BR112015026459A2 - motor de turboventilador de aeronave - Google Patents

motor de turboventilador de aeronave

Info

Publication number
BR112015026459A2
BR112015026459A2 BR112015026459A BR112015026459A BR112015026459A2 BR 112015026459 A2 BR112015026459 A2 BR 112015026459A2 BR 112015026459 A BR112015026459 A BR 112015026459A BR 112015026459 A BR112015026459 A BR 112015026459A BR 112015026459 A2 BR112015026459 A2 BR 112015026459A2
Authority
BR
Brazil
Prior art keywords
nozzle
stream
air
converging
duct
Prior art date
Application number
BR112015026459A
Other languages
English (en)
Inventor
Joseph Petersen Brian
Lynn Dawson David
Lee Lariviere Erin
Jerome Ellehorst Robert
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 BR112015026459A2 publication Critical patent/BR112015026459A2/pt

Links

Classifications

    • 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
    • F02K3/077—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 the plant being of the multiple flow type, i.e. having three or more flows
    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • 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
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
    • 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
    • F02K3/025—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 by-pass flow being at least partly used to create an independent thrust component
    • 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
    • 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
    • F02K3/075—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 controlling flow ratio between flows
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Exhaust Gas After Treatment (AREA)

Abstract

resumo “motor de turboventilador de aeronave” trata-se de um sistema de escape para um motor de aeronave de ciclo variável. o sistema de escape compreende um escapamento de núcleo para ar de desvio e gases quentes de combustão. o escapamento de núcleo inclui um bocal convergente-divergente. o bocal convergente-divergente é formado por uma pluralidade de abas e vedações. o sistema de escape compreende um terceiro duto de ar para uma terceira corrente de ar. a terceira corrente de ar é seletivamente escapada do terceiro duto através de um bocal secundário ou de fendas divergentes no bocal convergente-divergente ou de ambos, dependendo do modo de voo. uma válvula desviadora é posicionada no duto de terceira corrente para controlar seletivamente o fluxo de ar de terceira corrente através do bocal secundário, das fendas divergentes e combinações dos mesmos.
BR112015026459A 2013-05-07 2014-04-25 motor de turboventilador de aeronave BR112015026459A2 (pt)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/888,967 US9920710B2 (en) 2013-05-07 2013-05-07 Multi-nozzle flow diverter for jet engine
PCT/US2014/035497 WO2015012919A2 (en) 2013-05-07 2014-04-25 Multi-nozzle flow diverter for jet engine

Publications (1)

Publication Number Publication Date
BR112015026459A2 true BR112015026459A2 (pt) 2017-07-25

Family

ID=51900511

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112015026459A BR112015026459A2 (pt) 2013-05-07 2014-04-25 motor de turboventilador de aeronave

Country Status (7)

Country Link
US (1) US9920710B2 (pt)
EP (1) EP2994632A2 (pt)
JP (1) JP6471148B2 (pt)
CN (1) CN105190005B (pt)
BR (1) BR112015026459A2 (pt)
CA (1) CA2910960A1 (pt)
WO (1) WO2015012919A2 (pt)

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Also Published As

Publication number Publication date
WO2015012919A3 (en) 2015-03-26
WO2015012919A2 (en) 2015-01-29
EP2994632A2 (en) 2016-03-16
US9920710B2 (en) 2018-03-20
CA2910960A1 (en) 2015-01-29
US20140345253A1 (en) 2014-11-27
CN105190005A (zh) 2015-12-23
JP2016517927A (ja) 2016-06-20
JP6471148B2 (ja) 2019-02-13
CN105190005B (zh) 2017-10-31

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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]
B11B Dismissal acc. art. 36, par 1 of ipl - no reply within 90 days to fullfil the necessary requirements
B350 Update of information on the portal [chapter 15.35 patent gazette]