FR3109793B1 - PLATFORM FOR A FAN ROTOR OF AN AIRCRAFT TURBOMACHINE - Google Patents

PLATFORM FOR A FAN ROTOR OF AN AIRCRAFT TURBOMACHINE Download PDF

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Publication number
FR3109793B1
FR3109793B1 FR2004398A FR2004398A FR3109793B1 FR 3109793 B1 FR3109793 B1 FR 3109793B1 FR 2004398 A FR2004398 A FR 2004398A FR 2004398 A FR2004398 A FR 2004398A FR 3109793 B1 FR3109793 B1 FR 3109793B1
Authority
FR
France
Prior art keywords
platform
longitudinal
reinforcement
fan rotor
layer
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
FR2004398A
Other languages
French (fr)
Other versions
FR3109793A1 (en
Inventor
Thierry François Maurice Duchatelle
Yann André Maurice Perrin
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 FR2004398A priority Critical patent/FR3109793B1/en
Publication of FR3109793A1 publication Critical patent/FR3109793A1/en
Application granted granted Critical
Publication of FR3109793B1 publication Critical patent/FR3109793B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • 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
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/51—Building or constructing in particular ways in a modular way, e.g. using several identical or complementary parts or features
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6034—Orientation of fibres, weaving, ply angle
    • 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

Abstract

L’invention concerne une plateforme (4) pour un rotor de soufflante d’une turbomachine d’aéronef, cette plateforme (4) étant configurée pour être solidaire d’un disque de soufflante entre deux aubes de soufflante adjacentes, la plateforme (4) comportant une paroi (5) longitudinale définissant une face externe aérodynamique (6). Selon l’invention, la plateforme (4) comprend une armature (9) longitudinale et une couche longitudinale composite (10), l’armature (9) étant monobloc et comportant deux peaux longitudinales (7, 8) respectivement interne (7) et externe (8) qui s’étendent l’une au-dessus de l’autre et sont reliées entre elles par des voiles (25), la couche composite (10) recouvrant la peau externe (8) de l’armature métallique (9) et définissant ladite face aérodynamique (6). Figure pour l’abrégé : Figure 2The invention relates to a platform (4) for a fan rotor of an aircraft turbine engine, this platform (4) being configured to be integral with a fan disc between two adjacent fan blades, the platform (4) comprising a longitudinal wall (5) defining an aerodynamic external face (6). According to the invention, the platform (4) comprises a longitudinal reinforcement (9) and a composite longitudinal layer (10), the reinforcement (9) being one-piece and comprising two longitudinal skins (7, 8) respectively internal (7) and outer layer (8) which extend one above the other and are interconnected by webs (25), the composite layer (10) covering the outer skin (8) of the metal reinforcement (9 ) and defining said aerodynamic face (6). Figure for abstract: Figure 2

FR2004398A 2020-05-04 2020-05-04 PLATFORM FOR A FAN ROTOR OF AN AIRCRAFT TURBOMACHINE Active FR3109793B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2004398A FR3109793B1 (en) 2020-05-04 2020-05-04 PLATFORM FOR A FAN ROTOR OF AN AIRCRAFT TURBOMACHINE

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2004398A FR3109793B1 (en) 2020-05-04 2020-05-04 PLATFORM FOR A FAN ROTOR OF AN AIRCRAFT TURBOMACHINE
FR2004398 2020-05-04

Publications (2)

Publication Number Publication Date
FR3109793A1 FR3109793A1 (en) 2021-11-05
FR3109793B1 true FR3109793B1 (en) 2022-08-12

Family

ID=71662076

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2004398A Active FR3109793B1 (en) 2020-05-04 2020-05-04 PLATFORM FOR A FAN ROTOR OF AN AIRCRAFT TURBOMACHINE

Country Status (1)

Country Link
FR (1) FR3109793B1 (en)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6217283B1 (en) * 1999-04-20 2001-04-17 General Electric Company Composite fan platform
GB2414521B (en) * 2004-05-28 2007-04-11 Rolls Royce Plc Rotor assembly and annulus filler for gas turbine engine compressor
FR2913734B1 (en) 2007-03-16 2009-05-01 Snecma Sa TURBOMACHINE BLOWER
FR3029563B1 (en) * 2014-12-08 2020-01-17 Safran Aircraft Engines LOW HUB RATIO PLATFORM
FR3038653B1 (en) 2015-07-08 2017-08-04 Snecma ASSEMBLY OF A REPORTED PLATFORM OF BLOWER BLADE ON A BLOWER DISK
US20170101878A1 (en) * 2015-10-08 2017-04-13 General Electric Company Low modulus insert for a component of a gas turbine engine

Also Published As

Publication number Publication date
FR3109793A1 (en) 2021-11-05

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