BR0005767A - Estrutura para uma palheta de estator de motor a jato ou turbina a gás - Google Patents

Estrutura para uma palheta de estator de motor a jato ou turbina a gás

Info

Publication number
BR0005767A
BR0005767A BR0005767-3A BR0005767A BR0005767A BR 0005767 A BR0005767 A BR 0005767A BR 0005767 A BR0005767 A BR 0005767A BR 0005767 A BR0005767 A BR 0005767A
Authority
BR
Brazil
Prior art keywords
vanes
stator
vane
structural ring
gas turbine
Prior art date
Application number
BR0005767-3A
Other languages
English (en)
Other versions
BR0005767B1 (pt
Inventor
John Alan Manteiga
Jeffrey Howard Nussbaum
John Lawrence Noon
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 BR0005767A publication Critical patent/BR0005767A/pt
Publication of BR0005767B1 publication Critical patent/BR0005767B1/pt

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00Stators
    • F01D9/02Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005Sealing means between non relatively rotating elements

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)

Abstract

Patente de Invenção:<B>"ESTRUTURA PARA UMA PALHETA DE ESTATOR DE MOTOR A JATO OU TURBINA A GáS"<D>. Um conjunto de estrutura para palhetas de estator incluindo um anel estrutural externo (34), um anel estrutural interno (36), um conjunto de palhetas individuais (22) cada uma conectando o anel estrutural externo(34) e o anel estrutural interno (36), formando plataformas interna e externa com as palhetas (22) vizinhas definindo um conjunto de trajetórias de fluxo, um conjunto de membros de vedação (30, 32, 58, 70) conformado a um conjunto de folgas (60) entre o conjunto de palhetas (22) disposto para vedar a folga (60). Um método para a aplicação de um membro de vedação (30, 32,58, 70) contra as folgas (60) entre uma plataforma formada como resultado do acoplamento entre as palhetas (22) incluindo a fixação de um conjunto de palhetas de estator (22) em uma estrutura interna e a uma estrutura externa, e a vedação de um conjunto de membros de fixação (30, 32, 58, 70) sobre a superfície da parte traseira de uma estrutura de palheta de estator. A natureza discreta de uma palheta individual vedada pelos membros de vedação (30, 32, 58, 70) faz com que o conjunto de estrutura para palhetas de estator a adicione um efeito de amortecimento o qual aumenta a vida sem fadiga da palheta (22), e permite o emprego de material com menor resistência, mais leve e mais barato.
BRPI0005767-3A 1999-12-07 2000-12-07 conjunto de estrutura para palhetas de estator. BR0005767B1 (pt)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US09/456,967 US6343912B1 (en) 1999-12-07 1999-12-07 Gas turbine or jet engine stator vane frame

Publications (2)

Publication Number Publication Date
BR0005767A true BR0005767A (pt) 2001-07-17
BR0005767B1 BR0005767B1 (pt) 2008-11-18

Family

ID=23814880

Family Applications (1)

Application Number Title Priority Date Filing Date
BRPI0005767-3A BR0005767B1 (pt) 1999-12-07 2000-12-07 conjunto de estrutura para palhetas de estator.

Country Status (6)

Country Link
US (1) US6343912B1 (pt)
EP (1) EP1106784B1 (pt)
JP (1) JP4737820B2 (pt)
BR (1) BR0005767B1 (pt)
CA (1) CA2326425C (pt)
DE (1) DE60028507T2 (pt)

Families Citing this family (71)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6984108B2 (en) * 2002-02-22 2006-01-10 Drs Power Technology Inc. Compressor stator vane
US7651319B2 (en) * 2002-02-22 2010-01-26 Drs Power Technology Inc. Compressor stator vane
US6733237B2 (en) * 2002-04-02 2004-05-11 Watson Cogeneration Company Method and apparatus for mounting stator blades in axial flow compressors
US6969239B2 (en) 2002-09-30 2005-11-29 General Electric Company Apparatus and method for damping vibrations between a compressor stator vane and a casing of a gas turbine engine
US20050172485A1 (en) * 2004-02-10 2005-08-11 Ramsay Mussen Method of repair for cast article
US20050220622A1 (en) * 2004-03-31 2005-10-06 General Electric Company Integral covered nozzle with attached overcover
FR2902843A1 (fr) * 2006-06-23 2007-12-28 Snecma Sa Secteur de redresseur de compresseur ou secteur de distributeur de turbomachine
US7748956B2 (en) * 2006-12-19 2010-07-06 United Technologies Corporation Non-stablug stator apparatus and assembly method
US20090110552A1 (en) * 2007-10-31 2009-04-30 Anderson Rodger O Compressor stator vane repair with pin
EP2075412B1 (fr) * 2007-12-26 2012-02-29 Techspace Aero Dispositif de fixation par boulonnage d'aubes à une virole d'étage de stator d'une turbomachine et procédé associé de fixation par boulonnage
US8511983B2 (en) 2008-02-19 2013-08-20 United Technologies Corporation LPC exit guide vane and assembly
EP2199544B1 (fr) * 2008-12-22 2016-03-30 Techspace Aero S.A. Architecture de redresseur
US8162603B2 (en) * 2009-01-30 2012-04-24 General Electric Company Vane frame for a turbomachine and method of minimizing weight thereof
US8371810B2 (en) * 2009-03-26 2013-02-12 General Electric Company Duct member based nozzle for turbine
EP2339120B1 (fr) * 2009-12-22 2015-07-08 Techspace Aero S.A. Étage redresseur de turbomachine et compresseur associé
US8356975B2 (en) * 2010-03-23 2013-01-22 United Technologies Corporation Gas turbine engine with non-axisymmetric surface contoured vane platform
US9976433B2 (en) 2010-04-02 2018-05-22 United Technologies Corporation Gas turbine engine with non-axisymmetric surface contoured rotor blade platform
FR2961553B1 (fr) * 2010-06-18 2012-08-31 Snecma Secteur angulaire de redresseur pour compresseur de turbomachine, redresseur de turbomachine et turbomachine comprenant un tel secteur
US8966755B2 (en) 2011-01-20 2015-03-03 United Technologies Corporation Assembly fixture for a stator vane assembly
US8966756B2 (en) * 2011-01-20 2015-03-03 United Technologies Corporation Gas turbine engine stator vane assembly
US8951013B2 (en) 2011-10-24 2015-02-10 United Technologies Corporation Turbine blade rail damper
CN103917761B (zh) * 2011-12-29 2017-06-30 艾利奥特公司 一种燃气涡轮机装置及其进气壳组件的装配方法
WO2013180916A1 (en) * 2012-05-30 2013-12-05 United Technologies Corporation Assembly fixture for a stator vane assembly
US11035238B2 (en) 2012-06-19 2021-06-15 Raytheon Technologies Corporation Airfoil including adhesively bonded shroud
US10309235B2 (en) * 2012-08-27 2019-06-04 United Technologies Corporation Shiplap cantilevered stator
US9366149B2 (en) * 2012-09-21 2016-06-14 United Technologies Corporation Multi-stage high pressure compressor case
US20140169979A1 (en) * 2012-12-14 2014-06-19 United Technologies Corporation Gas turbine engine fan blade platform seal
WO2014137444A2 (en) 2012-12-29 2014-09-12 United Technologies Corporation Multi-ply finger seal
US9541006B2 (en) 2012-12-29 2017-01-10 United Technologies Corporation Inter-module flow discourager
US10294819B2 (en) 2012-12-29 2019-05-21 United Technologies Corporation Multi-piece heat shield
US10094389B2 (en) 2012-12-29 2018-10-09 United Technologies Corporation Flow diverter to redirect secondary flow
US9562478B2 (en) 2012-12-29 2017-02-07 United Technologies Corporation Inter-module finger seal
US9206742B2 (en) 2012-12-29 2015-12-08 United Technologies Corporation Passages to facilitate a secondary flow between components
EP2938868B1 (en) 2012-12-29 2019-08-07 United Technologies Corporation Flow diverter assembly
US10472987B2 (en) 2012-12-29 2019-11-12 United Technologies Corporation Heat shield for a casing
US9850780B2 (en) 2012-12-29 2017-12-26 United Technologies Corporation Plate for directing flow and film cooling of components
GB2524211B (en) 2012-12-29 2021-05-26 United Technologies Corp Turbine frame assembly and method of designing turbine frame assembly
WO2014105577A1 (en) 2012-12-29 2014-07-03 United Technologies Corporation Scupper channelling in gas turbine modules
EP2938857B2 (en) 2012-12-29 2020-11-25 United Technologies Corporation Heat shield for cooling a strut
US10060279B2 (en) 2012-12-29 2018-08-28 United Technologies Corporation Seal support disk and assembly
US10378370B2 (en) 2012-12-29 2019-08-13 United Technologies Corporation Mechanical linkage for segmented heat shield
WO2014105657A1 (en) 2012-12-29 2014-07-03 United Technologies Corporation Mount with deflectable tabs
US9631517B2 (en) 2012-12-29 2017-04-25 United Technologies Corporation Multi-piece fairing for monolithic turbine exhaust case
WO2014105800A1 (en) 2012-12-29 2014-07-03 United Technologies Corporation Gas turbine seal assembly and seal support
US9771818B2 (en) 2012-12-29 2017-09-26 United Technologies Corporation Seals for a circumferential stop ring in a turbine exhaust case
WO2014105604A1 (en) 2012-12-29 2014-07-03 United Technologies Corporation Angled cut to direct radiative heat load
US10329956B2 (en) 2012-12-29 2019-06-25 United Technologies Corporation Multi-function boss for a turbine exhaust case
US9297312B2 (en) 2012-12-29 2016-03-29 United Technologies Corporation Circumferentially retained fairing
EP2938845A4 (en) 2012-12-29 2016-01-13 United Technologies Corp TURBINE EXHAUST HOUSING ARCHITECTURE
WO2014105803A1 (en) 2012-12-29 2014-07-03 United Technologies Corporation Gas turbine seal assembly and seal support
US9347330B2 (en) 2012-12-29 2016-05-24 United Technologies Corporation Finger seal
US10053998B2 (en) 2012-12-29 2018-08-21 United Technologies Corporation Multi-purpose gas turbine seal support and assembly
US9863261B2 (en) 2012-12-29 2018-01-09 United Technologies Corporation Component retention with probe
WO2014143329A2 (en) 2012-12-29 2014-09-18 United Technologies Corporation Frame junction cooling holes
US9828867B2 (en) 2012-12-29 2017-11-28 United Technologies Corporation Bumper for seals in a turbine exhaust case
WO2014105688A1 (en) 2012-12-31 2014-07-03 United Technologies Corporation Turbine exhaust case multi-piece frame
US10054009B2 (en) 2012-12-31 2018-08-21 United Technologies Corporation Turbine exhaust case multi-piece frame
GB2524220B (en) 2012-12-31 2020-05-20 United Technologies Corp Turbine exhaust case multi-piece frame
US10330011B2 (en) 2013-03-11 2019-06-25 United Technologies Corporation Bench aft sub-assembly for turbine exhaust case fairing
US10087766B2 (en) 2013-03-13 2018-10-02 United Technologies Corporation Structural guide vane outer diameter K gussets
FR3008639B1 (fr) * 2013-07-18 2015-08-07 Snecma Procede d'assemblage de pieces de turbomachine et ensemble mis en œuvre lors d'un tel procede
US10344603B2 (en) * 2013-07-30 2019-07-09 United Technologies Corporation Gas turbine engine turbine vane ring arrangement
US9816387B2 (en) 2014-09-09 2017-11-14 United Technologies Corporation Attachment faces for clamped turbine stator of a gas turbine engine
US9810075B2 (en) 2015-03-20 2017-11-07 United Technologies Corporation Faceted turbine blade damper-seal
US9777594B2 (en) 2015-04-15 2017-10-03 Siemens Energy, Inc. Energy damping system for gas turbine engine stationary vane
US10301951B2 (en) 2016-05-20 2019-05-28 United Technologies Corporation Turbine vane gusset
FR3051840B1 (fr) * 2016-05-31 2020-01-10 Safran Aircraft Engines Carter intermediaire de turbomachine, equipee d'une piece d'etancheite a interface bras/virole
US10364748B2 (en) 2016-08-19 2019-07-30 United Technologies Corporation Finger seal flow metering
US20220290573A1 (en) * 2021-03-09 2022-09-15 Raytheon Technologies Corporation Chevron grooved mateface seal
US11674404B2 (en) 2021-05-04 2023-06-13 Raytheon Technologies Corporation Seal assembly with seal arc segment
CN114458628B (zh) * 2022-04-12 2022-06-24 广东威灵电机制造有限公司 风机及电器设备

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3752598A (en) * 1971-11-17 1973-08-14 United Aircraft Corp Segmented duct seal
US3892497A (en) * 1974-05-14 1975-07-01 Westinghouse Electric Corp Axial flow turbine stationary blade and blade ring locking arrangement
GB1483532A (en) * 1974-09-13 1977-08-24 Rolls Royce Stator structure for a gas turbine engine
US4422827A (en) * 1982-02-18 1983-12-27 United Technologies Corporation Blade root seal
US4492517A (en) * 1983-01-06 1985-01-08 General Electric Company Segmented inlet nozzle for gas turbine, and methods of installation
JPS60118306A (ja) * 1983-11-29 1985-06-25 Ishikawajima Harima Heavy Ind Co Ltd 圧延機
US4524980A (en) * 1983-12-05 1985-06-25 United Technologies Corporation Intersecting feather seals for interlocking gas turbine vanes
JPS60118306U (ja) * 1984-01-20 1985-08-10 株式会社日立製作所 流体機械における静翼部のシ−ル装置
US4655682A (en) * 1985-09-30 1987-04-07 United Technologies Corporation Compressor stator assembly having a composite inner diameter shroud
US4749333A (en) * 1986-05-12 1988-06-07 The United States Of America As Represented By The Secretary Of The Air Force Vane platform sealing and retention means
CA2031085A1 (en) * 1990-01-16 1991-07-17 Michael P. Hagle Arrangement for sealing gaps between adjacent circumferential segments of turbine nozzles and shrouds
US5074748A (en) * 1990-07-30 1991-12-24 General Electric Company Seal assembly for segmented turbine engine structures
US5154577A (en) * 1991-01-17 1992-10-13 General Electric Company Flexible three-piece seal assembly
CA2070511C (en) * 1991-07-22 2001-08-21 Steven Milo Toborg Turbine nozzle support
US5380155A (en) * 1994-03-01 1995-01-10 United Technologies Corporation Compressor stator assembly
US5411370A (en) * 1994-08-01 1995-05-02 United Technologies Corporation Vibration damping shroud for a turbomachine vane
US5820338A (en) * 1997-04-24 1998-10-13 United Technologies Corporation Fan blade interplatform seal
US5848874A (en) * 1997-05-13 1998-12-15 United Technologies Corporation Gas turbine stator vane assembly
DE69824925T2 (de) * 1997-09-17 2005-08-25 Mitsubishi Heavy Industries, Ltd. Leitschaufelpaar

Also Published As

Publication number Publication date
CA2326425C (en) 2007-06-12
CA2326425A1 (en) 2001-06-07
BR0005767B1 (pt) 2008-11-18
DE60028507T2 (de) 2007-06-06
JP4737820B2 (ja) 2011-08-03
EP1106784A2 (en) 2001-06-13
DE60028507D1 (de) 2006-07-20
EP1106784B1 (en) 2006-06-07
US6343912B1 (en) 2002-02-05
EP1106784A3 (en) 2003-07-16
JP2001207998A (ja) 2001-08-03

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Legal Events

Date Code Title Description
B06A Patent application procedure suspended [chapter 6.1 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 07/12/2000, OBSERVADAS AS CONDICOES LEGAIS.

B21F Lapse acc. art. 78, item iv - on non-payment of the annual fees in time
B24J Lapse because of non-payment of annual fees (definitively: art 78 iv lpi, resolution 113/2013 art. 12)