BR112016028347A8 - rotor para turbomáquina que compreende pás com plataformas adicionais - Google Patents

rotor para turbomáquina que compreende pás com plataformas adicionais

Info

Publication number
BR112016028347A8
BR112016028347A8 BR112016028347A BR112016028347A BR112016028347A8 BR 112016028347 A8 BR112016028347 A8 BR 112016028347A8 BR 112016028347 A BR112016028347 A BR 112016028347A BR 112016028347 A BR112016028347 A BR 112016028347A BR 112016028347 A8 BR112016028347 A8 BR 112016028347A8
Authority
BR
Brazil
Prior art keywords
rotor
blades
cavities
bulb
turbomachinery
Prior art date
Application number
BR112016028347A
Other languages
English (en)
Other versions
BR112016028347A2 (pt
BR112016028347B1 (pt
Inventor
Jean-Philippe Beaujard Antoine
Trappier Nicolas
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
Application filed by Safran Aircraft Engines filed Critical Safran Aircraft Engines
Publication of BR112016028347A2 publication Critical patent/BR112016028347A2/pt
Publication of BR112016028347A8 publication Critical patent/BR112016028347A8/pt
Publication of BR112016028347B1 publication Critical patent/BR112016028347B1/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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • 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)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

rotor para turbomáquina que compreende pás com plataformas adicionais. a invenção visa fornecer um rotor a uma turbomáquina que compreende: um disco que apresenta cavidades em sua periferia, denominadas cavidades primárias; uma pluralidade de pás (100), que apresentam uma base (110) que consiste em, na porção inferior da mesma, um bulbo (120) travado axialmente nas ditas cavidades primárias; uma pluralidade de plataformas adicionais (300, 400), em que cada uma está disposta entre duas pás (100) consecutivas; sendo que o dito rotor é distinguido pelo fato de que as ditas plataformas (300, 400) apresentam: uma placa substancialmente retilínea (301, 401) e um bulbo (302, 402) que se estende radialmente sob a placa (301, 401), sendo que o dito bulbo (302, 402) é travado axialmente nas cavidades secundárias dispostas na periferia do disco, em que as cavidades secundárias estão posicionadas entre duas cavidades primárias consecutivas; um spoiler (310, 410) que se estende de modo substancialmente axial, em que o dito spoiler (310, 410) forma um setor anular disposto voltado para pelo menos duas pás consecutivas.
BR112016028347-3A 2014-06-03 2015-06-03 Rotor para turbomáquina que compreende pás com plataformas adicionais BR112016028347B1 (pt)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1455017 2014-06-03
FR1455017A FR3021691B1 (fr) 2014-06-03 2014-06-03 Rotor pour turbomachine comportant des aubes a plates-formes raportees
PCT/FR2015/051471 WO2015185860A1 (fr) 2014-06-03 2015-06-03 Rotor pour turbomachine comportant des aubes a plates formes rapportées

Publications (3)

Publication Number Publication Date
BR112016028347A2 BR112016028347A2 (pt) 2017-08-22
BR112016028347A8 true BR112016028347A8 (pt) 2021-06-29
BR112016028347B1 BR112016028347B1 (pt) 2022-08-09

Family

ID=51862389

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112016028347-3A BR112016028347B1 (pt) 2014-06-03 2015-06-03 Rotor para turbomáquina que compreende pás com plataformas adicionais

Country Status (8)

Country Link
US (1) US10138737B2 (pt)
EP (1) EP3152404B1 (pt)
CN (1) CN106536862B (pt)
BR (1) BR112016028347B1 (pt)
CA (1) CA2951014C (pt)
FR (1) FR3021691B1 (pt)
RU (1) RU2692863C2 (pt)
WO (1) WO2015185860A1 (pt)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3085711B1 (fr) * 2018-09-06 2021-07-23 Safran Aircraft Engines Roue a aubes de turbomachine pour aeronef
GB202114773D0 (en) 2021-10-15 2021-12-01 Rolls Royce Plc Bladed disc
GB202114772D0 (en) * 2021-10-15 2021-12-01 Rolls Royce Plc Bladed disc
FR3140649A1 (fr) * 2022-10-07 2024-04-12 Safran Aircraft Engines Disque pour une turbine de turbomachine d’aeronef

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1426933A (fr) * 1964-08-05 1966-02-04 Gen Electric Perfectionnements aux rotors de turbomachines
US4033705A (en) * 1976-04-26 1977-07-05 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Blade retainer assembly
FR2524933B1 (fr) * 1982-04-13 1987-02-20 Snecma Dispositif de verrouillage axial d'aubes de rotor de turbine ou de compresseur
FR2608674B1 (fr) 1986-12-17 1991-04-19 Snecma Roue de turbine a aubes ceramique
FR2669686B1 (fr) * 1990-11-28 1994-09-02 Snecma Rotor de soufflante avec aubes sans plates-formes et sabots reconstituant le profil de veine.
FR2831207B1 (fr) 2001-10-24 2004-06-04 Snecma Moteurs Plates-formes pour aubes d'un ensemble rotatif
US7284958B2 (en) * 2003-03-22 2007-10-23 Allison Advanced Development Company Separable blade platform
US8105041B2 (en) * 2005-09-07 2012-01-31 Siemens Aktiengesellschaft Arrangement for axially securing rotating blades in a rotor, sealing element for such an arrangement, and use of such an arrangement
EP1944471B1 (de) * 2007-01-09 2009-09-02 Siemens Aktiengesellschaft Axialer Rotorabschnitt für einen Rotor einer Turbine
EP1978211A1 (de) * 2007-04-04 2008-10-08 Siemens Aktiengesellschaft Anordnung zur Axialsicherung an Laufschaufeln in einem Rotor sowie Gasturbine mit einer solchen Anordnung
US7878763B2 (en) * 2007-05-15 2011-02-01 General Electric Company Turbine rotor blade assembly and method of assembling the same
FR2918409B1 (fr) * 2007-07-05 2011-05-27 Snecma Partie tournante de turbomachine comprenant des secteurs inter-aubes formant plateforme rapportes fixement sur un disque

Also Published As

Publication number Publication date
BR112016028347A2 (pt) 2017-08-22
CN106536862A (zh) 2017-03-22
RU2016151174A3 (pt) 2018-12-06
US10138737B2 (en) 2018-11-27
RU2016151174A (ru) 2018-07-09
CA2951014A1 (fr) 2015-12-10
FR3021691A1 (fr) 2015-12-04
EP3152404A1 (fr) 2017-04-12
FR3021691B1 (fr) 2016-06-24
US20170218778A1 (en) 2017-08-03
CA2951014C (fr) 2022-04-26
CN106536862B (zh) 2018-09-18
EP3152404B1 (fr) 2018-08-01
WO2015185860A1 (fr) 2015-12-10
RU2692863C2 (ru) 2019-06-28
BR112016028347B1 (pt) 2022-08-09

Similar Documents

Publication Publication Date Title
BR112014029523A8 (pt) Pá de ventilador para turborreator de avião, ventilador de turborreator de avião, e, turborreator de avião
BR112016028347A8 (pt) rotor para turbomáquina que compreende pás com plataformas adicionais
BR112018006250A2 (pt) adjunto implantável que compreende camadas de ligação
BR112014012584A2 (pt) pá de turbomáquina, notadamente para disco com pás monobloco
BR112016030417A8 (pt) conjunto giratório para uma turbomáquina, turbina para uma turbomáquina e turbomáquina
BR112017006884A2 (pt) estator de turbomáquina de aeronave
ES2721160T3 (es) Grupo de álabes directores para una turbomáquina
BR112019007756A2 (pt) roda de corte, disco de corte e bem como montagem de cortador adequada para bombas trituradoras
BR112016007481A2 (pt) método para fabricar um estágio de uma turbina a vapor, setor para a montagem e estágio para uma turbina a vapor
BR112017002041A2 (pt) módulo de turbomáquina
BR112019002573A2 (pt) pneu, padrão de banda de rodagem, e, método para aumentar a resistência ao arrancamento e ao craqueamento de uma banda de rodagem de um pneu
BR112015020351A2 (pt) conjunto de disco de turbina e de lâmina, sistema para prevenir o vazamento de ar dentro de uma turbina, método de montagem de um conjunto de disco de turbina e de lâmina e método para prevenir vazamento de ar em uma turbina
BR112016001910A2 (pt) método para fabricar um invólucro de motor de turbina, invólucro de motor de turbina e motor de turbina
BR112016013725A8 (pt) anel de vedação e disposição de vedação
BR112017005641A2 (pt) roda de ventilador segmentada
BR112017008593A2 (pt) aleta de rotor para uma turbomáquina, conjunto giratório para uma turbomáquina, métodos de funcionamento de um conjunto giratório para uma turbomáquina e método de produção de uma aleta de rotor para uma turbomáquina
BR112017012593A2 (pt) conjunto de turbina de turbomáquina de aeronave
BR102016014684A8 (pt) ventiladores para um motor de turbina a gás
BR112017008587A2 (pt) pá de turbina de turbomáquina, disco de turbina e turbina de alta pressão de turborreator
BR112017009459A2 (pt) motor de indução
BR112016028799A2 (pt) conjunto de disco do rotor, sistema de geração de potência e método de fabricação de um conjunto de disco do rotor
BR112017001603A2 (pt) disco de roda para uma roda de disco
BR112017025336A2 (pt) rotor para uma máquina de fluido tendo pás removíveis
BR112015028949A2 (pt) montagem de turbomáquina, turbomáquina e métodos para montar uma montagem de turbomáquina e para desmontar uma montagem de turbomáquina
BR112015004935A2 (pt) dispositivo rotor para máquina de fluxo de fluido hidráulico

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 03/06/2015, OBSERVADAS AS CONDICOES LEGAIS