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BR112015020351A2 - 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 - Google Patents

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

Info

Publication number
BR112015020351A2
BR112015020351A2 BR112015020351A BR112015020351A BR112015020351A2 BR 112015020351 A2 BR112015020351 A2 BR 112015020351A2 BR 112015020351 A BR112015020351 A BR 112015020351A BR 112015020351 A BR112015020351 A BR 112015020351A BR 112015020351 A2 BR112015020351 A2 BR 112015020351A2
Authority
BR
Brazil
Prior art keywords
turbine
disk
air leakage
preventing air
disc assembly
Prior art date
Application number
BR112015020351A
Other languages
English (en)
Inventor
Jared Agnew Brian
Hamilton Grooms James
Alan Hile Michael
William Jendrix Richard
Original Assignee
Gen Electric
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 Gen Electric filed Critical Gen Electric
Publication of BR112015020351A2 publication Critical patent/BR112015020351A2/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
    • F01D5/30—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
    • 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
    • F01D5/3084—Fixing blades to rotors; Blade roots ; Blade spacers the blades being made of ceramics
    • 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
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • 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
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • F05D2300/5021—Expansivity
    • F05D2300/50212—Expansivity dissimilar
    • 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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

resumo “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” trate-se de um conjunto de disco de turbina e de lâmina que compreende um disco de turbina que inclui uma pluralidade de raios de disco que se estendem radialmente a partir do mesmo e uma pluralidade de fendas de disco entre os raios de disco adjacentes. o disco de turbina é de um primeiro material que tem um primeiro coeficiente de expansão térmica. o conjunto compreende adicionalmente uma pluralidade de lâminas de turbina. uma das lâminas de turbina é recebida em cada fenda de disco. as lâminas de turbina são de um segundo material que tem um segundo coeficiente de expansão térmica. o conjunto compreende adicionalmente uma pluralidade de placas de vedação, em que uma das placas de vedação é posicionada em cada fenda de disco radialmente para dentro da lâmina de turbina. as placas de vedação são de um material que tem um coeficiente de expansão térmica substancialmente semelhante àquele dos raios de disco ou da lâmina de turbina.
BR112015020351A 2013-03-08 2014-01-30 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 BR112015020351A2 (pt)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/790,758 US9453422B2 (en) 2013-03-08 2013-03-08 Device, system and method for preventing leakage in a turbine
PCT/US2014/013710 WO2014171990A2 (en) 2013-03-08 2014-01-30 Device, system and method for preventing leakage in a turbine

Publications (1)

Publication Number Publication Date
BR112015020351A2 true BR112015020351A2 (pt) 2017-07-18

Family

ID=51303103

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112015020351A BR112015020351A2 (pt) 2013-03-08 2014-01-30 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

Country Status (7)

Country Link
US (1) US9453422B2 (pt)
EP (1) EP2964896B1 (pt)
JP (1) JP6244383B2 (pt)
CN (1) CN105264176B (pt)
BR (1) BR112015020351A2 (pt)
CA (1) CA2902812C (pt)
WO (1) WO2014171990A2 (pt)

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US10428661B2 (en) * 2016-10-26 2019-10-01 Roll-Royce North American Technologies Inc. Turbine wheel assembly with ceramic matrix composite components
FR3075895B1 (fr) * 2017-12-22 2020-10-16 Arianegroup Sas Ensemble mecanique constitue par assemblage de pieces axisymetriques
US11156111B2 (en) 2018-08-31 2021-10-26 Rolls-Royce Corporation Pinned platform for blade with circumferential attachment
US10633986B2 (en) 2018-08-31 2020-04-28 Rolls-Roye Corporation Platform with axial attachment for blade with circumferential attachment
US10641111B2 (en) 2018-08-31 2020-05-05 Rolls-Royce Corporation Turbine blade assembly with ceramic matrix composite components
FR3092609B1 (fr) * 2019-02-12 2021-02-12 Safran Aircraft Engines Ensemble de turbine pour turbomachine d’aeronef a circuit de refroidissement de disque ameliore
US10876429B2 (en) 2019-03-21 2020-12-29 Pratt & Whitney Canada Corp. Shroud segment assembly intersegment end gaps control
JP7236337B2 (ja) * 2019-06-19 2023-03-09 三菱重工業株式会社 複合材翼及び複合材翼の成形方法
DE102019215220A1 (de) * 2019-10-02 2021-04-08 MTU Aero Engines AG System mit einer Laufschaufel für eine Gasturbine mit einem einen Dichtungsabschnitt aufweisenden Schaufelfußschutzblech

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Also Published As

Publication number Publication date
US20140286756A1 (en) 2014-09-25
WO2014171990A2 (en) 2014-10-23
EP2964896A2 (en) 2016-01-13
CA2902812C (en) 2017-12-05
JP2016510850A (ja) 2016-04-11
CA2902812A1 (en) 2014-10-23
WO2014171990A3 (en) 2014-12-24
CN105264176A (zh) 2016-01-20
US9453422B2 (en) 2016-09-27
EP2964896B1 (en) 2019-10-09
CN105264176B (zh) 2017-05-03
JP6244383B2 (ja) 2018-02-14

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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]
B11B Dismissal acc. art. 36, par 1 of ipl - no reply within 90 days to fullfil the necessary requirements