FR3081512B1 - LARGE DISPLACEMENT SEALING DEVICE FOR AN AIRCRAFT ENGINE - Google Patents
LARGE DISPLACEMENT SEALING DEVICE FOR AN AIRCRAFT ENGINE Download PDFInfo
- 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
Links
- 238000007789 sealing Methods 0.000 title abstract 4
- 238000006073 displacement reaction Methods 0.000 title 1
Classifications
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- 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
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- 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
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- 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
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- 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).
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)
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 |
-
2018
- 2018-05-28 FR FR1854512A patent/FR3081512B1/en active Active
Also Published As
Publication number | Publication date |
---|---|
FR3081512A1 (en) | 2019-11-29 |
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Effective date: 20191129 |
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