BRPI0908165A2 - distribuidor satorizado para uma turbomáquina, turbina baixa-pressão de turbomáquina e turbomáquina tal como um turborreator ou um turbopropulsor de avião - Google Patents

distribuidor satorizado para uma turbomáquina, turbina baixa-pressão de turbomáquina e turbomáquina tal como um turborreator ou um turbopropulsor de avião

Info

Publication number
BRPI0908165A2
BRPI0908165A2 BRPI0908165A BRPI0908165A BRPI0908165A2 BR PI0908165 A2 BRPI0908165 A2 BR PI0908165A2 BR PI0908165 A BRPI0908165 A BR PI0908165A BR PI0908165 A BRPI0908165 A BR PI0908165A BR PI0908165 A2 BRPI0908165 A2 BR PI0908165A2
Authority
BR
Brazil
Prior art keywords
turbomachine
satorized
turbojet
manifold
low
Prior art date
Application number
BRPI0908165A
Other languages
English (en)
Inventor
Bruno Marie Benjamin Jacques Richard
Christian Bernard Bariaud
Eric René Herzer
Sébastien Digard Brou De Cuissart
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 BRPI0908165A2 publication Critical patent/BRPI0908165A2/pt
Publication of BRPI0908165A8 publication Critical patent/BRPI0908165A8/pt
Publication of BRPI0908165B1 publication Critical patent/BRPI0908165B1/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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)
BRPI0908165 2008-03-19 2009-03-17 distribuidor setorizado para uma turbomáquina, turbina baixa-pressão de turbomáquina e turbomáquina tal como um turborreator ou um turbopropulsor de avião BRPI0908165B1 (pt)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0801499A FR2928961B1 (fr) 2008-03-19 2008-03-19 Distributeur sectorise pour une turbomachine.
PCT/FR2009/000277 WO2009125078A2 (fr) 2008-03-19 2009-03-17 Distributeur sectorisé pour une turbomachine

Publications (3)

Publication Number Publication Date
BRPI0908165A2 true BRPI0908165A2 (pt) 2015-12-15
BRPI0908165A8 BRPI0908165A8 (pt) 2019-01-29
BRPI0908165B1 BRPI0908165B1 (pt) 2019-12-03

Family

ID=39832406

Family Applications (1)

Application Number Title Priority Date Filing Date
BRPI0908165 BRPI0908165B1 (pt) 2008-03-19 2009-03-17 distribuidor setorizado para uma turbomáquina, turbina baixa-pressão de turbomáquina e turbomáquina tal como um turborreator ou um turbopropulsor de avião

Country Status (9)

Country Link
US (1) US8602726B2 (pt)
EP (1) EP2252772B1 (pt)
JP (1) JP5759363B2 (pt)
CN (1) CN101970804B (pt)
BR (1) BRPI0908165B1 (pt)
CA (1) CA2715454C (pt)
FR (1) FR2928961B1 (pt)
RU (1) RU2494264C2 (pt)
WO (1) WO2009125078A2 (pt)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2971022B1 (fr) * 2011-02-02 2013-01-04 Snecma Etage redresseur de compresseur pour une turbomachine
FR2979662B1 (fr) 2011-09-07 2013-09-27 Snecma Procede de fabrication d'un secteur de distributeur de turbine ou redresseur de compresseur en materiau composite pour turbomachine et turbine ou compresseur incorporant un distributeur ou un redresseur forme de tels secteurs
FR2988429B1 (fr) * 2012-03-26 2017-02-24 Snecma Aubage de turbomachine avec couronne interne rapportee et assemblage simplifie
EP2722486B1 (de) * 2012-10-17 2016-12-07 MTU Aero Engines AG Dichtungsträger für eine Leitschaufelanordnung
FR3001252B1 (fr) * 2013-01-23 2015-02-13 Snecma Aubage fixe de distribution de flux comprenant une plate-forme interne a renforts integres
FR3036436B1 (fr) * 2015-05-22 2020-01-24 Safran Ceramics Ensemble d'anneau de turbine avec maintien par brides
EP3290642A1 (de) * 2016-08-31 2018-03-07 Siemens Aktiengesellschaft Ringsegment für eine turbine und anordnung zur äusseren be-grenzung eines strömungspfades einer turbine
DE102017209420A1 (de) * 2017-06-02 2018-12-06 MTU Aero Engines AG Dichtungsanordnung mit angeschweißtem Dichtungsblech, Strömungsmaschine und Herstellungsverfahren
FR3091311B1 (fr) * 2018-12-31 2021-04-09 Safran Aircraft Engines Distributeur pour turbine, turbine de turbomachine équipée de ce distributeur et turbomachine équipée de cette turbine.
IT201900013218A1 (it) * 2019-07-29 2021-01-29 Ge Avio Srl Fascia interna per motore a turbina.
CN111561473B (zh) * 2020-05-25 2021-10-01 中国航发沈阳发动机研究所 一种风扇静子机匣结构
FR3113298B1 (fr) * 2020-08-10 2023-09-01 Safran Aircraft Engines Porte-abradable d’un distributeur basse pression comprenant une unique tôle
FR3120911A1 (fr) * 2021-03-16 2022-09-23 Safran Aircraft Engines Aube comprenant un membre d’attache résistant au frottement et roue mobile comprenant une telle aube d’une turbine axiale de turbomachine

Family Cites Families (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3941500A (en) * 1974-06-10 1976-03-02 Westinghouse Electric Corporation Turbomachine interstage seal assembly
FR2452590A1 (fr) * 1979-03-27 1980-10-24 Snecma Garniture d'etancheite amovible pour segment de distributeur de turbomachine
FR2524934B1 (fr) * 1982-04-08 1986-12-26 Snecma Dispositif de butee de securite pour pivot d'aubes de stator a calage variable
FR2556410B1 (fr) * 1983-12-07 1986-09-12 Snecma Dispositif de centrage de l'anneau interieur d'un stator a ailettes a calage variable
CN1006512B (zh) * 1985-07-10 1990-01-17 阿尔斯汤姆大西洋有限公司 涡轮发电机转子励磁绕组-端的护环下面的一种冷却气体分配装置
US4767267A (en) 1986-12-03 1988-08-30 General Electric Company Seal assembly
US4897021A (en) * 1988-06-02 1990-01-30 United Technologies Corporation Stator vane asssembly for an axial flow rotary machine
US5062767A (en) * 1990-04-27 1991-11-05 The United States Of America As Represented By The Secretary Of The Air Force Segmented composite inner shrouds
US5215435A (en) * 1991-10-28 1993-06-01 General Electric Company Angled cooling air bypass slots in honeycomb seals
FR2691749B1 (fr) * 1992-05-27 1994-07-22 Snecma Dispositif d'etancheite entre des etages d'aubes et un tambour tournant notamment pour eviter les fuites autour des etages d'aubes de redresseur .
US5346362A (en) * 1993-04-26 1994-09-13 United Technologies Corporation Mechanical damper
US5749701A (en) * 1996-10-28 1998-05-12 General Electric Company Interstage seal assembly for a turbine
US6139264A (en) * 1998-12-07 2000-10-31 General Electric Company Compressor interstage seal
ITMI991206A1 (it) * 1999-05-31 2000-12-01 Nuovo Pignone Spa Dispositivo di supporto e bloccaggio per ugelli di uno stadio ad altapressione in turbine a gas
FR2830873B1 (fr) * 2001-10-16 2004-01-16 Snecma Moteurs Procede de protection par aluminisation de pieces metalliques constituees au moins en partie par une structure en nid d'abeilles
US6901821B2 (en) * 2001-11-20 2005-06-07 United Technologies Corporation Stator damper anti-rotation assembly
FR2835563B1 (fr) * 2002-02-07 2004-04-02 Snecma Moteurs Agencement d'accrochage de secteurs en arc de cercle de distributeur porteur d'aubes
US6769865B2 (en) * 2002-03-22 2004-08-03 General Electric Company Band cooled turbine nozzle
US7033135B2 (en) * 2003-11-10 2006-04-25 General Electric Company Method and apparatus for distributing fluid into a turbomachine
FR2865002B1 (fr) * 2004-01-12 2006-05-05 Snecma Moteurs Turboreacteur a double flux comprenant un support de distribution de servitudes et le support de distribution de servitudes.
US7334983B2 (en) * 2005-10-27 2008-02-26 United Technologies Corporation Integrated bladed fluid seal
US7635251B2 (en) * 2006-06-10 2009-12-22 United Technologies Corporation Stator assembly for a rotary machine
US7837437B2 (en) * 2007-03-07 2010-11-23 General Electric Company Turbine nozzle segment and repair method

Also Published As

Publication number Publication date
CA2715454C (fr) 2016-09-06
WO2009125078A2 (fr) 2009-10-15
EP2252772B1 (fr) 2013-08-07
JP5759363B2 (ja) 2015-08-05
FR2928961B1 (fr) 2015-11-13
WO2009125078A3 (fr) 2009-11-26
CN101970804A (zh) 2011-02-09
BRPI0908165B1 (pt) 2019-12-03
EP2252772A2 (fr) 2010-11-24
JP2011515610A (ja) 2011-05-19
CA2715454A1 (fr) 2009-10-15
BRPI0908165A8 (pt) 2019-01-29
RU2010142483A (ru) 2012-04-27
RU2494264C2 (ru) 2013-09-27
US8602726B2 (en) 2013-12-10
US20110052380A1 (en) 2011-03-03
CN101970804B (zh) 2014-01-29
FR2928961A1 (fr) 2009-09-25

Similar Documents

Publication Publication Date Title
BRPI0908165A2 (pt) distribuidor satorizado para uma turbomáquina, turbina baixa-pressão de turbomáquina e turbomáquina tal como um turborreator ou um turbopropulsor de avião
BRPI0911341A2 (pt) rotor de compressor de uma turbomáquina e turbomáquina, tal como um turborreator ou um turbopropulsor de avião.
BRPI0911686A2 (pt) rotor de compressor de uma turbomáquina e turbomáquina, tal como um turborreator ou um turbopropulsor de avião
EP2142761A4 (en) GAS TURBINE ENGINE COMPONENT, TURBO-ENGINE ENGINE PROVIDED THEREWITH, AND AIRCRAFT PROVIDED THEREWITH
EP2270337A4 (en) BLADE OF A GAS TURBINE ENGINE FOR AN AIRCRAFT, AND METHOD OF MANUFACTURING THE SAME
EP2664767A4 (en) Fuel nozzle, gas turbine combustor equipped with same, and gas turbine equipped with this gas turbine combustor
EP2693122A4 (en) BURNER FOR A GAS TURBINE AND GAS TURBINE
BR112012010257A2 (pt) estágio de turbina para turbomáquina, e, turbomáquina, tal como um turborreator ou um turbopropulsor de avião
EP3027853A4 (en) Gas turbine engine cmc airfoil assembly
BRPI0924210A2 (pt) câmara anular de combustão de uma turbomáquina e turbomáquina tal como um turborreator ou um turbopropulsor de avião
SG11201403015WA (en) Geared turbofan gas turbine engine architecture
SG11201402667QA (en) Geared turbofan gas turbine engine architecture
SG11201403012PA (en) Geared turbofan gas turbine engine architecture
EP2809922A4 (en) ARCHITECTURE OF A DOUBLE FLOW AND GEAR TURBO ARRAY GAS TURBINE ENGINE
BRPI0820423A2 (pt) Dispositivo e processo de monitoramento de uma bomba de alta pressão em um curcuito de alimentação com combustível de uma turbomáquina e turbomáquina, tal como um turborreator ou um turbopropulsor de avião
EP2356327A4 (en) ADAPTIVE INTEGRATED SECURITY SYSTEM FOR GAS TURBINES CONTROLLED BY AUTOMATIC REGULATION WITH FULL REDUNDANT AUTHORITY
SG11201402824RA (en) Geared turbofan gas turbine engine architecture
SG11201403011RA (en) Geared turbofan gas turbine engine architecture
BRPI1008048A2 (pt) processo e sistema de regulagem de uma turbina a gás, turbina a gás e turborreator de avião
BRPI1013581A2 (pt) hélice não carenada com pás com ajuste variável para uma turbomáquina, e, turbomáquina
EP2855878A4 (en) ADMINISTRATION OF THE AREA OF A COMPRESSOR SHAFT TIP FOR A GAS TURBINE ENGINE
GB2473651B (en) Gas turbine aircraft engines and operation thereof
BRPI0921975A2 (pt) reversor de empuxo para nacela de motor turbofan, nacela de motor turbofan e aeronave.
BR112014028731A2 (pt) reversor de empuxo para uma nacela de motor turbojato e nacela de motor turbojato.
EP2900983A4 (en) GAS TURBINE ENGINE COMBUSTION CHAMBER HAVING INTEGRATED COMBUSTION CHAMBER BLADE

Legal Events

Date Code Title Description
B06F Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]
B06T Formal requirements before examination [chapter 6.20 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: 10 (DEZ) ANOS CONTADOS A PARTIR DE 03/12/2019, OBSERVADAS AS CONDICOES LEGAIS. (CO) 10 (DEZ) ANOS CONTADOS A PARTIR DE 03/12/2019, OBSERVADAS AS CONDICOES LEGAIS