BR0303430A - Sistema de controle ativo de área de passagem de fluxo efetivo, sistema de controle fluìdico de área de passagem de fluxo efetivo, entrada de área de passagem de fluxo efetivo e variável de um motor de aeronave, método para a mudança ativa de uma área de passagem de fluxo efetivo de uma região de entrada de um motor de aeronave e método fluìdico para a mudança ativa de uma área de passagem de fluxo efetivo de uma região de entrada de um motor de aeronave - Google Patents

Sistema de controle ativo de área de passagem de fluxo efetivo, sistema de controle fluìdico de área de passagem de fluxo efetivo, entrada de área de passagem de fluxo efetivo e variável de um motor de aeronave, método para a mudança ativa de uma área de passagem de fluxo efetivo de uma região de entrada de um motor de aeronave e método fluìdico para a mudança ativa de uma área de passagem de fluxo efetivo de uma região de entrada de um motor de aeronave

Info

Publication number
BR0303430A
BR0303430A BR0303430-5A BR0303430A BR0303430A BR 0303430 A BR0303430 A BR 0303430A BR 0303430 A BR0303430 A BR 0303430A BR 0303430 A BR0303430 A BR 0303430A
Authority
BR
Brazil
Prior art keywords
effective
passage area
aircraft engine
flow
control system
Prior art date
Application number
BR0303430-5A
Other languages
English (en)
Other versions
BR0303430B1 (pt
Inventor
Anurag Gupta
Paolo Graziosi
Ramani Mani
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 BR0303430A publication Critical patent/BR0303430A/pt
Publication of BR0303430B1 publication Critical patent/BR0303430B1/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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • 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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
    • B64D2033/0286—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for turbofan engines
    • 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
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/126—Baffles or ribs
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • 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
    • Y02T50/10—Drag reduction
    • 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)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)

Abstract

"SISTEMA DE CONTROLE ATIVO DE áREA DE PASSAGEM DE FLUXO EFETIVO, SISTEMA DE CONTROLE FLUìDICO DE áREA DE PASSAGEM DE FLUXO EFETIVO, ENTRADA DE áREA DE PASSAGEM DE FLUXO EFETIVO E VARIáVEL DE UM MOTOR DE AERONAVE, MéTODO PARA A MUDANçA ATIVA DE UMA áREA DE PASSAGEM DE FLUXO EFETIVO DE UMA REGIãO DE ENTRADA DE UM MOTOR DE AERONAVE E MéTODO FLUìDICO PARA A MUDANçA ATIVA DE UMA áREA DE PASSAGEM DE FLUXO EFETIVO DE UMA REGIãO DE ENTRADA DE UM MOTOR DE AERONAVE". A presente invenção refere-se a um sistema ativo de controle de área de passagem de fluxo efetivo (100) inclui um agitador de fluxo de parede a montante (20) situado em uma região de entrada (110) de um motor de aeronave (120). O agitador de fluxo de parede a jusante fica posicionado a jusante do agitador de fluxo de parede a montante. Os agitadores de fluxo de parede a montante e a jusante são configurados de modo a gerar e prender pelo menos uma região de turbilhonamento independente (150) no fluxo de ar através da região de entrada. Um método, para a mudança ativa de uma área de passagem de fluxo efetivo de uma região de entrada de um motor de aeronave, inclui a criação de pelo menos uma região de turbilhonamento independente em uma passagem de fluxo de ar (114) definida pela região de entrada. O método inclui ainda o aprisionamento da região de turbilhonamento independente na passagem de fluxo de ar. A região do turbilhonamento independente obstrui parcialmente um fluxo de ar de entrada principal.
BRPI0303430-5A 2002-08-27 2003-08-27 sistema de controle ativo de Área de passagem de fluxo efetivo, sistema de controle fluÍdico de Área de passagem de fluxo efetivo, entrada de Área de passagem de fluxo efetivo e variÁvel de um motor de aeronave, mÉtodo para a mudanÇa ativa de uma Área de passagem de fluxo efetivo de uma regiço de entrada de um motor de aeronave e mÉtodo fluÍdico para a mudanÇa ativa de uma Área de passagem de fluxo efetivo de uma regiço de entrada de um motor de aeronave. BR0303430B1 (pt)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US10/064,884 US6655632B1 (en) 2002-08-27 2002-08-27 System and method for actively changing an effective flow-through area of an inlet region of an aircraft engine

Publications (2)

Publication Number Publication Date
BR0303430A true BR0303430A (pt) 2004-09-08
BR0303430B1 BR0303430B1 (pt) 2012-06-12

Family

ID=29547861

Family Applications (1)

Application Number Title Priority Date Filing Date
BRPI0303430-5A BR0303430B1 (pt) 2002-08-27 2003-08-27 sistema de controle ativo de Área de passagem de fluxo efetivo, sistema de controle fluÍdico de Área de passagem de fluxo efetivo, entrada de Área de passagem de fluxo efetivo e variÁvel de um motor de aeronave, mÉtodo para a mudanÇa ativa de uma Área de passagem de fluxo efetivo de uma regiço de entrada de um motor de aeronave e mÉtodo fluÍdico para a mudanÇa ativa de uma Área de passagem de fluxo efetivo de uma regiço de entrada de um motor de aeronave.

Country Status (4)

Country Link
US (1) US6655632B1 (pt)
EP (1) EP1394388A3 (pt)
JP (1) JP2004084669A (pt)
BR (1) BR0303430B1 (pt)

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Also Published As

Publication number Publication date
EP1394388A3 (en) 2006-07-05
US6655632B1 (en) 2003-12-02
BR0303430B1 (pt) 2012-06-12
JP2004084669A (ja) 2004-03-18
EP1394388A2 (en) 2004-03-03

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Legal Events

Date Code Title Description
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 27/08/2003, OBSERVADAS AS CONDICOES LEGAIS.

B21F Lapse acc. art. 78, item iv - on non-payment of the annual fees in time

Free format text: REFERENTE A 16A ANUIDADE.

B24J Lapse because of non-payment of annual fees (definitively: art 78 iv lpi, resolution 113/2013 art. 12)

Free format text: EM VIRTUDE DA EXTINCAO PUBLICADA NA RPI 2529 DE 25-06-2019 E CONSIDERANDO AUSENCIA DE MANIFESTACAO DENTRO DOS PRAZOS LEGAIS, INFORMO QUE CABE SER MANTIDA A EXTINCAO DA PATENTE E SEUS CERTIFICADOS, CONFORME O DISPOSTO NO ARTIGO 12, DA RESOLUCAO 113/2013.