BR112015003953A2 - rotor de turbina para uma turbomáquina - Google Patents

rotor de turbina para uma turbomáquina

Info

Publication number
BR112015003953A2
BR112015003953A2 BR112015003953A BR112015003953A BR112015003953A2 BR 112015003953 A2 BR112015003953 A2 BR 112015003953A2 BR 112015003953 A BR112015003953 A BR 112015003953A BR 112015003953 A BR112015003953 A BR 112015003953A BR 112015003953 A2 BR112015003953 A2 BR 112015003953A2
Authority
BR
Brazil
Prior art keywords
disc
turbine rotor
teeth
turbomachine
blades
Prior art date
Application number
BR112015003953A
Other languages
English (en)
Inventor
Roussely-Rousseau Amaury
Burlet Guy
Mareix Jean-Pierre
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 BR112015003953A2 publication Critical patent/BR112015003953A2/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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • 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
    • 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
    • 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
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • 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
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1/1 resumo “rotor de turbina para uma turbomáquina” a invenção se refere a um rotor de turbina para uma turbomáquina, que compreende um disco (21) que compreende alvéolos que servem para a montagem de pés de pás, cada alvéolo sendo delimitado por dois dentes (5) adjacentes do disco (21), os pés de pás compreendendo faces de apoio que vêm se apoiar sobre faces de apoio dos dentes (5) do disco (21). lâminas (24) são montadas sobre os dentes (5) do disco (21), cada lâmina (24) tendo uma forma geral em u que compreende partes laterais de apoio intercaladas entre as faces de apoio correspondentes dos pés de pás e dos dentes (5) do disco (21), e uma parte mediana (26) situada em frente ao topo do dente correspondente (5) do disco (21) e que delimita uma cavidade (27) entre o dito topo e a lâmina (24). o rotor de turbina compreende por outro lado meios (28) de admissão de ar de resfriamento dentro da dita cavidade (27).
BR112015003953A 2012-09-03 2013-08-29 rotor de turbina para uma turbomáquina BR112015003953A2 (pt)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1258190A FR2995003B1 (fr) 2012-09-03 2012-09-03 Rotor de turbine pour une turbomachine
PCT/FR2013/051995 WO2014033408A1 (fr) 2012-09-03 2013-08-29 Rotor de turbine pour une turbomachine

Publications (1)

Publication Number Publication Date
BR112015003953A2 true BR112015003953A2 (pt) 2017-07-04

Family

ID=47137889

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112015003953A BR112015003953A2 (pt) 2012-09-03 2013-08-29 rotor de turbina para uma turbomáquina

Country Status (9)

Country Link
US (1) US10329912B2 (pt)
EP (1) EP2893141B1 (pt)
JP (1) JP6212558B2 (pt)
CN (1) CN104603397B (pt)
BR (1) BR112015003953A2 (pt)
CA (1) CA2882320A1 (pt)
FR (1) FR2995003B1 (pt)
RU (1) RU2015112099A (pt)
WO (1) WO2014033408A1 (pt)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2981132B1 (fr) * 2011-10-10 2013-12-06 Snecma Ensemble pour turbomachine a refroidissement de disque
US10822952B2 (en) 2013-10-03 2020-11-03 Raytheon Technologies Corporation Feature to provide cooling flow to disk
US9835032B2 (en) * 2015-06-01 2017-12-05 United Technologies Corporation Disk lug cooling flow trenches
FR3037367B1 (fr) * 2015-06-15 2017-06-30 Snecma Ensemble rotatif de turbomachine a garnitures de protection bombees
FR3057015B1 (fr) * 2016-09-30 2018-12-07 Safran Aircraft Engines Disque de rotor comportant une toile a epaisseur variable
DE102018207873A1 (de) * 2018-05-18 2019-11-21 MTU Aero Engines AG Laufschaufel für eine Strömungsmaschine
FR3095234B1 (fr) * 2019-04-19 2021-07-09 Safran Aircraft Engines Ensemble de turbomachine comprenant un dispositif de limitation de temperature pour fond d’alveole non refroidi
FR3096397B1 (fr) * 2019-05-21 2021-04-16 Safran Aircraft Engines Pion amovible sur distributeur de turbomachine
FR3096734B1 (fr) * 2019-05-29 2021-12-31 Safran Aircraft Engines Ensemble pour turbomachine
FR3099520B1 (fr) * 2019-07-31 2021-07-23 Safran Aircraft Engines Roue de turbomachine
US11352903B2 (en) 2020-01-20 2022-06-07 Raytheon Technologies Corporation Rotor stack bushing with adaptive temperature metering for a gas turbine engine
CN112444398A (zh) * 2020-11-23 2021-03-05 东方电气集团东方汽轮机有限公司 一种燃气轮机转子冷气输送试验件及试验参数设计方法
US11773731B2 (en) 2022-01-04 2023-10-03 Rtx Corporation Bathtub damper seal arrangement for gas turbine engine
CN117027966B (zh) * 2023-08-09 2024-04-05 秦皇岛华宇通电力科技有限公司 用于减少轴端汽封漏气量的u型齿扰流汽封装置

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3290466A (en) 1964-09-16 1966-12-06 Universal Oil Prod Co Pressure switch with high and low limits
FR2503247B1 (fr) * 1981-04-07 1985-06-14 Snecma Perfectionnements aux etages de turbine a gaz de turboreacteurs munis de moyens de refroidissement par air du disque de la roue de la turbine
JPS5999101U (ja) * 1982-12-24 1984-07-04 株式会社日立製作所 ガスタ−ビンの動翼固定装置
JPH0618602U (ja) * 1992-08-10 1994-03-11 石川島播磨重工業株式会社 タービン動翼のダンパー
US5281097A (en) * 1992-11-20 1994-01-25 General Electric Company Thermal control damper for turbine rotors
JP2595474Y2 (ja) * 1993-06-29 1999-05-31 石川島播磨重工業株式会社 タービン動翼植込部の緩衝材
JPH078502U (ja) * 1993-06-29 1995-02-07 三菱重工業株式会社 翼止装置
US5800124A (en) * 1996-04-12 1998-09-01 United Technologies Corporation Cooled rotor assembly for a turbine engine
FR2831207B1 (fr) * 2001-10-24 2004-06-04 Snecma Moteurs Plates-formes pour aubes d'un ensemble rotatif
GB2409240B (en) * 2003-12-18 2007-04-11 Rolls Royce Plc A gas turbine rotor
FR2913735B1 (fr) * 2007-03-16 2013-04-19 Snecma Disque de rotor d'une turbomachine
FR2918703B1 (fr) * 2007-07-13 2009-10-16 Snecma Sa Ensemble de rotor de turbomachine
FR2918702B1 (fr) * 2007-07-13 2009-10-16 Snecma Sa Clinquant pour aube de turbomachine
US8616832B2 (en) * 2009-11-30 2013-12-31 Honeywell International Inc. Turbine assemblies with impingement cooling
GB201016597D0 (en) * 2010-10-04 2010-11-17 Rolls Royce Plc Turbine disc cooling arrangement

Also Published As

Publication number Publication date
CA2882320A1 (fr) 2014-03-06
JP6212558B2 (ja) 2017-10-11
RU2015112099A (ru) 2016-10-20
US20150322796A1 (en) 2015-11-12
EP2893141B1 (fr) 2016-10-26
JP2015526650A (ja) 2015-09-10
FR2995003A1 (fr) 2014-03-07
CN104603397B (zh) 2016-06-29
WO2014033408A1 (fr) 2014-03-06
CN104603397A (zh) 2015-05-06
EP2893141A1 (fr) 2015-07-15
FR2995003B1 (fr) 2014-08-15
US10329912B2 (en) 2019-06-25

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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]
B08F Application dismissed because of non-payment of annual fees [chapter 8.6 patent gazette]

Free format text: REFERENTE A 6A ANUIDADE.

B08K Patent lapsed as no evidence of payment of the annual fee has been furnished to inpi [chapter 8.11 patent gazette]

Free format text: EM VIRTUDE DO ARQUIVAMENTO PUBLICADO NA RPI 2529 DE 25-06-2019 E CONSIDERANDO AUSENCIA DE MANIFESTACAO DENTRO DOS PRAZOS LEGAIS, INFORMO QUE CABE SER MANTIDO O ARQUIVAMENTO DO PEDIDO DE PATENTE, CONFORME O DISPOSTO NO ARTIGO 12, DA RESOLUCAO 113/2013.