FR3122209B1 - Procede de fabrication d’une aube composite pour turbomachine d’aeronef - Google Patents

Procede de fabrication d’une aube composite pour turbomachine d’aeronef Download PDF

Info

Publication number
FR3122209B1
FR3122209B1 FR2104159A FR2104159A FR3122209B1 FR 3122209 B1 FR3122209 B1 FR 3122209B1 FR 2104159 A FR2104159 A FR 2104159A FR 2104159 A FR2104159 A FR 2104159A FR 3122209 B1 FR3122209 B1 FR 3122209B1
Authority
FR
France
Prior art keywords
blade
manufacturing
aircraft turbomachine
composite blade
patch
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
FR2104159A
Other languages
English (en)
Other versions
FR3122209A1 (fr
Inventor
Didier Queant
Richard Anandavelou Mounien
Julien David Alexandre Trebaol
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 FR2104159A priority Critical patent/FR3122209B1/fr
Publication of FR3122209A1 publication Critical patent/FR3122209A1/fr
Application granted granted Critical
Publication of FR3122209B1 publication Critical patent/FR3122209B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/027—Arrangements for balancing
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/662—Balancing of rotors
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/80—Repairing, retrofitting or upgrading methods
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • 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)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Composite Materials (AREA)
  • Moulding By Coating Moulds (AREA)

Abstract

L’invention concerne un procédé de fabrication d’une aube composite (10) de turbomachine d’aéronef, cette aube (10) comportant une pale (12) qui comprend un intrados (20) et un extrados (22) et qui est formée à partir d’une préforme fibreuse noyée dans une matrice polymérique. Selon l’invention, le procédé comprend les étapes de : a) polymérisation de la matrice et solidification de la pale (12), b) mesure d’un poids moment de l’aube (10), c) détermination des dimensions et de la position d’au moins un patch (24) à rapporter sur l’intrados et/ou l’extrados (22) de la pale (12) pour corriger le poids moment de l’aube (10), d) rapporter le ou chaque patch (24) sur l’intrados et/ou l’extrados (22) dans la position déterminée, et e) application d’un revêtement sur la pale (12). Figure pour l'abrégé : Figure 4a
FR2104159A 2021-04-21 2021-04-21 Procede de fabrication d’une aube composite pour turbomachine d’aeronef Active FR3122209B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2104159A FR3122209B1 (fr) 2021-04-21 2021-04-21 Procede de fabrication d’une aube composite pour turbomachine d’aeronef

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2104159 2021-04-21
FR2104159A FR3122209B1 (fr) 2021-04-21 2021-04-21 Procede de fabrication d’une aube composite pour turbomachine d’aeronef

Publications (2)

Publication Number Publication Date
FR3122209A1 FR3122209A1 (fr) 2022-10-28
FR3122209B1 true FR3122209B1 (fr) 2023-03-10

Family

ID=75954119

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2104159A Active FR3122209B1 (fr) 2021-04-21 2021-04-21 Procede de fabrication d’une aube composite pour turbomachine d’aeronef

Country Status (1)

Country Link
FR (1) FR3122209B1 (fr)

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2921099B1 (fr) * 2007-09-13 2013-12-06 Snecma Dispositif d'amortissement pour aube en materiau composite
FR2956057B1 (fr) 2010-02-10 2012-01-27 Snecma Decoupe de preformes avant injection rtm par jet d'eau et cryogenisation
FR3023212B1 (fr) * 2014-07-03 2019-10-11 Safran Ceramics Procede de fabrication d'une piece revetue par un revetement de surface comportant un alliage
FR3029134B1 (fr) 2014-12-02 2017-10-06 Snecma Procede de controle de position d'une preforme d'aube composite de turbomachine dans un moule
FR3051386B1 (fr) 2016-05-19 2024-03-29 Snecma Element de moule pour moulage rtm
FR3081370B1 (fr) * 2018-05-22 2020-06-05 Safran Aircraft Engines Corps d'aube et aube en materiau composite ayant un renfort fibreux compose d'un tissage tridimensionnel et de fibres courtes et leur procede de fabrication
FR3085417B1 (fr) * 2018-08-29 2020-12-04 Safran Aircraft Engines Aube comprenant une structure en materiau composite et procede de fabrication associe

Also Published As

Publication number Publication date
FR3122209A1 (fr) 2022-10-28

Similar Documents

Publication Publication Date Title
US8075267B2 (en) Method and sensor setup for determination of deflection and/or strain for failure detection
JP6770556B2 (ja) 逆スラスト装置用カスケード組立体の製造方法
SE443184B (sv) Rotorblad, rotorskiva samt rotorbladenhet
FR3103731B1 (fr) Aube composite pour un moteur d’aeronef et ses procedes de fabrication et de reparation
FR3122209B1 (fr) Procede de fabrication d’une aube composite pour turbomachine d’aeronef
CN104652242B (zh) 一种用于加固psc连续箱梁桥的吊杆连接结构及施工方法
US7507073B2 (en) Methods and apparatus for assembling a steam turbine bucket
FR3111659B1 (fr) Aube de turbomachine a bord d’attaque metallique
CN114329697A (zh) 横向分布活载作用下悬索桥结构变形和内力的确定方法
CN110387820B (zh) 一种基于智能张拉系统的吊杆测控一体化施工方法
CN109614713B (zh) 基于修正刚度方法的复合材料多钉连接钉载分配预测方法
US20210293152A1 (en) Turbine blade having a structural reinforcement with enhanced adherence
CN109933838A (zh) 一种装配式剪力连接件全过程滑移计算方法
US6942455B2 (en) Strain isolated trim tab
FR3060441B1 (fr) Structure de composant et procede pour la fabriquer
CN110147622B (zh) 确定全装配式钢-混组合梁桥的裂缝宽度的方法
CN111335168A (zh) 千米级混合梁斜拉桥合龙方法
CN106844925B (zh) 基于偏频仿真的两级副簧式渐变刚度板簧接触载荷的调整设计法
FR3096399B1 (fr) Aube de turbomachine à bord d’attaque métallique intégré et procédé pour l’obtenir
US20100143110A1 (en) Vane for a compressor or a turbine of an aircraft engine, aircraft engine comprising such a vane and a method for coating a vane of an aircraft engine
EP2638249B1 (fr) Procede d'optimisation du profil d'une aube pour roue mobile de turbomachine
CN114964784A (zh) 飞脱试验叶片的设计方法、叶片及叶片飞脱试验方法
US6176681B1 (en) Rotor blade with improved attachment on a hub of a fan
FR3080385B1 (fr) Procede de fabrication d'un element aubage metallique pour une turbomachine d'aeronef
FR3116560B1 (fr) Aube composite pour une turbomachine d’aéronef et son procédé de fabrication

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20221028

PLFP Fee payment

Year of fee payment: 3

PLFP Fee payment

Year of fee payment: 4