BR112018012664A2 - blindagem de bordo de ataque para uma pá de turbomáquina, pá, turbomáquina, ventoinha, e, turbofan. - Google Patents

blindagem de bordo de ataque para uma pá de turbomáquina, pá, turbomáquina, ventoinha, e, turbofan.

Info

Publication number
BR112018012664A2
BR112018012664A2 BR112018012664-0A BR112018012664A BR112018012664A2 BR 112018012664 A2 BR112018012664 A2 BR 112018012664A2 BR 112018012664 A BR112018012664 A BR 112018012664A BR 112018012664 A2 BR112018012664 A2 BR 112018012664A2
Authority
BR
Brazil
Prior art keywords
turbocharger
leading edge
turbofan
shovel
fan
Prior art date
Application number
BR112018012664-0A
Other languages
English (en)
Other versions
BR112018012664B1 (pt
Inventor
Jean-Bernard Pouzadoux Frédéric
Jacques Michel Bassot Alain
Guivarc'h Jérémy
Romero Jean-Louis
Ruf Thibault
Original Assignee
Safran Aircraft Engines
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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=55542879&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=BR112018012664(A2) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Safran Aircraft Engines filed Critical Safran Aircraft Engines
Publication of BR112018012664A2 publication Critical patent/BR112018012664A2/pt
Publication of BR112018012664B1 publication Critical patent/BR112018012664B1/pt

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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • 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
    • F01D5/288—Protective coatings for 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
    • F04D29/02—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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/388—Blades characterised by construction
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • 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
    • 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)
  • Architecture (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

a invenção refere-se ao campo de pás de turbomáquina e, mais especificamente, a uma blindagem de bordo de ataque (32) para uma pá de turbomáquina (16), a dita blindagem de bordo de ataque (32) compreendendo um lado de pressão (34) e um lado de sucção (36). cada uma do lado de pressão (34) e do lado de sucção (36) se estende na direção de sua altura de uma borda inferior (50) para uma borda superior (51), e na direção de seu comprimento do bordo de ataque (18) para uma borda traseira (40, 42) e são conectadas através do bordo de ataque (18); a borda traseira (42) do lado de sucção (36) tem pelo menos um segmento (s1, s2) formado de tal modo que o comprimento da lado de sucção (36) dentro do dito segmento é menor que o comprimento (l2, l3, l21, l22, l31, l32) do lado de sucção (36) em cada extremidade do segmento (s1, s2).
BR112018012664-0A 2015-12-21 2016-12-21 Blindagem de bordo de ataque para uma pá de turbomáquina, pá, turbomáquina, ventoinha, e, turbofan BR112018012664B1 (pt)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1563007A FR3045712B1 (fr) 2015-12-21 2015-12-21 Bouclier de bord d'attaque
FR1563007 2015-12-21
PCT/FR2016/053607 WO2017109407A1 (fr) 2015-12-21 2016-12-21 Bouclier de bord d'attaque

Publications (2)

Publication Number Publication Date
BR112018012664A2 true BR112018012664A2 (pt) 2018-12-04
BR112018012664B1 BR112018012664B1 (pt) 2023-03-07

Family

ID=55542879

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112018012664-0A BR112018012664B1 (pt) 2015-12-21 2016-12-21 Blindagem de bordo de ataque para uma pá de turbomáquina, pá, turbomáquina, ventoinha, e, turbofan

Country Status (9)

Country Link
US (1) US11131196B2 (pt)
EP (1) EP3394398B1 (pt)
JP (1) JP6927978B2 (pt)
CN (1) CN108463614B (pt)
BR (1) BR112018012664B1 (pt)
CA (1) CA3009226A1 (pt)
FR (1) FR3045712B1 (pt)
RU (1) RU2728673C2 (pt)
WO (1) WO2017109407A1 (pt)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10760428B2 (en) * 2018-10-16 2020-09-01 General Electric Company Frangible gas turbine engine airfoil
US11466576B2 (en) * 2019-11-04 2022-10-11 Raytheon Technologies Corporation Airfoil with continuous stiffness joint
FR3103855B1 (fr) * 2019-11-29 2022-10-21 Safran Structure améliorée de bord d’attaque d’aube.
FR3115079B1 (fr) * 2020-10-12 2022-10-14 Safran Aircraft Engines Aube en materiau composite comprenant un bouclier de bord d’attaque, turbomachine comprenant l’aube
FR3123380A1 (fr) * 2021-05-28 2022-12-02 Safran Aircraft Engines Bouclier de bord d'attaque amélioré
FR3124217B1 (fr) * 2021-06-21 2023-06-30 Safran Aircraft Engines Procede de fabrication d’une aube composite de turbomachine avec controle du poids moment
FR3138816A1 (fr) * 2022-08-12 2024-02-16 Safran Aircraft Engines Piece pour une turbomachine d’aeronef et procede de fabrication associe

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1096294A (en) * 1964-06-12 1967-12-29 English Electric Co Ltd Turbine blades
US3989406A (en) * 1974-11-26 1976-11-02 Bolt Beranek And Newman, Inc. Method of and apparatus for preventing leading edge shocks and shock-related noise in transonic and supersonic rotor blades and the like
US4006999A (en) * 1975-07-17 1977-02-08 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Leading edge protection for composite blades
GB1500776A (en) * 1976-04-08 1978-02-08 Rolls Royce Fibre reinforced composite structures
JPS62165506A (ja) * 1986-01-16 1987-07-22 Toshiba Corp タ−ビン翼
JPS62165512A (ja) * 1986-01-17 1987-07-22 Toshiba Corp タ−ビン翼
DE3815906A1 (de) * 1988-05-10 1989-11-23 Mtu Muenchen Gmbh Luftschraubenblatt aus faserverstaerktem kunststoff
DE4411679C1 (de) * 1994-04-05 1994-12-01 Mtu Muenchen Gmbh Schaufelblatt in Faserverbundbauweise mit Schutzprofil
JPH094405A (ja) * 1995-06-21 1997-01-07 Mitsubishi Heavy Ind Ltd 蒸気タービンの耐摩耗性ブレード
JPH11182204A (ja) * 1997-12-15 1999-07-06 Toshiba Corp タービン動翼
US7736130B2 (en) * 2007-07-23 2010-06-15 General Electric Company Airfoil and method for protecting airfoil leading edge
FR2921099B1 (fr) * 2007-09-13 2013-12-06 Snecma Dispositif d'amortissement pour aube en materiau composite
US20110229334A1 (en) * 2010-03-16 2011-09-22 United Technologies Corporation Composite leading edge sheath and dovetail root undercut
EP2585370B1 (en) * 2010-06-22 2016-06-01 Sikorsky Aircraft Corporation Erosion resistant helicopter blade
US20120021243A1 (en) * 2010-07-23 2012-01-26 General Electric Company Components with bonded edges
FR2978931B1 (fr) * 2011-08-10 2014-05-09 Snecma Procede de realisation d'un renfort de protection du bord d'attaque d'une pale
EP2867473B1 (en) * 2012-06-21 2020-07-29 United Technologies Corporation Blades for an aviation engine and corresponding gas turbine aviation engine
FR2994708B1 (fr) * 2012-08-23 2018-07-27 Safran Aircraft Engines Aube a bord renforce pour une turbomachine
US20140219808A1 (en) * 2012-10-01 2014-08-07 United Technologies Corporation Sheath with extended wings
EP2971527B1 (en) * 2013-03-15 2020-08-05 United Technologies Corporation Hybrid fan blade biscuit construction
FR3017884B1 (fr) * 2014-02-25 2017-09-22 Snecma Bord de protection d'aube et son procede de fabrication

Also Published As

Publication number Publication date
FR3045712B1 (fr) 2020-11-13
EP3394398B1 (fr) 2022-04-27
JP2019500537A (ja) 2019-01-10
CA3009226A1 (fr) 2017-06-29
CN108463614A (zh) 2018-08-28
CN108463614B (zh) 2021-05-28
US20190003312A1 (en) 2019-01-03
WO2017109407A1 (fr) 2017-06-29
EP3394398A1 (fr) 2018-10-31
FR3045712A1 (fr) 2017-06-23
US11131196B2 (en) 2021-09-28
BR112018012664B1 (pt) 2023-03-07
RU2018126658A (ru) 2020-01-24
RU2728673C2 (ru) 2020-07-30
RU2018126658A3 (pt) 2020-05-29
JP6927978B2 (ja) 2021-09-01

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Legal Events

Date Code Title Description
B06U Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]
B09A Decision: intention to grant [chapter 9.1 patent gazette]
B16A Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]

Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 21/12/2016, OBSERVADAS AS CONDICOES LEGAIS