BRPI0407675A - tubeira confluente de escape - Google Patents

tubeira confluente de escape

Info

Publication number
BRPI0407675A
BRPI0407675A BRPI0407675-3A BRPI0407675A BRPI0407675A BR PI0407675 A BRPI0407675 A BR PI0407675A BR PI0407675 A BRPI0407675 A BR PI0407675A BR PI0407675 A BRPI0407675 A BR PI0407675A
Authority
BR
Brazil
Prior art keywords
main
outlet
confluent
exhaust nozzle
duct
Prior art date
Application number
BRPI0407675-3A
Other languages
English (en)
Inventor
Jean-Pierre Lair
Original Assignee
Nordam Group Inc
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 Nordam Group Inc filed Critical Nordam Group Inc
Publication of BRPI0407675A publication Critical patent/BRPI0407675A/pt
Publication of BRPI0407675B1 publication Critical patent/BRPI0407675B1/pt

Links

Classifications

    • 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
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
    • F02K1/34—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for attenuating noise
    • 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
    • F02K1/46—Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing
    • 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
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • 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
    • F02K3/077—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

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)
  • Supercharger (AREA)
  • Exhaust Silencers (AREA)

Abstract

"TUBEIRA CONFLUENTE DE ESCAPE". Descreve-se uma tubeira de escape de motor de turbina a gás (38), que inclui uma nacela (16) tendo uma entrada (32) e saída principal (46) nas extremidades opostas, e um duto principal (36) estendendo-se entre elas. Um duto secundário de derivação (48) se estende radialmente através da nacela (16) a montante da saída principal (46) e inclui uma entrada secundária (50) desobstruída, unida ao duto principal (36), e uma saída secundária (52) envolvendo a saída principal (46) para descarga coletiva do fluxo de escape em correntes confluentes.
BRPI0407675-3A 2003-02-26 2004-02-19 Bocal de escapamento convergente BRPI0407675B1 (pt)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US45012103P 2003-02-26 2003-02-26
US60/450,121 2003-02-26
PCT/US2004/004690 WO2005001247A2 (en) 2003-02-26 2004-02-19 Confluent exhaust nozzle

Publications (2)

Publication Number Publication Date
BRPI0407675A true BRPI0407675A (pt) 2006-03-01
BRPI0407675B1 BRPI0407675B1 (pt) 2019-06-04

Family

ID=33551259

Family Applications (1)

Application Number Title Priority Date Filing Date
BRPI0407675-3A BRPI0407675B1 (pt) 2003-02-26 2004-02-19 Bocal de escapamento convergente

Country Status (5)

Country Link
US (1) US6971229B2 (pt)
EP (1) EP1597472B1 (pt)
BR (1) BRPI0407675B1 (pt)
CA (1) CA2515849C (pt)
WO (1) WO2005001247A2 (pt)

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FR2890696B1 (fr) * 2005-09-12 2010-09-17 Airbus France Turbomoteur a bruit de jet attenue
MX2008015788A (es) * 2006-06-09 2009-03-06 Textron Innovations Inc Sistema de escape de motor.
US8132755B2 (en) * 2006-06-09 2012-03-13 Bell Helicopter Textron Inc. Engine exhaust system with directional nozzle
US8157207B2 (en) * 2006-08-09 2012-04-17 The Boeing Company Jet engine nozzle exit configurations, including projections oriented relative to pylons, and associated systems and methods
US7966824B2 (en) 2006-08-09 2011-06-28 The Boeing Company Jet engine nozzle exit configurations and associated systems and methods
US8015797B2 (en) 2006-09-21 2011-09-13 Jean-Pierre Lair Thrust reverser nozzle for a turbofan gas turbine engine
US7797944B2 (en) * 2006-10-20 2010-09-21 United Technologies Corporation Gas turbine engine having slim-line nacelle
US7870721B2 (en) * 2006-11-10 2011-01-18 United Technologies Corporation Gas turbine engine providing simulated boundary layer thickness increase
US7870722B2 (en) * 2006-12-06 2011-01-18 The Boeing Company Systems and methods for passively directing aircraft engine nozzle flows
US7966826B2 (en) * 2007-02-14 2011-06-28 The Boeing Company Systems and methods for reducing noise from jet engine exhaust
US8408491B2 (en) 2007-04-24 2013-04-02 United Technologies Corporation Nacelle assembly having inlet airfoil for a gas turbine engine
US8205430B2 (en) * 2007-05-16 2012-06-26 United Technologies Corporation Variable geometry nacelle assembly for a gas turbine engine
US8727267B2 (en) * 2007-05-18 2014-05-20 United Technologies Corporation Variable contraction ratio nacelle assembly for a gas turbine engine
US7766280B2 (en) * 2007-05-29 2010-08-03 United Technologies Corporation Integral suction device with acoustic panel
US8402739B2 (en) 2007-06-28 2013-03-26 United Technologies Corporation Variable shape inlet section for a nacelle assembly of a gas turbine engine
US9228534B2 (en) * 2007-07-02 2016-01-05 United Technologies Corporation Variable contour nacelle assembly for a gas turbine engine
US9759087B2 (en) 2007-08-08 2017-09-12 Rohr, Inc. Translating variable area fan nozzle providing an upstream bypass flow exit
EP2578864B1 (en) * 2007-08-08 2014-09-24 Rohr, Inc. Variable area fan nozzle with bypass flow
US10167813B2 (en) 2007-08-23 2019-01-01 United Technologies Corporation Gas turbine engine with fan variable area nozzle to reduce fan instability
US9494084B2 (en) 2007-08-23 2016-11-15 United Technologies Corporation Gas turbine engine with fan variable area nozzle for low fan pressure ratio
US9701415B2 (en) 2007-08-23 2017-07-11 United Technologies Corporation Gas turbine engine with axial movable fan variable area nozzle
US9004399B2 (en) * 2007-11-13 2015-04-14 United Technologies Corporation Nacelle flow assembly
US8052086B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser door
US7735778B2 (en) * 2007-11-16 2010-06-15 Pratt & Whitney Canada Corp. Pivoting fairings for a thrust reverser
US8172175B2 (en) 2007-11-16 2012-05-08 The Nordam Group, Inc. Pivoting door thrust reverser for a turbofan gas turbine engine
US8091827B2 (en) 2007-11-16 2012-01-10 The Nordam Group, Inc. Thrust reverser door
US8051639B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser
US8052085B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser for a turbofan gas turbine engine
US8192147B2 (en) 2007-12-14 2012-06-05 United Technologies Corporation Nacelle assembly having inlet bleed
US8186942B2 (en) 2007-12-14 2012-05-29 United Technologies Corporation Nacelle assembly with turbulators
US7762086B2 (en) * 2008-03-12 2010-07-27 United Technologies Corporation Nozzle extension assembly for ground and flight testing
US8127530B2 (en) 2008-06-19 2012-03-06 The Nordam Group, Inc. Thrust reverser for a turbofan gas turbine engine
DE102008045851A1 (de) * 2008-09-05 2010-03-11 Rolls-Royce Deutschland Ltd & Co Kg Vorrichtung zum Öffnen und Schließen einer Schubumkehrertür eines Strahltriebwerks
US8844262B2 (en) * 2009-12-29 2014-09-30 Rolls-Royce North American Technologies, Inc. Exhaust for a gas turbine engine
FR2956446B1 (fr) * 2010-02-12 2012-07-27 Turbomeca Dispositif d'ejection de gaz d'un moteur a turbine a gaz et moteur a turbine a gaz
US10041442B2 (en) * 2010-06-11 2018-08-07 United Technologies Corporation Variable area fan nozzle
FR2971553B1 (fr) * 2011-02-10 2015-05-29 Eads Europ Aeronautic Defence Reacteur a signature acoustique reduite
US8955304B2 (en) 2012-02-10 2015-02-17 United Technologies Corporation Gas turbine engine with modular cores and propulsion unit
US8789354B2 (en) 2012-02-10 2014-07-29 United Technologies Corporation Gas turbine engine with separate core and propulsion unit
GB201220378D0 (en) * 2012-11-13 2012-12-26 Rolls Royce Plc A gas turbine engine exhaust nozzle
US9759133B2 (en) 2013-03-07 2017-09-12 Rolls-Royce Corporation Turbofan with variable bypass flow
US10371093B2 (en) 2013-03-08 2019-08-06 Rolls-Royce North American Technologies Inc. Aircraft nozzle with a variable nozzle area of a second flow path
US10040563B1 (en) * 2013-04-11 2018-08-07 Geoffrey P. Pinto Dual panel actuator system for jet engines
US10400710B2 (en) * 2013-05-07 2019-09-03 General Electric Company Secondary nozzle for jet engine
US9920710B2 (en) 2013-05-07 2018-03-20 General Electric Company Multi-nozzle flow diverter for jet engine
US20150267644A1 (en) * 2014-03-19 2015-09-24 The Boeing Company Integrated Primary Nozzle
FR3030452A1 (fr) * 2014-12-17 2016-06-24 Aircelle Sa Nacelle pour un turboreacteur d'aeronef double flux

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Also Published As

Publication number Publication date
CA2515849A1 (en) 2005-01-06
US20050204742A1 (en) 2005-09-22
EP1597472A4 (en) 2011-11-23
US6971229B2 (en) 2005-12-06
WO2005001247A2 (en) 2005-01-06
BRPI0407675B1 (pt) 2019-06-04
EP1597472B1 (en) 2018-06-20
CA2515849C (en) 2011-05-24
EP1597472A2 (en) 2005-11-23
WO2005001247A3 (en) 2005-09-22

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Legal Events

Date Code Title Description
B06A Patent application procedure suspended [chapter 6.1 patent gazette]
B25G Requested change of headquarter approved

Owner name: THE NORDAM GROUP, INC. (US)

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: 10 (DEZ) ANOS CONTADOS A PARTIR DE 04/06/2019, OBSERVADAS AS CONDICOES LEGAIS. (CO) 10 (DEZ) ANOS CONTADOS A PARTIR DE 04/06/2019, OBSERVADAS AS CONDICOES LEGAIS

B25F Entry of change of name and/or headquarter and transfer of application, patent and certif. of addition of invention: change of name on requirement

Owner name: THE NORDAM GROUP, INC. (US)

Free format text: A FIM DE ATENDER A ALTERACAO DE NOME REQUERIDA ATRAVES DA PETICAO NO 870200148319, DE 24/11/2020, E NECESSARIO APRESENTAR O DOCUMENTO NOTARIZADO E COM APOSTILAMENTO OU LEGALIZACAO CONSULAR, ALEM DA GUIA DE CUMPRIMENTO DE EXIGENCIA.

B25E Requested change of name of applicant rejected

Owner name: THE NORDAM GROUP, INC. (US)

Free format text: INDEFERIDO O PEDIDO DE ALTERACAO DE NOME CONTIDO NA PETICAO 870200148319 DE 24/11/2020, POR AUSENCIA DE CUMPRIMENTO DA EXIGENCIA PUBLICADA NA RPI NO 2623, DE 13/04/2021.

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

Free format text: REFERENTE A 18A 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 2658 DE 14-12-2021 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.