BR112015025386A2 - disco de ventilador para um motor turbojato e motor turbojato - Google Patents

disco de ventilador para um motor turbojato e motor turbojato

Info

Publication number
BR112015025386A2
BR112015025386A2 BR112015025386A BR112015025386A BR112015025386A2 BR 112015025386 A2 BR112015025386 A2 BR 112015025386A2 BR 112015025386 A BR112015025386 A BR 112015025386A BR 112015025386 A BR112015025386 A BR 112015025386A BR 112015025386 A2 BR112015025386 A2 BR 112015025386A2
Authority
BR
Brazil
Prior art keywords
turbojet engine
branch
fan
turbojet
fan disc
Prior art date
Application number
BR112015025386A
Other languages
English (en)
Other versions
BR112015025386B1 (pt
Inventor
Tan-Kim Alexandre
Accary Arnaud
Kiener-Calvet Benjamin
Petard Benjamin
Dejaune Claude
Foll Julien
Bois Stéphane
Original Assignee
Snecma
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 filed Critical Snecma
Publication of BR112015025386A2 publication Critical patent/BR112015025386A2/pt
Publication of BR112015025386B1 publication Critical patent/BR112015025386B1/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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • 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
    • F01D5/025—Fixing blade carrying members on shafts
    • 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
    • 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
    • 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
    • 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
    • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
    • F04D29/329—Details of the hub
    • 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
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet 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
    • 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
    • F05D2240/60—Shafts
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

resumo “disco de ventilador para um motor turbojato e motor turbojato” a invenção refere-se ao campo de turbomáquina e, mais particularmente, ao campo de motores turbojato que inclui um ventilador integral a um eixo de acionamento. o disco de ventilador (10) para um motor turbojato (1), em que um gás circula em uma direção de circulação, em que o mesmo tem uma seção radial no formato de um pino que inclui uma primeira ramificação (12), projetada para ser fixada a um eixo de acionamento (20) do motor turbojato (1), uma segunda ramificação (16), que se estende voltada para a primeira ramificação (12) e projetada para suportar uma pluralidade de pás de ventilador (3a), e uma parede de junção curvada (14) que se estende entre a primeira ramificação (12) e a segunda ramificação (16).
BR112015025386-5A 2013-04-09 2014-03-28 Disco de ventilador para um motor turbojato e motor turbojato BR112015025386B1 (pt)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1353177A FR3004227B1 (fr) 2013-04-09 2013-04-09 Disque de soufflante pour un turboreacteur
FR1353177 2013-04-09
PCT/FR2014/050743 WO2014167209A1 (fr) 2013-04-09 2014-03-28 Disque de soufflante pour un turboréacteur et turboréacteur

Publications (2)

Publication Number Publication Date
BR112015025386A2 true BR112015025386A2 (pt) 2017-07-18
BR112015025386B1 BR112015025386B1 (pt) 2022-01-25

Family

ID=48468607

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112015025386-5A BR112015025386B1 (pt) 2013-04-09 2014-03-28 Disco de ventilador para um motor turbojato e motor turbojato

Country Status (8)

Country Link
US (1) US10125630B2 (pt)
EP (2) EP3124795B1 (pt)
CN (2) CN105308332B (pt)
BR (1) BR112015025386B1 (pt)
CA (1) CA2908363C (pt)
FR (1) FR3004227B1 (pt)
RU (2) RU2668511C2 (pt)
WO (1) WO2014167209A1 (pt)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3048015B1 (fr) * 2016-02-19 2020-03-06 Safran Aircraft Engines Aube de turbomachine, comprenant un pied aux concentrations de contrainte reduites
FR3057907B1 (fr) * 2016-10-24 2019-11-22 Safran Aircraft Engines Ensemble a effet anti-usure pour turboreacteur
FR3066552B1 (fr) * 2017-05-22 2021-11-19 Safran Aircraft Engines Assemblage sur un arbre de turbomachine d'un disque aubage monobloc et d'un rotor de compresseur basse pression a au moins deux etages d'aubes mobiles
GB201800511D0 (en) * 2018-01-12 2018-02-28 Rolls Royce Plc Fan disc assembly
GB201800512D0 (en) * 2018-01-12 2018-02-28 Rolls Royce Plc Fan disc assembly
US11365630B1 (en) * 2020-12-28 2022-06-21 Rolls-Royce North American Technologies Inc. Fan rotor with tapered drive joint

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US5112193A (en) * 1990-09-11 1992-05-12 Pratt & Whitney Canada Fan blade axial retention device
US5067877A (en) * 1990-09-11 1991-11-26 United Technologies Corporation Fan blade axial retention device
FR2752024B1 (fr) 1996-08-01 1998-09-04 Snecma Support d'arbre cassant a l'apparition d'un balourd
US6564317B1 (en) * 1999-12-20 2003-05-13 Intel Corporation Method and apparatus for securing computer firmware wherein unlocking of nonvolatile memory is prohibited unless address line masking Is disabled during an initialization event
US6390775B1 (en) * 2000-12-27 2002-05-21 General Electric Company Gas turbine blade with platform undercut
FR2831624A1 (fr) 2001-10-31 2003-05-02 Snecma Moteurs Systeme decoupleur pour l'arbre d'une soufflante de turboreacteur
DE10218459B3 (de) * 2002-04-25 2004-01-15 Mtu Aero Engines Gmbh Verdichter in mehrstufiger Axialbauart
US6902376B2 (en) * 2002-12-26 2005-06-07 General Electric Company Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
US7121803B2 (en) * 2002-12-26 2006-10-17 General Electric Company Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
US6761536B1 (en) * 2003-01-31 2004-07-13 Power Systems Mfg, Llc Turbine blade platform trailing edge undercut
US6951447B2 (en) * 2003-12-17 2005-10-04 United Technologies Corporation Turbine blade with trailing edge platform undercut
US7153102B2 (en) * 2004-05-14 2006-12-26 Pratt & Whitney Canada Corp. Bladed disk fixing undercut
US7252481B2 (en) * 2004-05-14 2007-08-07 Pratt & Whitney Canada Corp. Natural frequency tuning of gas turbine engine blades
FR2875842B1 (fr) * 2004-09-28 2010-09-24 Snecma Moteurs Dispositif de limitation de survitesse de turbine dans une turbomachine
WO2006124617A2 (en) * 2005-05-12 2006-11-23 General Electric Company BLADE/DISK DOVETAIL BACKCUT FOR BLADE/DISK STRESS REDUCTION (9FA+e, STAGE 1)
US7452188B2 (en) * 2005-09-26 2008-11-18 Pratt & Whitney Canada Corp. Pre-stretched tie-bolt for use in a gas turbine engine and method
US7513103B2 (en) * 2005-10-19 2009-04-07 General Electric Company Gas turbine engine assembly and methods of assembling same
US7476085B2 (en) * 2006-05-12 2009-01-13 General Electric Company Blade/disk dovetail backcut for blade/disk stress reduction (6FA+E, stage2)
US7594799B2 (en) * 2006-09-13 2009-09-29 General Electric Company Undercut fillet radius for blade dovetails
FR2913734B1 (fr) * 2007-03-16 2009-05-01 Snecma Sa Soufflante de turbomachine
RU74166U1 (ru) * 2007-12-17 2008-06-20 Открытое акционерное общество "Климов" Рабочее колесо турбины
US8240042B2 (en) * 2008-05-12 2012-08-14 Wood Group Heavy Industrial Turbines Ag Methods of maintaining turbine discs to avert critical bucket attachment dovetail cracks
US8287241B2 (en) * 2008-11-21 2012-10-16 Alstom Technology Ltd Turbine blade platform trailing edge undercut
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FR2974864B1 (fr) * 2011-05-04 2016-05-27 Snecma Rotor de turbomachine avec moyen de retenue axiale des aubes
FR2974863B1 (fr) * 2011-05-06 2015-10-23 Snecma Disque de soufflante de turbomachine
US9169730B2 (en) * 2011-11-16 2015-10-27 Pratt & Whitney Canada Corp. Fan hub design
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US20170074107A1 (en) * 2015-09-15 2017-03-16 General Electric Company Blade/disk dovetail backcut for blade disk stress reduction (9e.04, stage 2)

Also Published As

Publication number Publication date
CN108843410B (zh) 2021-01-01
RU2761506C2 (ru) 2021-12-08
RU2668511C2 (ru) 2018-10-01
RU2018131434A3 (pt) 2021-11-17
CN105308332B (zh) 2017-09-08
RU2015147901A (ru) 2017-05-15
US20160069207A1 (en) 2016-03-10
RU2015147901A3 (pt) 2018-03-26
RU2018131434A (ru) 2018-10-02
BR112015025386B1 (pt) 2022-01-25
CN105308332A (zh) 2016-02-03
EP2984349B1 (fr) 2021-05-26
EP2984349A1 (fr) 2016-02-17
FR3004227A1 (fr) 2014-10-10
CN108843410A (zh) 2018-11-20
WO2014167209A1 (fr) 2014-10-16
FR3004227B1 (fr) 2016-10-21
CA2908363A1 (fr) 2014-10-16
US10125630B2 (en) 2018-11-13
CA2908363C (fr) 2021-11-02
EP3124795A1 (fr) 2017-02-01
EP3124795B1 (fr) 2018-12-26

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Legal Events

Date Code Title Description
B06F Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]
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 28/03/2014, OBSERVADAS AS CONDICOES LEGAIS.