FR3028882B1 - PROCESS FOR MAKING A MULTI-LAYER ABRADABLE COATING WITH INTEGRATED TUBULAR STRUCTURE, AND ABRADABLE COATING OBTAINED BY SUCH A PROCESS - Google Patents
PROCESS FOR MAKING A MULTI-LAYER ABRADABLE COATING WITH INTEGRATED TUBULAR STRUCTURE, AND ABRADABLE COATING OBTAINED BY SUCH A PROCESS Download PDFInfo
- Publication number
- FR3028882B1 FR3028882B1 FR1461247A FR1461247A FR3028882B1 FR 3028882 B1 FR3028882 B1 FR 3028882B1 FR 1461247 A FR1461247 A FR 1461247A FR 1461247 A FR1461247 A FR 1461247A FR 3028882 B1 FR3028882 B1 FR 3028882B1
- Authority
- FR
- France
- Prior art keywords
- abradable coating
- layer
- abradable
- making
- tubular structure
- 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
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
- F01D11/122—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 erodable or abradable material
- F01D11/125—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 erodable or abradable material with a reinforcing structure
-
- 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
- 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
- F16J15/44—Free-space packings
- F16J15/444—Free-space packings with facing materials having honeycomb-like structure
-
- 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
- F16J15/44—Free-space packings
- F16J15/445—Free-space packings with means for adjusting the clearance
-
- 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
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
-
- 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
- F05D2230/90—Coating; Surface treatment
-
- 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
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/09—Purpose of the control system to cope with emergencies
- F05D2270/096—Purpose of the control system to cope with emergencies caused by water or hail ingestion
Abstract
Procédé de réalisation d'un revêtement abradable (12) pour carter (10) de soufflante de turbomachine, comprenant les étapes suivantes : le dépôt d'au moins une première couche (16) de matériau abradable sur une piste d'abradable (14) d'un carter de soufflante, l'insertion d'au moins une structure à cellules tubulaires (18) dans la première couche de matériau abradable de sorte que le matériau abradable de la première couche remplisse au moins partiellement l'ensemble des cellules tubulaires de ladite structure à cellules tubulaires, le dépôt d'au moins une deuxième couche (20) de matériau abradable de sorte à immerger complètement la structure à cellules tubulaires dans le matériau abradable des première et deuxième couches, et la solidification des première et deuxième couches de matériau abradable. L'invention concerne également un revêtement abradable (12) obtenu par un tel procédé.A method of producing an abradable coating (12) for a turbomachine fan casing (10), comprising the following steps: depositing at least a first layer (16) of abradable material on an abradable track (14) of a fan housing, inserting at least one tubular cell structure (18) into the first layer of abradable material such that the abradable material in the first layer at least partially fills all of the tubular cells with said tubular cell structure, depositing at least a second layer (20) of abradable material so as to completely immerse the tubular cell structure in the abradable material of the first and second layers, and solidifying the first and second layers of abradable material. The invention also relates to an abradable coating (12) obtained by such a method.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1461247A FR3028882B1 (en) | 2014-11-20 | 2014-11-20 | PROCESS FOR MAKING A MULTI-LAYER ABRADABLE COATING WITH INTEGRATED TUBULAR STRUCTURE, AND ABRADABLE COATING OBTAINED BY SUCH A PROCESS |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1461247A FR3028882B1 (en) | 2014-11-20 | 2014-11-20 | PROCESS FOR MAKING A MULTI-LAYER ABRADABLE COATING WITH INTEGRATED TUBULAR STRUCTURE, AND ABRADABLE COATING OBTAINED BY SUCH A PROCESS |
Publications (2)
Publication Number | Publication Date |
---|---|
FR3028882A1 FR3028882A1 (en) | 2016-05-27 |
FR3028882B1 true FR3028882B1 (en) | 2021-05-28 |
Family
ID=52345421
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR1461247A Active FR3028882B1 (en) | 2014-11-20 | 2014-11-20 | PROCESS FOR MAKING A MULTI-LAYER ABRADABLE COATING WITH INTEGRATED TUBULAR STRUCTURE, AND ABRADABLE COATING OBTAINED BY SUCH A PROCESS |
Country Status (1)
Country | Link |
---|---|
FR (1) | FR3028882B1 (en) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3064669B1 (en) * | 2017-03-31 | 2020-11-13 | Safran Aircraft Engines | SEALING DEVICE FOR A TURBOMACHINE WITH ABRADABLE COATING |
FR3073890B1 (en) | 2017-11-21 | 2021-01-22 | Safran Aircraft Engines | ABRADABLE LABYRINTH SEAL, ESPECIALLY FOR AIRCRAFT TURBINE |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2744042A (en) * | 1951-06-21 | 1956-05-01 | Goodyear Tire & Rubber | Laminated panels |
FR2339741A1 (en) * | 1976-01-30 | 1977-08-26 | Snecma | ABRADABLE STATOR GASKET FOR AXIAL TURBOMACHINE AND ITS EXECUTION PROCESS |
US4349313A (en) * | 1979-12-26 | 1982-09-14 | United Technologies Corporation | Abradable rub strip |
US4409054A (en) * | 1981-01-14 | 1983-10-11 | United Technologies Corporation | Method for applying abradable material to a honeycomb structure and the product thereof |
JPS61149506A (en) * | 1984-12-21 | 1986-07-08 | Kawasaki Heavy Ind Ltd | Seal device at turbine blade tip |
US4639388A (en) * | 1985-02-12 | 1987-01-27 | Chromalloy American Corporation | Ceramic-metal composites |
US4687691A (en) * | 1986-04-28 | 1987-08-18 | United Technologies Corporation | Honeycomb spliced multilayer foam core aircraft composite parts and method for making same |
JPH02127448A (en) * | 1988-09-06 | 1990-05-16 | Imi Tech Corp | Rehardenable hardened cellular material |
US5080934A (en) * | 1990-01-19 | 1992-01-14 | Avco Corporation | Process for making abradable hybrid ceramic wall structures |
DE102005041830A1 (en) * | 2005-09-02 | 2007-03-08 | Mtu Aero Engines Gmbh | Honeycomb structure is applied to gas turbine components by pressing into a soft surface coating which is then hardened |
DE102009034025A1 (en) * | 2009-07-21 | 2011-01-27 | Mtu Aero Engines Gmbh | Inlet lining for arrangement on a gas turbine component |
FR2977827B1 (en) * | 2011-07-13 | 2015-03-13 | Snecma | PROCESS FOR MANUFACTURING A TURBOMACHINE BLOWER HOUSING WITH ABRADABLE AND ACOUSTIC COATINGS |
-
2014
- 2014-11-20 FR FR1461247A patent/FR3028882B1/en active Active
Also Published As
Publication number | Publication date |
---|---|
FR3028882A1 (en) | 2016-05-27 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
DE602008001879D1 (en) | METHOD FOR PRODUCING CONDUCTIVE FILMS AND ARTICLES MADE IN THIS PROCESS | |
EP4243224A3 (en) | Method for assisting cable harness production | |
WO2009019147A3 (en) | Deposition from ionic liquids | |
WO2015095617A3 (en) | Structures having selectively metallized regions and methods of manufacturing the same | |
GB2468820A (en) | Method and apparatus for estimating a downhole fluid property | |
FR3021902B1 (en) | METHOD FOR DETERMINING THE POINTS TO BE SUPPORTED FOR AN OBJECT MADE BY MEANS OF AN ADDITIVE MANUFACTURING PROCESS; INFORMATION RECORDING MEDIUM AND RELATED SUPPORT STRUCTURE | |
ATE509856T1 (en) | PACKAGING FOR FILM CONTAINING ACTIVE INGREDIENTS AND METHOD FOR THE PRODUCTION THEREOF | |
WO2008091852A3 (en) | Polymeric substrates for surface enhanced raman spectroscopy | |
FR2967813B1 (en) | METHOD FOR PRODUCING A BENTALLIC METAL LAYER STRUCTURE | |
WO2013078494A3 (en) | Tipping paper for a smoking article | |
AR073294A1 (en) | COMPOSITIONS AND METHODS TO PREVENT THE DEPOSIT OF ASPHALTENS | |
FR3028882B1 (en) | PROCESS FOR MAKING A MULTI-LAYER ABRADABLE COATING WITH INTEGRATED TUBULAR STRUCTURE, AND ABRADABLE COATING OBTAINED BY SUCH A PROCESS | |
MY183132A (en) | Stand-off clamp for pipeline repair | |
TW201614353A (en) | Narrow pre-deposition laser edge deletion | |
ATE436034T1 (en) | LENSES MOLDED FROM A HIGH MOLECULAR WEIGHT POLYCARBONATE WITH A CERTAIN VISCOSITY | |
FR3004006B1 (en) | ACTIVE NANOWIRE ELECTROLUMINESCENT DEVICE AND CONTACT NANOWIRES AND METHOD OF MANUFACTURE | |
FR2974021B1 (en) | PROCESS FOR THE PREPARATION OF METALLIC PARTICLES | |
FR3079448B1 (en) | METHOD FOR MANUFACTURING A CLADDING AND CORRESPONDING CLADDING | |
WO2012113369A3 (en) | Method for generatively producing or repairing a component, and component | |
ATE380066T1 (en) | METHOD FOR PRODUCING MEMBRANES | |
DE602006009137D1 (en) | COOLING ELEMENT AND METHOD FOR THE PRODUCTION THEREOF | |
FR3028448B1 (en) | METHOD AND FACILITY FOR AUTOMATICALLY MANUFACTURING A VACUUM ASSEMBLY | |
ATE503575T1 (en) | LAYER COMPOSITE AND ITS PRODUCTION | |
WO2014023809A3 (en) | Laser-based method and machining table for metallising the back of a semiconductor component | |
WO2012048692A3 (en) | Indexable insert, and method for the production thereof |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PLFP | Fee payment |
Year of fee payment: 2 |
|
PLSC | Publication of the preliminary search report |
Effective date: 20160527 |
|
PLFP | Fee payment |
Year of fee payment: 3 |
|
PLFP | Fee payment |
Year of fee payment: 4 |
|
CD | Change of name or company name |
Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
|
PLFP | Fee payment |
Year of fee payment: 5 |
|
PLFP | Fee payment |
Year of fee payment: 6 |
|
PLFP | Fee payment |
Year of fee payment: 7 |
|
PLFP | Fee payment |
Year of fee payment: 8 |
|
PLFP | Fee payment |
Year of fee payment: 9 |
|
PLFP | Fee payment |
Year of fee payment: 10 |