BR112014016602A8 - motor de turbina a gás com arquitetura de engrenagens - Google Patents

motor de turbina a gás com arquitetura de engrenagens

Info

Publication number
BR112014016602A8
BR112014016602A8 BR112014016602A BR112014016602A BR112014016602A8 BR 112014016602 A8 BR112014016602 A8 BR 112014016602A8 BR 112014016602 A BR112014016602 A BR 112014016602A BR 112014016602 A BR112014016602 A BR 112014016602A BR 112014016602 A8 BR112014016602 A8 BR 112014016602A8
Authority
BR
Brazil
Prior art keywords
fan
nacelle
central
gas turbine
turbine engine
Prior art date
Application number
BR112014016602A
Other languages
English (en)
Other versions
BR112014016602A2 (pt
BR112014016602B1 (pt
Inventor
M Schwarz Frederick
G Smith Peter
S Ochs Stuart
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
Priority claimed from US13/346,100 external-priority patent/US20120222398A1/en
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of BR112014016602A2 publication Critical patent/BR112014016602A2/pt
Publication of BR112014016602A8 publication Critical patent/BR112014016602A8/pt
Publication of BR112014016602B1 publication Critical patent/BR112014016602B1/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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • 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
    • F02K3/06—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 front fan
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)

Abstract

1 / 1 resumo “motor de turbina a gãs” um motor de turbina a gã¡s de acordo com um aspecto exemplificativo da presente invenã§ã£o inclui uma nacele central definida ao redor de um eixo geomã©trico central de motor, uma nacele de ventoinha montada, pelo menos parcialmente, ao redor da nacele central para definir um trajeto de fluxo de desvio de ventoinha para um fluxo de ar desviado de vertical, um bocal de ã¡rea variã¡vel de ventoinha mã³vel axialmente em relaã§ã£o ã  nacele de ventoinha para variar a ã¡rea de saã­da de bocal de ventoinha e ajustar uma razã£o de pressã£o do fluxo de ar desviado de ventoinha durante operaã§ã£o do motor, e um sistema de engrenagens acionado por um motor central dentro da nacele central para acionar uma ventoinha dentro da nacele de ventoinha, o sistema de engrenagens definindo uma relaã§ã£o de reduã§ã£o de engrenagens maior ou igual e cerca de 2,3.
BR112014016602-1A 2012-01-09 2013-01-03 Motor de turbina a gás BR112014016602B1 (pt)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US13/346,100 US20120222398A1 (en) 2007-07-27 2012-01-09 Gas turbine engine with geared architecture
US13/346,100 2012-01-09
PCT/US2013/020040 WO2013106223A1 (en) 2012-01-09 2013-01-03 Gas turbine engine with geared architecture

Publications (3)

Publication Number Publication Date
BR112014016602A2 BR112014016602A2 (pt) 2017-06-13
BR112014016602A8 true BR112014016602A8 (pt) 2017-07-04
BR112014016602B1 BR112014016602B1 (pt) 2022-03-29

Family

ID=48781820

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112014016602-1A BR112014016602B1 (pt) 2012-01-09 2013-01-03 Motor de turbina a gás

Country Status (8)

Country Link
EP (1) EP2802745A4 (pt)
JP (2) JP2015503705A (pt)
CN (1) CN104040117A (pt)
BR (1) BR112014016602B1 (pt)
CA (1) CA2853694C (pt)
RU (1) RU2647558C2 (pt)
SG (1) SG11201402663XA (pt)
WO (1) WO2013106223A1 (pt)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2862597C (en) * 2013-10-03 2018-12-11 Karl L. Hasel Geared gas turbine engine architecture for enhanced efficiency
EP3048266A1 (en) * 2015-01-22 2016-07-27 United Technologies Corporation Gas turbine engine with low fan pressure ratio
CN106286010B (zh) * 2015-06-26 2018-10-26 中航空天发动机研究院有限公司 一种反向安装核心机的齿轮传动涡扇发动机
US9821917B2 (en) * 2015-09-21 2017-11-21 General Electric Company Aft engine for an aircraft
US10677264B2 (en) 2016-10-14 2020-06-09 General Electric Company Supersonic single-stage turbofan engine
US11421627B2 (en) * 2017-02-22 2022-08-23 General Electric Company Aircraft and direct drive engine under wing installation
GB201719539D0 (en) * 2017-11-24 2018-01-10 Rolls Royce Plc Gas Turbine Engine
GB201811281D0 (en) * 2018-07-10 2018-08-29 Rolls Royce Plc A geared turbofan bas turbine engine mounting arrangement
GB201812553D0 (en) * 2018-08-01 2018-09-12 Rolls Royce Plc Gas turbine engine
GB201820930D0 (en) * 2018-12-21 2019-02-06 Rolls Royce Plc Turbine engine
GB201906168D0 (en) * 2019-05-02 2019-06-19 Rolls Royce Plc Gas turbine engine with fan outlet guide vanes
IT202000000652A1 (it) 2020-01-15 2021-07-15 Ge Avio Srl Turbomacchina e gruppo ingranaggi

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US3747343A (en) * 1972-02-10 1973-07-24 United Aircraft Corp Low noise prop-fan
US5259187A (en) * 1993-02-05 1993-11-09 General Electric Company Method of operating an aircraft bypass turbofan engine having variable fan outlet guide vanes
JPH09317557A (ja) * 1996-05-30 1997-12-09 Ishikawajima Harima Heavy Ind Co Ltd ターボファンエンジン
US5794432A (en) * 1996-08-27 1998-08-18 Diversitech, Inc. Variable pressure and variable air flow turbofan engines
US6732502B2 (en) * 2002-03-01 2004-05-11 General Electric Company Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor
US6775990B2 (en) * 2002-10-17 2004-08-17 Mark Douglas Swinford Methods and apparatus for regulating gas turbine engine fluid flow
FR2866387B1 (fr) * 2004-02-12 2008-03-14 Snecma Moteurs Adaptation aerodynamique de la soufflante arriere d'un turboreacteur double soufflante
RU2315887C2 (ru) * 2005-12-23 2008-01-27 Открытое акционерное общество "Авиадвигатель" Турбореактивный двигатель сверхвысокой степени двухконтурности
US20100303608A1 (en) * 2006-09-28 2010-12-02 Mitsubishi Heavy Industries, Ltd. Two-shaft gas turbine
EP2074312B1 (en) * 2006-10-12 2017-12-13 United Technologies Corporation Fan variable area nozzle for a gas turbine engine fan nacelle with sliding actuation system
EP2426342B1 (en) * 2006-10-12 2018-02-28 United Technologies Corporation Turbofan engine with variable bypass nozzle exit area and method of operation
EP2064434B1 (en) * 2006-10-12 2012-06-27 United Technologies Corporation Operational line management of low pressure compressor in a turbofan engine
EP2069629B1 (en) * 2006-10-12 2014-09-24 United Technologies Corporation Gas turbine engine fan variable area nozzle with swivalable insert system
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
US8127529B2 (en) * 2007-03-29 2012-03-06 United Technologies Corporation Variable area fan nozzle and thrust reverser
US20080310956A1 (en) * 2007-06-13 2008-12-18 Jain Ashok K Variable geometry gas turbine engine nacelle assembly with nanoelectromechanical system
US8347633B2 (en) * 2007-07-27 2013-01-08 United Technologies Corporation Gas turbine engine with variable geometry fan exit guide vane system
US8074440B2 (en) * 2007-08-23 2011-12-13 United Technologies Corporation Gas turbine engine with axial movable fan variable area nozzle
US20110120079A1 (en) * 2009-11-24 2011-05-26 Schwark Jr Fred W Variable area fan nozzle stiffeners and placement

Also Published As

Publication number Publication date
JP2015503705A (ja) 2015-02-02
CA2853694A1 (en) 2013-07-18
EP2802745A4 (en) 2015-10-21
WO2013106223A1 (en) 2013-07-18
RU2647558C2 (ru) 2018-03-19
BR112014016602A2 (pt) 2017-06-13
CA2853694C (en) 2016-03-22
CN104040117A (zh) 2014-09-10
BR112014016602B1 (pt) 2022-03-29
EP2802745A1 (en) 2014-11-19
JP2017015095A (ja) 2017-01-19
SG11201402663XA (en) 2014-09-26
RU2014130443A (ru) 2016-02-27

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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]
B350 Update of information on the portal [chapter 15.35 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 03/01/2013, OBSERVADAS AS CONDICOES LEGAIS.