BR112015010811A2 - seção de turbina de um motor de turbina de gás, e, motor de turbina de gás - Google Patents

seção de turbina de um motor de turbina de gás, e, motor de turbina de gás

Info

Publication number
BR112015010811A2
BR112015010811A2 BR112015010811A BR112015010811A BR112015010811A2 BR 112015010811 A2 BR112015010811 A2 BR 112015010811A2 BR 112015010811 A BR112015010811 A BR 112015010811A BR 112015010811 A BR112015010811 A BR 112015010811A BR 112015010811 A2 BR112015010811 A2 BR 112015010811A2
Authority
BR
Brazil
Prior art keywords
turbine
gas turbine
turbine engine
pressure turbine
low pressure
Prior art date
Application number
BR112015010811A
Other languages
English (en)
Other versions
BR112015010811B1 (pt
Inventor
M Schwarz Frederick
A Glahn Jorn
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Publication of BR112015010811A2 publication Critical patent/BR112015010811A2/pt
Publication of BR112015010811B1 publication Critical patent/BR112015010811B1/pt

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/06—Arrangements of bearings; Lubricating
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/072—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with counter-rotating, e.g. fan rotors

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Retarders (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1 / 1 resumo “seã‡ãƒo de turbina de um motor de turbina de gãs, e, motor de turbina de gãs” um motor de turbina de gã¡s inclui uma turbina de baixa pressã£o de velocidade muito alta tal que uma quantidade definida pela ã¡rea de saã­da da turbina de baixa pressã£o multiplicada pelo quadrado da velocidade rotativa da turbina de baixa pressã£o comparada com os mesmos parã¢metros para uma turbina de pressã£o mais alta estã¡ em uma razã£o entre cerca de 0,5 e cerca de 1,5. alã©m disso, a turbina de pressã£o mais baixa ã© montada com um primeiro mancal montado em uma armaã§ã£o de turbina mã©dia, e um segundo mancal montado dentro de uma caixa de exaustã£o da turbina.
BR112015010811-3A 2012-11-14 2013-11-07 Seção de turbina de um motor de turbina de gás, e, motor de turbina de gás BR112015010811B1 (pt)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
US201261726211P 2012-11-14 2012-11-14
US61/726,211 2012-11-14
US13/719,620 2012-12-19
US13/719,620 US20140130479A1 (en) 2012-11-14 2012-12-19 Gas Turbine Engine With Mount for Low Pressure Turbine Section
PCT/US2013/068838 WO2014078157A1 (en) 2012-11-14 2013-11-07 Gas turbine engine with mount for low pressure turbine section

Publications (2)

Publication Number Publication Date
BR112015010811A2 true BR112015010811A2 (pt) 2017-07-11
BR112015010811B1 BR112015010811B1 (pt) 2021-08-31

Family

ID=50680353

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112015010811-3A BR112015010811B1 (pt) 2012-11-14 2013-11-07 Seção de turbina de um motor de turbina de gás, e, motor de turbina de gás

Country Status (6)

Country Link
US (1) US20140130479A1 (pt)
EP (2) EP3594483A1 (pt)
JP (3) JP2015536409A (pt)
BR (1) BR112015010811B1 (pt)
CA (1) CA2889618C (pt)
WO (1) WO2014078157A1 (pt)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10240526B2 (en) 2012-01-31 2019-03-26 United Technologies Corporation Gas turbine engine with high speed low pressure turbine section
US20150345426A1 (en) 2012-01-31 2015-12-03 United Technologies Corporation Geared turbofan gas turbine engine architecture
US9222417B2 (en) * 2012-01-31 2015-12-29 United Technologies Corporation Geared turbofan gas turbine engine architecture
US9845726B2 (en) 2012-01-31 2017-12-19 United Technologies Corporation Gas turbine engine with high speed low pressure turbine section
US10287914B2 (en) 2012-01-31 2019-05-14 United Technologies Corporation Gas turbine engine with high speed low pressure turbine section and bearing support features
US9816442B2 (en) 2012-01-31 2017-11-14 United Technologies Corporation Gas turbine engine with high speed low pressure turbine section
US10309232B2 (en) * 2012-02-29 2019-06-04 United Technologies Corporation Gas turbine engine with stage dependent material selection for blades and disk
US10125693B2 (en) 2012-04-02 2018-11-13 United Technologies Corporation Geared turbofan engine with power density range
US9897001B2 (en) * 2014-03-04 2018-02-20 United Technologies Corporation Compressor areas for high overall pressure ratio gas turbine engine
EP3012410B1 (en) 2014-09-29 2023-05-10 Raytheon Technologies Corporation Advanced gamma tial components
EP3032084A1 (en) * 2014-12-12 2016-06-15 United Technologies Corporation Gas turbine engine with high speed low pressure turbine section
EP3034849A1 (en) * 2014-12-17 2016-06-22 United Technologies Corporation Gas turbine engine with high speed low pressure turbine section
EP3165754A1 (en) * 2015-11-03 2017-05-10 United Technologies Corporation Gas turbine engine with high speed low pressure turbine section and bearing support features
CA2945264A1 (en) * 2015-11-05 2017-05-05 United Technologies Corporation Gas turbine engine with mount for low pressure turbine section
GB201704502D0 (en) * 2017-03-22 2017-05-03 Rolls Royce Plc Gas turbine engine

Family Cites Families (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS57171032A (en) * 1981-04-10 1982-10-21 Teledyne Ind Gas turbine engine
US4790133A (en) * 1986-08-29 1988-12-13 General Electric Company High bypass ratio counterrotating turbofan engine
US4916894A (en) * 1989-01-03 1990-04-17 General Electric Company High bypass turbofan engine having a partially geared fan drive turbine
US5010729A (en) * 1989-01-03 1991-04-30 General Electric Company Geared counterrotating turbine/fan propulsion system
US5361580A (en) * 1993-06-18 1994-11-08 General Electric Company Gas turbine engine rotor support system
US5520512A (en) * 1995-03-31 1996-05-28 General Electric Co. Gas turbines having different frequency applications with hardware commonality
US5623823A (en) * 1995-12-06 1997-04-29 United Technologies Corporation Variable cycle engine with enhanced stability
US6619030B1 (en) * 2002-03-01 2003-09-16 General Electric Company Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors
US6666017B2 (en) * 2002-05-24 2003-12-23 General Electric Company Counterrotatable booster compressor assembly for a gas turbine engine
GB0406174D0 (en) * 2004-03-19 2004-04-21 Rolls Royce Plc Turbine engine arrangement
US7097413B2 (en) * 2004-05-12 2006-08-29 United Technologies Corporation Bearing support
SE527711C2 (sv) * 2004-10-06 2006-05-16 Volvo Aero Corp Lagerstativstruktur och gasturbinmotor som innefattar lagerstativstrukturen
US7374403B2 (en) * 2005-04-07 2008-05-20 General Electric Company Low solidity turbofan
US7393182B2 (en) * 2005-05-05 2008-07-01 Florida Turbine Technologies, Inc. Composite tip shroud ring
US7513102B2 (en) * 2005-06-06 2009-04-07 General Electric Company Integrated counterrotating turbofan
US7628579B2 (en) * 2005-07-20 2009-12-08 United Technologies Corporation Gear train variable vane synchronizing mechanism for inner diameter vane shroud
US7665959B2 (en) * 2005-07-20 2010-02-23 United Technologies Corporation Rack and pinion variable vane synchronizing mechanism for inner diameter vane shroud
US7775049B2 (en) * 2006-04-04 2010-08-17 United Technologies Corporation Integrated strut design for mid-turbine frames with U-base
US8016561B2 (en) * 2006-07-11 2011-09-13 General Electric Company Gas turbine engine fan assembly and method for assembling to same
US7694505B2 (en) * 2006-07-31 2010-04-13 General Electric Company Gas turbine engine assembly and method of assembling same
US20120213628A1 (en) * 2006-08-15 2012-08-23 Mccune Michael E Gas turbine engine with geared architecture
US8939864B2 (en) * 2006-08-15 2015-01-27 United Technologies Corporation Gas turbine engine lubrication
US7721549B2 (en) * 2007-02-08 2010-05-25 United Technologies Corporation Fan variable area nozzle for a gas turbine engine fan nacelle with cam drive ring actuation system
US7950237B2 (en) * 2007-06-25 2011-05-31 United Technologies Corporation Managing spool bearing load using variable area flow nozzle
US8347633B2 (en) * 2007-07-27 2013-01-08 United Technologies Corporation Gas turbine engine with variable geometry fan exit guide vane system
US8277174B2 (en) * 2007-09-21 2012-10-02 United Technologies Corporation Gas turbine engine compressor arrangement
US8337147B2 (en) * 2007-09-21 2012-12-25 United Technologies Corporation Gas turbine engine compressor arrangement
US20090092494A1 (en) * 2007-10-04 2009-04-09 General Electric Company Disk rotor and method of manufacture
US8511986B2 (en) * 2007-12-10 2013-08-20 United Technologies Corporation Bearing mounting system in a low pressure turbine
WO2010089880A1 (ja) * 2009-02-06 2010-08-12 トヨタ自動車株式会社 ターボファンエンジン
FR2944558B1 (fr) * 2009-04-17 2014-05-02 Snecma Moteur a turbine a gaz double corps pourvu d'un palier de turbine bp supplementaire.
US8176725B2 (en) * 2009-09-09 2012-05-15 United Technologies Corporation Reversed-flow core for a turbofan with a fan drive gear system
US8517672B2 (en) * 2010-02-23 2013-08-27 General Electric Company Epicyclic gearbox
US8904753B2 (en) * 2011-04-28 2014-12-09 United Technologies Corporation Thermal management system for gas turbine engine
US8291690B1 (en) * 2012-01-31 2012-10-23 United Technologies Corporation Gas turbine engine with variable area fan nozzle positioned for starting

Also Published As

Publication number Publication date
JP6336648B2 (ja) 2018-06-06
US20140130479A1 (en) 2014-05-15
JP2015536409A (ja) 2015-12-21
EP2920445A1 (en) 2015-09-23
CA2889618C (en) 2018-03-06
EP3594483A1 (en) 2020-01-15
JP2017160911A (ja) 2017-09-14
WO2014078157A1 (en) 2014-05-22
CA2889618A1 (en) 2014-05-22
JP2018135889A (ja) 2018-08-30
BR112015010811B1 (pt) 2021-08-31
EP2920445A4 (en) 2015-12-16

Similar Documents

Publication Publication Date Title
BR112015010811A2 (pt) seção de turbina de um motor de turbina de gás, e, motor de turbina de gás
BR112014007754A2 (pt) sistema de engrenagens de acionamento de ventoinha, e, motor de turbina a gás
BR112014031197A2 (pt) invólucro de escape de turbina, e, motor de turbina a gás
BR112014031498A2 (pt) composição lubrificante, e, uso de uma composição lubrificante
BR112017005466A2 (pt) conjunto de balancim de válvula de escape
BR112014007438A2 (pt) motor de turbina a gás, e, arranjo para um motor de turbina a gás
CL2015002703A1 (es) Motor de combustión interna de pistón opuesto con sellado de capa no viscosa
BR112012016552A2 (pt) sistema de hélice de contra-rotação para um motor de turbina de aeronave
BR112014030742A2 (pt) controle de um freio de liberação de compressão
BR112015009878A2 (pt) aeronave propelida por um turborreator de ventoinhas contrarrotativas
BR112015003696A2 (pt) polissacarídeo de alternan funcionalizado, método para funcionalização de um polissacarídeo de alternan com grupos carbóxi, composição, e, uso de um polissacarídeo de alternan funcionalizado
BR112015017860A2 (pt) método e sistema de geração de microbolhas
BRPI1003517A8 (pt) sistema de lubrificação para motor quatro tempos
BR112013005250A2 (pt) motor de turbina a gás que compreende meios de retenção axial de uma ventoinha do dito motor
BR112015006325A2 (pt) pá de turbina eólica, e, turbina eólica
BR112015026722A2 (pt) embalagem de aditivo para uma composição lubrificante, composição lubrificante, e, método para lubrificar um sistema
EP2809953A4 (en) LOW PRESSURE, HIGH SPEED TURBINE SECTION GAS TURBINE ENGINE AND BEARING SUPPORT ELEMENTS
BR112013023299A2 (pt) turbocarregador; e método de operação de turbocarregador
BR112014000196A2 (pt) sistema de acionamento, especialmente um sistema de acionamento para veículo automotor
BR112014013673A8 (pt) sistema de vedação de uma câmara de óleo de um volume exterior adjacente e motor da turbina provido com tal sistema de vedação
BR112015020829A2 (pt) sistemas de escape de difusor radial para uso com um motor de turbina a gás
BR112015018667A2 (pt) sistema de propulsão
SG11201403614VA (en) Gas turbine engine with high speed low pressure turbine section and bearing support features
EP3070264A4 (en) Vane structure for axial flow turbomachine and gas turbine engine
BR112015000292A2 (pt) método para detectar degradação de uma turbomáquina

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]
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 07/11/2013, OBSERVADAS AS CONDICOES LEGAIS.