEEL AND A TURBOMACHINE DISTRIBUTOR
FR3117152B1 (en) COMBUSTION MODULE FOR A TURBOMACHINE
BR0312892A (en) Seal assembly to seal an annular gap between an inner tube and an outer tube in a double wall subsea pipeline, pipe system, and valve
FR3057333B1 (en) CLAMP ASSEMBLY WITH SEAL
JP2010037962A (en) Oil control valve attachment structure
FR3081511B1 (en) SEALING DEVICE BETWEEN TWO ANNULAR WALLS OF AN AIRCRAFT ENGINE
FR3102823B1 (en) Sealed junction device between two containment enclosures offering improved sealing
FR3098547B1 (en) HOLDING ASSEMBLY FOR A GEAR TRAIN IN A TURBOMACHINE
FR3026178A1 (en)
FR3135769B1 (en) Box for driving accessories
FR3089561B1 (en) IMPROVED AIR TIGHTNESS DEVICE INTENDED TO BE INTERPOSED BETWEEN A DOUBLE-FLOW AIRCRAFT TURBOMACHINE CASING ELEMENT, AND A NACELLE ELEMENT
FR3092316B1 (en) Aircraft propulsion unit
US1519047A (en) Flexible joint

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20191129

PLFP Fee payment

Year of fee payment: 3

PLFP Fee payment

Year of fee payment: 4

PLFP Fee payment

Year of fee payment: 5

PLFP Fee payment

Year of fee payment: 6

PLFP Fee payment

Year of fee payment: 7