BR0311164A - Bocal com turbo-ventilador bifurcado - Google Patents

Bocal com turbo-ventilador bifurcado

Info

Publication number
BR0311164A
BR0311164A BR0311164-4A BR0311164A BR0311164A BR 0311164 A BR0311164 A BR 0311164A BR 0311164 A BR0311164 A BR 0311164A BR 0311164 A BR0311164 A BR 0311164A
Authority
BR
Brazil
Prior art keywords
fan
duct
nozzle
turbocharged
fork
Prior art date
Application number
BR0311164-4A
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 BR0311164A publication Critical patent/BR0311164A/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/30—Exhaust heads, chambers, or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
    • B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
    • 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
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • 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
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • F02K1/1207—Varying effective area of jet pipe or nozzle by means of pivoted flaps of one series of flaps hinged at their upstream ends on a fixed structure
    • 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
    • F02K1/38—Introducing air inside the jet
    • F02K1/386—Introducing air inside the jet mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
    • 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
    • F02K1/40—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet
    • 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
    • F02K1/40—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet
    • F02K1/42—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet the means being movable into an inoperative position
    • 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
    • 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
    • F05D2220/327—Application in turbines in gas turbines to drive shrouded, high solidity propeller
    • 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
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Abstract

"BOCAL COM TURBO-VENTILADOR BIFURCADO". Um bocal de escapamento com turbo-ventilador (28) inclui um conduto de ventilador (40) definido entre uma nacela de ventilador (23) e uma capota de motor de núcleo (30). O conduto de ventilador (40) inclui uma parede de extremidade longitudinal (48) e uma partição afastada dela de modo a se definir um conduto de fluxo secundário (52). O conduto de ventilador (40) inclui também uma saída primária (42), e o conduto secundário (52) inclui uma saída secundária (54). A partição (50) entre os dois condutos inclui uma abertura (56) coberta por um flape seletivamente móvel (58).
BR0311164-4A 2002-05-21 2003-05-19 Bocal com turbo-ventilador bifurcado BR0311164A (pt)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US38239702P 2002-05-21 2002-05-21
PCT/US2003/015644 WO2003099654A2 (en) 2002-05-21 2003-05-19 Bifurcated turbofan exhaust nozzle

Publications (1)

Publication Number Publication Date
BR0311164A true BR0311164A (pt) 2005-08-16

Family

ID=29584407

Family Applications (1)

Application Number Title Priority Date Filing Date
BR0311164-4A BR0311164A (pt) 2002-05-21 2003-05-19 Bocal com turbo-ventilador bifurcado

Country Status (5)

Country Link
US (1) US6820410B2 (pt)
EP (1) EP1509447A4 (pt)
BR (1) BR0311164A (pt)
CA (1) CA2486175A1 (pt)
WO (1) WO2003099654A2 (pt)

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US8997454B2 (en) * 2002-03-20 2015-04-07 The Regents Of The University Of California Turbofan engine noise suppression using fan flow deflector
GB0505184D0 (en) * 2005-03-14 2005-04-20 Rolls Royce Plc Thrust reverser mounting structure
US20110101158A1 (en) * 2005-03-29 2011-05-05 The Boeing Company Thrust Reversers Including Monolithic Components
US7721551B2 (en) * 2006-06-29 2010-05-25 United Technologies Corporation Fan variable area nozzle for a gas turbine engine fan nacelle
FR2905734B1 (fr) * 2006-09-07 2012-07-13 Airbus France Dispositif permettant d'ameliorer l'efficacite des traitements acoustiques dans un conduit d'une motorisation d'aeronef
US8015797B2 (en) 2006-09-21 2011-09-13 Jean-Pierre Lair Thrust reverser nozzle for a turbofan gas turbine engine
WO2008045063A1 (en) 2006-10-12 2008-04-17 United Technologies Corporation Variable area nozzle assisted gas turbine engine restarting
EP2074317B1 (en) * 2006-10-12 2012-03-07 United Technologies Corporation Nacelle assembly for a gas turbine engine comprising a pylon located in the fan bypass flow path with a variable area flow system
US8137060B2 (en) * 2006-10-12 2012-03-20 United Technologies Corporation Actuation of a turbofan engine bifurcation to change an effective nozzle exit area
EP2069629B1 (en) 2006-10-12 2014-09-24 United Technologies Corporation Gas turbine engine fan variable area nozzle with swivalable insert system
EP2074313B1 (en) * 2006-10-12 2014-07-09 United Technologies Corporation Fan variable area nozzle with electromechanical actuator
WO2008045094A1 (en) * 2006-10-12 2008-04-17 United Technologies Corporation Bifurcation and aft vent used to vary fan nozzle exit area
WO2008045050A1 (en) * 2006-10-12 2008-04-17 United Technologies Corporation Gas turbine engine with fan variable area nozzle, nacelle assembly and method of varying area of a fan nozzle
US7726116B2 (en) * 2006-11-14 2010-06-01 General Electric Company Turbofan engine nozzle assembly and method of operating same
US7673458B2 (en) * 2006-11-14 2010-03-09 General Electric Company Turbofan engine nozzle assembly and method for operating the same
GB0700238D0 (en) 2007-01-06 2007-02-14 Rolls Royce Plc Nozzle arrangement
US20080273961A1 (en) 2007-03-05 2008-11-06 Rosenkrans William E Flutter sensing and control system for a gas turbine engine
US7966827B2 (en) * 2007-05-31 2011-06-28 United Technologies Corporation Gas turbine engine with fan variable area nozzle having a rotational valve system
FR2920197B1 (fr) * 2007-08-20 2013-08-09 Aircelle Sa Ressort pour volet d'inverseur de poussee a grilles pour turboreacteur d'aeronef
US8051639B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser
US8091827B2 (en) 2007-11-16 2012-01-10 The Nordam Group, Inc. Thrust reverser door
US8172175B2 (en) 2007-11-16 2012-05-08 The Nordam Group, Inc. Pivoting door thrust reverser for a turbofan gas turbine engine
US8052085B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser for a turbofan gas turbine engine
US7735778B2 (en) * 2007-11-16 2010-06-15 Pratt & Whitney Canada Corp. Pivoting fairings for a thrust reverser
US8052086B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser door
US8127530B2 (en) 2008-06-19 2012-03-06 The Nordam Group, Inc. Thrust reverser for a turbofan gas turbine engine
US9181899B2 (en) * 2008-08-27 2015-11-10 General Electric Company Variable slope exhaust nozzle
US9885313B2 (en) * 2009-03-17 2018-02-06 United Technologes Corporation Gas turbine engine bifurcation located fan variable area nozzle
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GB201007215D0 (en) 2010-04-30 2010-06-16 Rolls Royce Plc Gas turbine engine
US9022311B2 (en) 2010-08-20 2015-05-05 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Active aircraft pylon noise control system
US8651429B2 (en) 2010-08-20 2014-02-18 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Blended cutout flap for reduction of jet-flap interaction noise
US8876043B2 (en) * 2010-08-20 2014-11-04 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Aircraft engine exhaust nozzle system for jet noise reduction
US8549834B2 (en) 2010-10-21 2013-10-08 United Technologies Corporation Gas turbine engine with variable area fan nozzle
FR2975971B1 (fr) * 2011-06-01 2013-05-17 Aircelle Sa Nacelle pour un turboreacteur double flux d'un aeronef
US9249731B2 (en) 2012-06-05 2016-02-02 United Technologies Corporation Nacelle bifurcation for gas turbine engine
GB201220378D0 (en) * 2012-11-13 2012-12-26 Rolls Royce Plc A gas turbine engine exhaust nozzle
JP6317946B2 (ja) * 2014-02-18 2018-04-25 三菱航空機株式会社 航空機
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US9810178B2 (en) 2015-08-05 2017-11-07 General Electric Company Exhaust nozzle with non-coplanar and/or non-axisymmetric shape
US10040560B2 (en) * 2015-09-30 2018-08-07 The Boeing Company Trailing edge core compartment vent for an aircraft engine
US9863368B1 (en) * 2016-09-09 2018-01-09 Florida Turbine Technologies, Inc. Aircraft with gas turbine engine having outer bypass elements removed
PL419827A1 (pl) * 2016-12-16 2018-06-18 General Electric Company Rozpórki do ram wylotowych systemów turbin
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FR3074227B1 (fr) * 2017-11-28 2020-02-28 Airbus Operations Structure interne d'un conduit d'ejection primaire
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Also Published As

Publication number Publication date
WO2003099654A2 (en) 2003-12-04
CA2486175A1 (en) 2003-12-04
WO2003099654A3 (en) 2004-08-05
EP1509447A4 (en) 2010-07-21
US20040187476A1 (en) 2004-09-30
US6820410B2 (en) 2004-11-23
EP1509447A2 (en) 2005-03-02

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Legal Events

Date Code Title Description
B08F Application fees: application dismissed [chapter 8.6 patent gazette]

Free format text: REFERENTE 6A. E 8A, ANUIDADE(S).

B08K Patent lapsed as no evidence of payment of the annual fee has been furnished to inpi [chapter 8.11 patent gazette]

Free format text: NAO APRESENTADA A GUIA DE CUMPRIMENTO DE EXIGENCIA. REFERENTE AS 8A E 9A ANUIDADES.