FR3095833B1 - Anneau d’etancheite pour une turbomachine d’aeronef - Google Patents
Anneau d’etancheite pour une turbomachine d’aeronef Download PDFInfo
- Publication number
- FR3095833B1 FR3095833B1 FR1904770A FR1904770A FR3095833B1 FR 3095833 B1 FR3095833 B1 FR 3095833B1 FR 1904770 A FR1904770 A FR 1904770A FR 1904770 A FR1904770 A FR 1904770A FR 3095833 B1 FR3095833 B1 FR 3095833B1
- Authority
- FR
- France
- Prior art keywords
- sealing ring
- aircraft turbomachine
- annular wall
- abradable coating
- cells
- 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 2
- 239000011248 coating agent Substances 0.000 abstract 2
- 238000000576 coating method Methods 0.000 abstract 2
- 238000005192 partition Methods 0.000 abstract 2
- 210000004027 cell Anatomy 0.000 abstract 1
- 210000001316 polygonal cell Anatomy 0.000 abstract 1
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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- 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
- F05D2250/10—Two-dimensional
- F05D2250/18—Two-dimensional patterned
- F05D2250/182—Two-dimensional patterned crenellated, notched
-
- 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
- F05D2250/20—Three-dimensional
- F05D2250/28—Three-dimensional patterned
- F05D2250/283—Three-dimensional patterned honeycomb
-
- 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
- F05D2250/20—Three-dimensional
- F05D2250/29—Three-dimensional machined; miscellaneous
- F05D2250/294—Three-dimensional machined; miscellaneous grooved
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
L’invention concerne un anneau (20) d’étanchéité pour une turbomachine d’aéronef comprenant une paroi annulaire (21) présentant une surface intérieure (210) munie d’un revêtement abradable (22), ce revêtement abradable présentant une structure alvéolaire, par exemple en nid d’abeille, comprenant une pluralité d’alvéoles (220) polygonales présentant une première extrémité (220a) fixée à la surface intérieure (210) de la paroi annulaire (21) et une seconde extrémité (220b) libre, les alvéoles (220) étant reliées entre elles par des cloisons jointives, caractérisé en ce que l’une au moins des cloisons (221, 221’, 221’’, 222, 222’, 222’’) jointives est munie d’une échancrure (30). Figure pour l'abrégé : Figure 3
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1904770A FR3095833B1 (fr) | 2019-05-07 | 2019-05-07 | Anneau d’etancheite pour une turbomachine d’aeronef |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1904770A FR3095833B1 (fr) | 2019-05-07 | 2019-05-07 | Anneau d’etancheite pour une turbomachine d’aeronef |
FR1904770 | 2019-05-07 |
Publications (2)
Publication Number | Publication Date |
---|---|
FR3095833A1 FR3095833A1 (fr) | 2020-11-13 |
FR3095833B1 true FR3095833B1 (fr) | 2021-05-28 |
Family
ID=67587864
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR1904770A Active FR3095833B1 (fr) | 2019-05-07 | 2019-05-07 | Anneau d’etancheite pour une turbomachine d’aeronef |
Country Status (1)
Country | Link |
---|---|
FR (1) | FR3095833B1 (fr) |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3867061A (en) * | 1973-12-26 | 1975-02-18 | Curtiss Wright Corp | Shroud structure for turbine rotor blades and the like |
GB2310895A (en) * | 1996-03-04 | 1997-09-10 | Rolls Royce Plc | Turbine shroud assembly |
US9080459B2 (en) * | 2012-01-03 | 2015-07-14 | General Electric Company | Forward step honeycomb seal for turbine shroud |
FR2985759B1 (fr) | 2012-01-17 | 2014-03-07 | Snecma | Aube mobile de turbomachine |
US10883373B2 (en) * | 2017-03-02 | 2021-01-05 | Rolls-Royce Corporation | Blade tip seal |
-
2019
- 2019-05-07 FR FR1904770A patent/FR3095833B1/fr active Active
Also Published As
Publication number | Publication date |
---|---|
FR3095833A1 (fr) | 2020-11-13 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PLFP | Fee payment |
Year of fee payment: 2 |
|
PLSC | Publication of the preliminary search report |
Effective date: 20201113 |
|
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 |