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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 PDF

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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
Application number
FR1461247A
Other languages
French (fr)
Other versions
FR3028882A1 (en
Inventor
Biez Philippe Charles Alain Le
Pierre Marie Montfort
Adrien Paixao
Serge Georges Vladimir Selezneff
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
SNECMA 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 SNECMA SAS filed Critical SNECMA SAS
Priority to FR1461247A priority Critical patent/FR3028882B1/en
Publication of FR3028882A1 publication Critical patent/FR3028882A1/en
Application granted granted Critical
Publication of FR3028882B1 publication Critical patent/FR3028882B1/en
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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
    • F01D11/08—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

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

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.

FR1461247A 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 Active FR3028882B1 (en)

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 (3)

* Cited by examiner, † Cited by third party
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
DE102019219090A1 (en) * 2019-12-06 2021-06-10 MTU Aero Engines AG Seal carrier for a turbo machine with slot-like openings in the seal body

Family Cites Families (12)

* Cited by examiner, † Cited by third party
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

Also Published As

Publication number Publication date
FR3028882A1 (en) 2016-05-27

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